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Behavior of Extraction Parachutes in the Wake of a Powered Airplane Model.
Report Number: AFFDL TR 68-15
Author(s): Heinrich, Helmut G.; Hulcher, G. D.
Corporate Author: Minnesota Univ Minneapolis Dept Of Aeronautics And Engineering Mechanics
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1968
Pages: 102
Contract: F33615-67-C-1010
Project: 6065
Task: 606503
AD Number: AD0842569
Photo Enhancement: Complete
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Preliminary Design and Experimental Investigation of the FDL-5A Unmanned High L/D Spacecraft: Part I - Summary
Report Number: AFFDL TR 68-24 Part 1
Author(s): J. T. Lloyd
Corporate Author: Lockheed-California Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1968
Pages: 89
Features: + Foldout(s)
Contract: AF 33(615)-5241
Project: 1366
Task: 136616
AD Number: AD0390193
Photo Enhancement: Complete
Abstract Text:
Conceptual design and experimental wind tunnel testing of unmanned entry research vehicles having high hypersonic lift/drag ration and high volume are desribed. Analytic parametic data are presented for two lifting body classes designated HLD-35 and FDL-5. The FDL-5 is a unique configuration which is aerodynamically stabilized without outboard fins. Experimental aerodynamic and heat transfer data from the Arnold Engineering Development Center Wind Tunnels A, B, C and F are compared with analytic data for the FDL-5. Candidate structure and subsystems are selected for performing unmanned hypersonic research with the vehicle.
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Preliminary Design and Experimental Investigation of the FDL-5A Unmanned High L/D Spacecraft: Part II - Parametric Configuration Development and Evaluation
Report Number: AFFDL TR 68-24 Part 2
Author(s): C. F. Ehrlich; F. L. Guard
Corporate Author: Lockheed-California Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1968
Pages: 160
Features: + Foldout(s)
Contract: AF 33(615)-5241
Project: 1366
Task: 136616
AD Number: AD0390194
Photo Enhancement: Not Needed
Abstract Text:
The derivation of two volumetric efficient high L/D entry vehicles is described. Parametric trades in the areas of aerodynamics and aerothermodynamics are discussed and selected parameters are identified. Alternate modes of vehicle recovery are described and the effect on vehicle design determined. The evolution of the FDL-5 configuration selected for wind tunnel testing is described through the presentation of a series of intermediate configurations.
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Preliminary Design and Experimental Investigation of the FDL-5A Unmanned High L/D Spacecraft: Part III - Aerodynamics
Report Number: AFFDL TR 68-24 Part 3
Author(s): C. F. Ehrlich; J. J. Rising; R. S. Peyton; C. M. Onspaugh
Corporate Author: Lockheed-California Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1968
Pages: 551
Features: + Foldout(s)
Contract: AF 33(615)-5241
Project: 1366
Task: 136616
AD Number: AD0390195
Photo Enhancement: Complete
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Preliminary Design and Experimental Investigation of the FDL-5A Unmanned High L/D Spacecraft: Part IV - Aerothermodynamics
Report Number: AFFDL TR 68-24 Part 4
Author(s): F. L. Guard; H. D. Schultz
Corporate Author: Lockheed-California Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1968
Pages: 408
Features: + Foldout(s)
Contract: AF 33(615)-5241
Project: 1366
Task: 136616
AD Number: AD0390205
Photo Enhancement: Complete
Abstract Text:
Design and experimental analyses of unmanned entry research vehicles having high hypersonic L/D and high volume are described. Analytic parametric data are presented for two lifting body classes designated HLD-35 and FDL-5. Experimental aerodynamic and heat transfer data obtained from Arnold Engineering Development Wind Tunnels A, B, C, and F are compared with analytic data for the FDL-5 vehicle. Structure and subsystems are selected for performing unmanned hypersonic research with the vehicle.
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Preliminary Design and Experimental Investigation of the FDL-5A Unmanned High L/D Spacecraft: Part V - Vehicle Design
Report Number: AFFDL TR 68-24 Part 5
Author(s): P. P. Plank; I. F. Sakata; M. Verhaegh
Corporate Author: Lockheed-California Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1968
Pages: 125
Features: + Foldout(s)
Contract: AF 33(615)-5241
Project: 1366
Task: 136616
AD Number: AD0390196
Photo Enhancement: Not Needed
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Design, Fabrication, Testing, And Data Analysis Of Adam II Concept (Propulsive Wing). Part I, General And Summary Information
Report Number: AFFDL TR 68-31 Part 1
Author(s): McClure, James G.; Shumway, Justin F.; Cragin, Glen P.; Jr
Corporate Author: LTV Aerospace Corp Dallas Tx Vought Aeronautics Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 5/1/1968
Pages: 89
Features: + Drawing(s) + Foldout(s) + Photo(s) + Table(s)
Contract: AF 33(615)-3293
Project: 1366
Task: 136617
AD Number: AD0832603
Photo Enhancement: Complete
Abstract Text:
Design, fabrication, testing, and data analysis of an ADAM II concept (propulsive wing) V/STOL airplane model has been performed by the Vought Aeronautics Division, LTV Aerospace Corporation, Dallas, Texas, under a contract supported jointly by the United States Air Force and the United States Army. The actual testing was conducted by the personnel of the NASA Langley Research Center (LRC) in the 17-foot test section of the LRC 7-foot by 10-foot low speed wind tunnel and in the LRC 16-foot transonic wind tunnel. The results detailed in Parts II, III, and IV are generally favorable and have led to a recommendation for continued development of the ADAM II concept.
