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High Altitude Critical Atmospheric Turbulence Data System
Report