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Design, Fabrication, Testing, And Data Analysis Of Adam II Concept (Propulsive Wing). Part II. Shakedown Testing In Vad 7-Ft X 10-Ft Low Speed Wind Tunnel
Report Number: AFFDL TR 68-31 Part 2
Author(s): Meyer, Robert D.; English, Robert B.; Davidson, Jim K.
Corporate Author: LTV Aerospace Corp Dallas Tx Vought Aeronautics Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 5/1/1968
Pages: 54
Features: + Drawing(s) + Foldout(s) + Graph(s) + Table(s)
Contract: AF 33(615)-3293
Project: 1366
Task: 136617
AD Number: AD0832604
Photo Enhancement: Not Needed
Abstract Text:
An analysis is presented of the data obtained from a short series of tests to "shakedown" a powered model of the ADAM II V/STOL concept. Correlating data from tests of a related semispan model are also included. Results show that the longitudinal stability of the present configuration in the cruise mode has a greater nariation with angle of attack and power than conventional airplanes. The data indicated that, for this test, possible lower surface flap separation and detached nose fan exit flow caused nonlinearities in pitching moment. These can be eliminated by redesign at critical points to provide good stability. The location of the horizontal tails in the wing tip vortex results in an upwash derivative (negative d(espilon)/d(alpha)) that results in a high level of horizontal tail contribution to stability. Although the basic low aspect ration horizontal tails were highly loaded and operating wih disturbed flow conditions much of the time, there was no indication of tail stall. Horizontal tail control effectiveness appears to be adequate at the present stability levels. The model was less stable directionally than longitudinally in the sense that a greater forward movement in c. g. location is required for neutral stability. In this test, directional stability was independent of angle of attack and power effects, and lateral stability was at all times positive and varied with angle of attack and power effects.
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Design, Fabrication, Testing, And Data Analysis Of Adam II Concept (Propulsive Wing). Part III, Testing In 17 Ft Test Section Of 7 Ft X 10 Ft Wind Tunnel, Nasa Langley Research Center
Report Number: AFFDL TR 68-31 Part 3
Author(s): Brownrigg, William E., Jr.; Meyer, Robert D.; English, Robert B.
Corporate Author: LTV Aerospace Corp Dallas Tx Vought Aeronautics Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 5/1/1968
Pages: 101
Features: + Diagram(s) + Foldout(s) + Graph(s)
Contract: AF 33(615)-3293
Project: 1366
Task: 136617
AD Number: AD0832605
Photo Enhancement: Not Needed
Abstract Text:
An analysis of selected data obtained from a low speed wind tunnel test of a straight, low aspect ratio propulsive wing V/STOL aircraft concept is presented. Essential features of the model are four compressed air tip driven fans in the wing with vectroable exhaust, fixed exhausts blwoing over the top of the flap simulating hot gas turbine exhaust, a forward-facing nose fan for pitch control with a vectorable exhaust, and tail surfaces mounted on booms extending aft as part of the wing tips. The model was tested in the V/STOL mode where the propulsive flows were defelected symmetrically downward by internal vanes at 30, 60, and 90 degrees and by flap deflections from 30 to 90 degrees. Stability, control, and a limited amount of pressure data were obtained for various flow deflections, momentum co-efficients, configuration changes, and ground board heights. Because of the proximity of the tails to the wing tip vortex, the horizontal tail contribution to the longitudinal stability is increased due to favorable upwash, and the directional stability contribution of the vertical tail is reduced due to high angles of sidewash. Removing the vertical tails from the booms and adding a centerline vertical tail to the fuselage improved directional stability and the linearity of the pitching moment curves. At high momentum coefficients, the high velocity propulsive flow induces additional dynamic pressure at the horizontal tails, and control effectiveness is improved. At low momentum coefficients the horizontal tail effectiveness is low. Control by deflectiion of the propulsive flow with wing vanes and flaps is adequate. In general, the effect of the ground board is to increase thrust-included lift by increasing bottom surface pressures and to reduce the effective exhaust flow deflection angle. Drag increments due to ground effects vary with vane and flap defelctions.
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Design, Fabrication, Testing, And Data Analysis Of Adam II Concept (Propulsive Wing). Part IV. Testing In The Langley Research Center 16-Foot Transonic Wind Tunnel
Report Number: AFFDL TR 68-31 Part 4
Author(s): English, Robert B.; Brownrigg, William E., Jr.; Davidson, Jim K.
Corporate Author: LTV Aerospace Corp Dallas Tx Vought Aeronautics Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 5/1/1968
Pages: 174
Features: + Foldout(s) + Graph(s) + Photo(s) + Table(s)
Contract: AF 33(615)-3293
Project: 1366
Task: 136617
AD Number: AD0832606
Photo Enhancement: Complete
Abstract Text:
An analysis of data obtained from a high speed wind tunnel test of a straight, low aspect ratio propulsive wing V/STOL aircraft concept is presented. Essential features of the model are four compressed-air tip driven fans in the wing with vectorable exhaust, fixed exhausts blowing over the top of a remotely controlled flap simulating hot gas turbine exhaust velocities, a forward-facing nose fan for pitch control with vectorable exhaust, horizontal tail surfaces mounted on booms extending aft as part of the wing tips, and a centerline vertical tail. The model was tested in the cruise mode, where the propulsive flows were deflected symmetrically by flap deflections ranging from 0 to 41 degrees. Stability, control, and a limited amount of pressure data were obtained for various momentum coefficients, Mach numbers, and configuration changes. Results in terms of drag-rise Mach number and flying qualities are generally satisfactory. The small capture-area wing inlets tested with the fan nose configuration indicated an improvement in drag and stability over the large capture-area inlets. Because of the proximity of the horizontal tails to the wing tip vortex, the horizontal tail contribution to longitudinal stability is increased due to favorable upwash. The centerline vertical tail provides an improvement to directional stability over the outboard vertical tails. While these Langley wind tunnel test results have contributed data and insight to the ADAM II propulsive wing concept, certain aspects of the data indicate the need for additional wind tunnel testing.
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Large Deflection And Stability Analysis Of Two-Dimensional Truss And Frame Structures
Report Number: AFFDL TR 68-38
Author(s): Przemieniecki, John S.; Purdy, David M.
Corporate Author: Air Force Flight Dynamics Lab Wright-Patterson AFB Ohio
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 5/1/1968
Pages: 64
Contract: Laboratory Research - No Contract
Project: 1467
Task: 146701
AD Number: AD0672816
Photo Enhancement: Not Needed
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Evaluation And Utilization Of Airplane Flight Loads Data. Part I. Techniques And Uncertainities
Report Number: AFFDL TR 68-52 Part 1
Author(s): Gray, Cory L.
Corporate Author: Measurement Analysis Corp Los Angeles CA
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 5/1/1968
Pages: 176
Contract: AF 33615-67-C-1033
Project: 1367
Task: 136716
AD Number: AD0835798
Photo Enhancement: Not Needed
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Evaluation And Utilization Of Airplane Flight Loads Data. Part II. Data Acquisition Equipment Performance And Accuracy
Report Number: AFFDL TR 68-52 Part 2
Author(s): Rentz, Peter E.
Corporate Author: Measurement Analysis Corp Los Angeles CA
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 5/1/1968
Pages: 240
Contract: AF 33615-67-C-1033
Project: 1367
Task: 136716
AD Number: AD0835799
Photo Enhancement: Not Needed
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Multiple Time Scales Approach To The Analysis Of Linear Systems.
Report Number: AFFDL TR 68-60
Author(s): Ramnath, Rudrapatna V.
Corporate Author: Princeton Univ N J
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 10/1/1968
Pages: 202
Contract: AF 33(615)-3657
Project: 8219
Task: 821904
AD Number: AD0680015
Photo Enhancement: Not Needed
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Compilation Of Computer Programs In Flight Vehicle Technology 1964-1967
Report Number: AFFDL TR 68-66
Author(s): Nutt, Ambrose B.
Corporate Author: Air Force Flight Dynamics Lab Wright-Patterson AFB Ohio
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 4/1/1968
Pages: 154
Contract: Laboratory Research - No Contract
Project: None Given
Task: None Given
AD Number: AD0835368
Photo Enhancement: Not Needed
Notes: Bibliography
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Vuilleumier Cycle Cryogenic Refrigerator Development
Report Number: AFFDL TR 68-67
Author(s): F. N. Magee; R. D. Doering
Corporate Author: Hughes Aircraft Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1968
Pages: 255
Features: + Diagram(s) + Drawing(s) + Foldout(s) + Graph(s) + Photo(s) + Table(s)
Contract: F33615-67-C-1532
Project: 1470
Task: 147001
AD Number: AD0841543
Photo Enhancement: Not Needed
Abstract Text:
This report covers Phase I effort in an exploratory development program to evaluate the Vuillemier heat driven refrigeratiion cycle for aircraft and spacecraft cryogenic applications. The effort includes a study of the theoretical aspects of the cycle and development of three miniature breadboard cryogenic refrigerators based on the cycle and operated by electric powered heating capsules. Two of the breadboard units are of identical design; these deliver 2 watts cooling capacity at 77 degrees K. The remaining breadboard is a two-stage unit designed to deliver 0.5 watt aat 30 degrees K and 5 watts at 75 degrees K. Performance data from these units were incorporated in the theoretical study. All units met their design requirements and confirmed the feasibility and inherent advantages of. The Vuillemier cycle for miniature long-life cryogenic refrigerators for both aircraft and spacecraft applications.
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Study And Simulation Program To Investigate The Mechanization Of An Aircraft Flight Control System That Employs Direct Lift. Volume II. Pilot-In-The-Loop Simulation Study Of Direct Lift Control.
Report Number: AFFDL TR 68-69 Volume 2
Author(s): Chase, Thomas W.; Falkner, Victor L;. Helfinstine, Robert F.
Corporate Author: Honeywell Inc Minneapolis MN Aerospace Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 6/1/1968
Pages: 218
Contract: F33615-67-C-1502
Project: 8225
Task: 822505
AD Number: AD0835102
Photo Enhancement: Complete
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Cathode Ray Tube Centered Horizontal Situation Indicator
Report Number: AFFDL TR 68-71
Author(s): Sobocinski, R. S.
Corporate Author: Astronautics Corp Of America Milwaukee WI
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 5/1/1968
Pages: 100
Contract: F33615-67-C-1316
Project: None Given
Task: None Given
AD Number: AD0839574
Photo Enhancement: Complete
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Pilot Rating Techniques for the Estimation and Evaluation of Handling Qualities
Report Number: AFFDL TR 68-76
Author(s): John H. McDonnell
Corporate Author: Systems Technology, Inc.
Laboratory: Air Force Flight Dynamics Laboartory
Publication Date: 12/1/1968
Pages: 214
Contract: AF 33(615)-3960
Project: None Given
Task: None Given
AD Number: AD0681845
Photo Enhancement: Not Needed
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Flight Test Investigation of Transonic Shock-Boundary Layer Phenomena
Report Number: AFFDL TR 68-84 Volume 1
Author(s): Jones F. Cahill; Bill L. Cooper
Corporate Author: Lockheed-Georgia Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 7/1/1968
Pages: 78
Contract: F33615-67-C-1777
Project: None Given
Task: None Given
AD Number: AD0835774
Photo Enhancement: Complete
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Improved Radiant Heat Source
Report Number: AFFDL TR 68-93
Author(s): Cass, L. A.
Corporate Author: Avco Government Products Group Wilmington Ma Avco Space Systems Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1968
Pages: 124
Contract: AF 33(615)-5384
Project: 1347
Task: 134704
AD Number: AD0848023
Photo Enhancement: Complete
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Turbulent Boundary Layer Skin Friction, Heat Transfer and Pressure Measurements on Hypersonic Inlet Compression Surfaces
Report Number: AFFDL TR 68-102
Author(s): M. O. Ryder, Jr.
Corporate Author: Cornell Aeronautical Laboratory
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 7/1/1968
Pages: 144
Contract: F33615-67-C-1203
Project: 1366
Task: None Given
AD Number: AD0672836
Photo Enhancement: Complete
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Development Of Experimental Solid State Engine Instrument Displays.
Report Number: AFFDL TR 68-104
Author(s): King, Robert C.
Corporate Author: Westinghouse Electric Corp Newbury Park CA Astroelectronics Lab
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 9/1/1968
Pages: 40
Contract: F33615-67-C-1818
Project: 6190
Task: 619009
AD Number: AD0841816
Photo Enhancement: Complete
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Inhibition Of Flow Separation At High Speed. Volume III. Experimental Results For Laminar Boundary Layers.
Report Number: AFFDL TR 68-119 Volume 3
Author(s): Nielsen, Jack N.; Lynes, Larry L.; Goodwin, Frederick K.
Corporate Author: Nielsen Engineering And Research Inc Palo Alto Calif
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1969
Pages: 64
Contract: F33615-67-C-1096
Project: 8219
Task: 821902
AD Number: AD0686800
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Analysis of the Elastic Contact of a Hollow Ball with a Flat Plate.
Report Number: AFFDL TR 68-123
Author(s): Rumbarger, John H.; Herrick, R. Clyde
Corporate Author: Franklin Inst Research Labs Philadelphia PA
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 1/1/1969
Pages: 62
Contract: F33615-C-68-1203
Project: 1315
Task: 131502
AD Number: AD0851361
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Computer-Display Feasibility Study for Flight Performance Optimization.
Report Number: AFFDL TR 68-125
Author(s): Dunlap, D. F.; Ursel, L. V.; Jeffery, D. B.; Bolz, E. H.; Polhemus, W. I.
Corporate Author: Polhemus Associates Inc Ann Arbor Mi
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 10/1/1968
Pages: 162
Contract: F33615-C-68-1253
Project: 6190
Task: 619008
AD Number: AD0844468
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Developments In Discrete Element Finite Deflection Structural Analysis By Function Minimization.
Report Number: AFFDL TR 68-126
Author(s): Schmit, Lucien A., Jr
Corporate Author: Case-Western Reserve Univ Cleveland Ohio School Of Engineering
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 9/1/1968
Pages: 312
Contract: AF 33(615)-3432
Project: 1467
Task: 146701
AD Number: AD0678064
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Application of Multiparameter Flight Loads Data to Structural Design Criteria. Volume II. Distributions of Peaks and Correlated Variables. Part I. Graphical Presentation.
Report Number: AFFDL TR 68-131 Volume 2 Part 1
Author(s): Trent, D. J. Bouton, Innes
Corporate Author: Rockwell International Downey CA Space Businesses
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1969
Pages: 194
Contract: AF 33(615)-3448
Project: 1367
Task: 136717
AD Number: AD0851254
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Application of Multiparameter Flight Loads Data to Structural Design Criteria. Volume II. Distributions of Peaks and Correlated Variables. Part II. Tabulated Results.
Report Number: AFFDL TR 68-131 Volume 2 Part 2
Author(s): Bouton, Innes; Trent, D. J.
Corporate Author: Rockwell International Downey Ca Space Businesses
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1969
Pages: 840
Contract: AF 33(615)-3448
Project: 1367
Task: 136717
AD Number: AD0853495
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Application of Multiparameter Flight Loads Data to Structural Design Criteria. Volume III: Time Distributions and Peak Envelopes.
Report Number: AFFDL TR 68-131 Volume 3
Author(s): Trent, D. J.; Bouton, Innes
Corporate Author: Rockwell International Downey CA Space Businesses
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1969
Pages: 142
Contract: AF 33(615)-3448
Project: 1367
Task: 136717
AD Number: AD0851966
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Development of a Solid-State Display System
Report Number: AFFDL TR 68-133
Author(s): Archie L. Fisher; Paul R. Decker
Corporate Author: ITT Federal Laboratories
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1970
Pages: 60
Contract: F33615-67-C-1541
Project: 6190
Task: 619009
AD Number: AD0868080
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Pressure Distribution During Parachute Opening. Phase II. Finite Mass Operating Case.
Report Number: AFFDL TR 68-135
Author(s): Melzig, H. D. Saliaris, C.
Corporate Author: Deutsche Forschungsanstalt Fuer Luft- Und Raumfahrt E V Brunswick (Germany F R) Inst Fuer Flugmechanik
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 2/1/1969
Pages: 94
Contract: AF 61(052)-922
Project: 6065
Task: 606503
AD Number: AD0850942
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On The Influence Of Initial Geometric Imperfections On The Buckling And Postbuckling Behavior Of Fiber-Reinforced Cylindrical Shells Under Uniform Axial Compression.
Report Number: AFFDL TR 68-136
Author(s): Khot, N. S.
Corporate Author: Air Force Flight Dynamics Lab Wright-Patterson AFB OH
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 10/1/1968
Pages: 68
Contract: Laboratory Research - No Contract
Project: 1473
Task: 147306
AD Number: AD0680014
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Proceedings of the Conference on Matrix Methods in Structural Mechanics (2nd) Held At Wright Patterson Air Force Base, Ohio, On 15-17 October 1968
Report Number: AFFDL TR 68-150
Author(s):
Corporate Author: Air Force Flight Dynamics Lab Wright-Patterson AFB Ohio
Publication Date: 12/1/1969
Pages: 1462
Project: 0
Task: 0
AD Number: AD0703685
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Abstract Text:
The purpose of the conference was to discuss the recent developments in matrix structural analysis and design of structural systems. Forty papers were presented in seven sessions entitled: Structural weight Optimization; Dynamics; General Elements; Curved Elements; Applications; General Methods; and Nonlinear Analysis.
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Table of Contents
Report Number: AFFDL TR 68-150 p. i-ix
Author(s):
Corporate Author:
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 9
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Addresses
Report Number: AFFDL TR 68-150 p. 1-13
Author(s):
Corporate Author:
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 13
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Matrix Methods of Aerospace Structural Analysis
Report Number: AFFDL TR 68-150 p. 15-79
Author(s): Dehke, Paul H.
Corporate Author: Douglas Aircraft Company, MCDonnell Douglas Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 65
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Application of the Created Response Surface Technique to Structural Optimization
Report Number: AFFDL TR 68-150 p. 83-110
Author(s): Marcal, Pedro V., Gellatly, Ronald A.
Corporate Author: Boeing Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 28
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Optimization of Structures Based on the Study of Energy Distribution
Report Number: AFFDL TR 68-150 p. 111-153
Author(s): Venkayya, V. B., Khot, N. S., Reddy, V. S.
Corporate Author: Air Force Flight Dynamics Laboratory
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 43
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Fully-Stressed Design of Airplane Redundant Structures
Report Number: AFFDL TR 68-150 p. 155-181
Author(s): Dwyer, W., Rosenbaum, J. Shulman, M., Pardo, H.
Corporate Author: Grumman Aircraft Engineering Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 27
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Dynamic Analysis of Shells Using Double-Curved Finite Elements
Report Number: AFFDL TR 68-150 p. 185-212
Author(s): Greene, B. E, Jones, R. E., McLay, R. W., Strome, D. R.
Corporate Author: University of California
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 28
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Static and Dynamic Finite Element Analysis of Sandwich Structures
Report Number: AFFDL TR 68-150 p. 213-245
Author(s): Abel, J. F., Popov, E. P.
Corporate Author: University of California, Berkeley
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 33
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Vibration Analysis of Cantilevered Curved Plates Using a New Cylindrical Shell Finite Element
Report Number: AFFDL TR 68-150 p. 247-269
Author(s): Olson, Mervyn D., Lindberg, Garry M.
Corporate Author: National Aeronautical Establishment
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 23
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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A Minimization Method for the Solution of the Eigenproblem Arising in Structural Dynamics
Report Number: AFFDL TR 68-150 p. 271-306
Author(s): Fox, R. L., Kapoor, M. P.
Corporate Author: Case Western Reserve University; Indian Institute of Technology
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 36
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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A Practical Computational Method for Reducing a Dynamical System with Constraints to an Equivalent System with Independent Coordinates
Report Number: AFFDL TR 68-150 p. 307-330
Author(s): Walton Jr., William C., Steeves, Earl C.
Corporate Author: NASA Langley Research Center
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 24
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Some New Elements for the Matrix Displacement Method
Report Number: AFFDL TR 68-150 p. 333-397
Author(s): Argyris, J. H., Buck, K. E., Scharpf, D. W., Hilber, H. M., Mareczek, G.
Corporate Author: University of Wales
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 61
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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A Refined Quadrilateral Element for Analysis of Plate Bending
Report Number: AFFDL TR 68-150 p. 399-440
Author(s): Clough, Ray W., Felippa, Carlos A.
Corporate Author: University of California, Berkeley; Boeing Aircraft Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 42
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Rationalization in Deriving Element Stiffness Matrix by Assumed Stress Approach
Report Number: AFFDL TR 68-150 p. 441-469
Author(s): Pian, Theodore H. H., Tong, Pin
Corporate Author: Massachusetts Institute of Technology
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 29
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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A Finite Element Application of the Hellinger-Reissner Variational Theorem
Report Number: AFFDL TR 68-150 p. 471-487
Author(s): Dunham, Robert S., Pister, Karl S.
Corporate Author: University of California, Berkeley
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 17
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Finite Elements in Linear Viscoelasticity
Report Number: AFFDL TR 68-150 p. 489-516
Author(s): White, J. L.
Corporate Author: Boeing Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 28
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
Photo Enhancement: Not Needed
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Finite Element Analysis of Fluid Flows
Report Number: AFFDL TR 68-150 p. 517-535
Author(s): Martin, Harold C.
Corporate Author: Univeristy of Washnigton
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 19
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Curved Thick Shell and Membrane Elements with Particular Reference to Axisymmetric Problems
Report Number: AFFDL TR 68-150 p. 539-572
Author(s): Ahmad, Sohrabuddin, Irons, Bruce M.
Corporate Author: Technological University
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 34
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
Photo Enhancement: Not Needed
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Finite Element Analysis of Sandwich Plates and Cylindrical Shells with Laminated Faces
Report Number: AFFDL TR 68-150 p. 573-616
Author(s): Monforton, G. R., Schmit, Jr., L. A.
Corporate Author: Case Western Reserve University
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 44
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Curved Triangular Elements for the Analysis of Shells
Report Number: AFFDL TR 68-150 p. 617-639
Author(s): Bonnes, G., Dhatt, G., Giroux, Y. M., Robichaud, L. P. A.
Corporate Author: Laval University
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 23
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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A Doubly Curved Triangular Shell Element
Report Number: AFFDL TR 68-150 p. 641-666
Author(s): Strickland Jr., Gordon E., Loden, William A.
Corporate Author: Lockheed Missiles and Space Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 26
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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The Analysis of Thin Shells with Transverse Shear Strains by the Finite Element Method
Report Number: AFFDL TR 68-150 p. 667-710
Author(s): Key, Samuel W., Beisinger, Zelma E.
Corporate Author: Sandia Laboratories
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 44
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Elastic Instability Predictions for Doubly-Curved Shells
Report Number: AFFDL TR 68-150 p. 711-739
Author(s): Gallagher, Richard H., Yang, Henry T. Y.
Corporate Author: Cornell University
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 29
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Analysis of the 747 Aircraft Wing-Body Intersection
Report Number: AFFDL TR 68-150 p. 743-788
Author(s): Hansen, S. D., Anderton, G. L., Connacher, N. E., Dougherty, C. S.
Corporate Author: Grumman Aircraft Engineering Corp.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 45
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Structural Analysis Practices for Large Scale Systems
Report Number: AFFDL TR 68-150 p. 789-838
Author(s): Mallett, Robet H., Braun, Frederick W., Hunter, Donald T.
Corporate Author: Bell Aerosystems; NASA Manned Spacecraft Center
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 50
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Applications Experience with the Format Computer Program
Report Number: AFFDL TR 68-150 p. 839-867
Author(s): Warren, Dale S.
Corporate Author: McDonnell Douglas Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 29
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Some Applications of Finite Analysis to Shell Buckling Prediction
Report Number: AFFDL TR 68-150 p. 869-893
Author(s): Backus, Walter E., Mello, Raymond M.
Corporate Author: Boeing Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 25
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Structural Survivability Analysis
Report Number: AFFDL TR 68-150 p. 895-928
Author(s): Melosh, R. J., Johnson, J. R., Luik, Rein
Corporate Author: Philco-Ford; Air Force Flight Dynamics Laboratory
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 34
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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The Role of Computer Graphics in the Structural Design Process
Report Number: AFFDL TR 68-150 p. 929-964
Author(s): Batdorf, W. J., Kapur, S. S., Sayer, R. B.Kawai, T., Ohtsubo, H.
Corporate Author: Lockheed-Georgia Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 36
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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A Method for the Complicated Buckling Problems of Elastic Plates with Combined Use of Rayleigh-Ritz's Procedure in the Finite Element Method
Report Number: AFFDL TR 68-150 p. 967-994
Author(s): Kawai, T., Ohtsubo, H.
Corporate Author: Royal Aircraft Establishment
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 28
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Accuracy and Convergence of Finite Element Approximations
Report Number: AFFDL TR 68-150 p. 995-1027
Author(s): Walz, Joseph E., Fulton, Robert E., Cyrus, Nancy Jane
Corporate Author: NASA Langley Research Center
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 33
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
Photo Enhancement: Not Needed
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Numerical Conditioning of Stiffness Matrix Formulations for Frame Structures
Report Number: AFFDL TR 68-150 p. 1029-1060
Author(s): Rosanoff, R. A., Gloudeman, J. F., Levy, S.
Corporate Author: North American Rockwell Corp.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 32
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Completeness and Convergence in the Finite Element Method
Report Number: AFFDL TR 68-150 p. 1061-1089
Author(s): De Arantes e Oliveira, Eduardo Romano
Corporate Author: Laboratorio Nacional De Engenharia Civil
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 29
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
Photo Enhancement: Not Needed
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Analysis of General Coupled Thermoelasticity Problems by the Finite Element Method
Report Number: AFFDL TR 68-150 p. 1091-1120
Author(s): Oden, J. T., Kross, D. A.
Corporate Author: Research Institute, University of Alabama, Huntsville
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 30
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
Photo Enhancement: Not Needed
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The Heat Conduction and Thermal Stress Analysis by the Finite Element Method
Report Number: AFFDL TR 68-150 p. 1121-1163
Author(s): Fujino, T., Ohsaka, K.
Corporate Author: Mitsubishi Heavy Industries, Ltd.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 43
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
Photo Enhancement: Not Needed
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Hydroelastic of Axisymmetric Systems by a Finite Element Method
Report Number: AFFDL TR 68-150 p. 1165-1203
Author(s): Guyan, R. J., Ujihara, B. H., Welch, P. W.
Corporate Author: North American Rockwell Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 39
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
Photo Enhancement: Not Needed
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An Approximate Analysis of Thin Plates
Report Number: AFFDL TR 68-150 p. 1207-1230
Author(s): Murray, D. W., Wilson, E. L.
Corporate Author: NASA Langley Research Center
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 24
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
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Linear and Nonlinear Analysis of Shells of Revolution with Asymmetrical Stiffness Properties
Report Number: AFFDL TR 68-150 p. 1231-1251
Author(s): Stricklin, James A., DeAndrade, Jose C., Stebbins, Frederick J., Cwiertny, Jr., Anthony J.
Corporate Author: Texas A&M University; NASA Manned Spacecraft Center
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 21
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
Photo Enhancement: Not Needed
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Analysis of Tension Structures
Report Number: AFFDL TR 68-150 p. 1253-1270
Author(s): Bogner, F. K.,
Corporate Author: Bell Telephone Laboratories, Incorporated
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 18
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
Photo Enhancement: Not Needed
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Analysis of the Elastic-Plastic Problems by the Matrix Displacement Method
Report Number: AFFDL TR 68-150 p. 1271-1299
Author(s): Yamada, Y., Kawai, T., Yoshimura, N., Sakuri, T.
Corporate Author: University of Tokyo; Mitsubishi Atomic Pwer Industries, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 29
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
Photo Enhancement: Not Needed
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A Finite Element Method for the Plastic Bending Analysis of Structures
Report Number: AFFDL TR 68-150 p. 1301-1339
Author(s): Armen Jr., A., Pifko, A., Levine, H. S.
Corporate Author: Grumman Aircraft Engineering Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 39
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
Photo Enhancement: Not Needed
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Progress Report on Discrete-Element Elastic and Elastic-Plastic Analyses of Shells of Revolution Subjected to Axisymmetric and Asymmetric Loading
Report Number: AFFDL TR 68-150 p. 1341-1453
Author(s): Wimer, Emmett A., Kotanchik, James J.
Corporate Author: Massachusetts Institute of Technology
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1969
Pages: 13
Contract: None Given
Project: None Given
Task: None Given
AD Number: See AD0703685
Photo Enhancement: Not Needed
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V/STOL Flight Test Instrumentation Requirements for Extraction of Aerodynamic Coefficients
Report Number: AFFDL TR 68-154 Volume 1
Author(s): R. W. Hill; I. L. Clinkenbeard; N. F. Bolling
Corporate Author: LTV Aerospace Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1968
Pages: 310
Features: + Diagram(s) + Drawing(s) + Foldout(s) + Graph(s) + Photo(s) + Table(s)
Contract: F33615-68-C-1222
Project: 3170
Task: 317004
AD Number: AD0850956
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Abstract Text:
The results of a synthesis of pertinent maneuvers with a mathematical model of the XC-142 V/STOL airplane have served to establish tolerances in the measurement of flight parameters which provide the time histories used in the derivation of aerodynamic coefficients. Extracting valid aerodynamic coefficients from flight test time histories requires highly accurate instruments or detailed a priori knowledge of instrumentation errors. Furthermore, the mathematical technique used should provide the capability of extracting many coefficients simultaneously and delineating the probable error of each coefficient. The method of multiple linear regression, a least squares algorithm, provides the requisite mathematical tool with adequate statistical credentials. A state-of-the-art survey and a vendor-product-line review have provided guidelines for a system that will meet the overall accuracy requirements established. Details of equipment installations, oriented toward minimizing environmental stresses (particularly vibrations), have been studied. Conclusions drawn from this program are that the assembly and application of a precision data acquisition system based on digital 'onboard' handling techniques, with the appropriate sensing instrumentation, is entirely feasible but that limited development of measurement techniques, hardware, and software are required.
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Investigation of an Integrated Aircrew Escape/Rescue System Capability (AERCAB).
Report Number: AFFDL TR 68-159
Author(s): Manzuk, Robert J.; Peck, Walter R.; Yost, Charles A.; Duncan, James W.; Braunlich, E. A.
Corporate Author: Stencel Aero Engineering Corp Arden NC
Corp. Rep. Number: SAEC No. FTR-419-1
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 1/1/1969
Pages: 378
Features: + Diagram(s) + Drawing(s) + Foldout(s) + Graph(s) + Table(s)
Contract: F33615-68-C-1461
Project: 6065
Task: 606509
AD Number: AD0860590
Photo Enhancement: Complete
Abstract Text:
A concept was investigated whereby aircrewmembers are given a capability to aid in their own rescue subsequent to emergency ejection from their mission vehicle. The self-rescue capability was achieved by way of integrating a parawing into the ejection-seat escape system to provide an aerodynamic-lift generating surface, and also a twin-turbofan jet engine to provide propulsion for gaining altitude and departing from the emergency site toward a safe area for liason with allied forces. The escape/rescue system analyses concluded that in the conventional ejection/recovery mode of operation the AERCAB provides a survival capability surpassing that of currently in-service systems. In the self-rescue mode, AERCAB is capable of flight at 10,000 feet (MSL) over a distance of fifty nautical miles at airspeeds approaching 100 knots. The system is manually controllable in both powered and unpowered flight, and it appears feasible to incorporate an automatic homing flight control system. AERCAB is shown capable of adverse weather operation in powered flight provided suitable protective clothing is worn by the occupant. Under all emergency circumstances, the aircrewman using AERCAB retains the capability to descend to terrain level with his personnel parachute. A detailed preliminary design study was accomplished, and it is shown that the system is retrofittable in the existing crewstations of the A-7 and F-4 aircraft with only minor modifications thereto. The investigative program resulted in the generation of specific operational and design criteria for an integrated aircrew escape/rescue system capability; operational and performance limits thereof were defined; and it was analytically shown that the AERCAB concept is feasible, and merits continued study, experimental testing, and development. A full-scale system mockup was prepared during the program, and delivered to the Air Force Flight Dynamics Laboratory integrated in a simulation of the A-7 crewstation.
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Investigation Of The High Pressure Electrodeless Arc In Air
Report Number: AFFDL TR 68-160
Author(s): Hollister, Donald D.
Corporate Author: Philco-Ford Corp Newport Beach Calif Aeronutronic Div
Laboratory: AF Flight Dynamics Laboratory
Publication Date: 2/1/1969
Pages: 244
Contract: F33615-68-C-1137
Project: None Given
Task: None Given
AD Number: AD0685779
Photo Enhancement: Not Needed
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Correlation of Aerodynamic Stability and Control Derivatives Obtained from Flight Tests and Wind Tunnel Tests on the XC-142A Airplane.
Report Number: AFFDL TR 68-167
Author(s): Black, Ernest L. Booth, George C.
Corporate Author: Ltv Aerospace Corp Dallas Tex Ltv Vought Aeronautics Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 4/1/1969
Pages: 198
Features: + Foldout(s) + Graph(s) + Photo(s) + Table(s)
Contract: AF 33(615)-2897
Project: 8219
Task: 821907
AD Number: AD0854018
Photo Enhancement: Complete
Abstract Text:
A wind tunnel-flight data correlation program using the XC-142A airplane was undertaken to assess the degree of correlation attainable and to establish the sreas where present wind tunnel testing and correction techniques appear to be inadequate. Wind tunnel data obtained from tests of three models of the XC-142A airplane in four different size test sections could not be satisfactorily correlated because of differences in model configuration and test conditions. Three special tests were performed using the same model but in different size test sections of the same tunnel. The results of these tests indicated that with proper equipment and techniques, valid V/STOL wind tunnel data can be acquired. The flight data were obtained from the Contractor's Category I test program. The objective of this flight test program was primarily to perform a qualitative evaluation of the airplane rather than to obtain the quantitative data desired for aerodynamic analysis purposes. The flight data were not acquired in a manner that would provide suitable quality to allow a high degree of confidence in inverse solutions for aerodynamic derivatives. It is recommended that future programs include a critical review of the instrumentation system and flight maneuvers in order to obtain the best possible data for determining the low speed flight aerodynamic characteristics.
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Parametric Study Of Tsai's Strength Criteria For Filamentary Composites.
Report Number: AFFDL TR 68-168
Author(s): Sandhu, R. S.
Corporate Author: Air Force Flight Dynamics Lab Wright-Patterson AFB Ohio
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 5/1/1969
Pages: 34
Contract: Laboratory Research - No Contract
Project: 1473
Task: 147306
AD Number: AD0691028
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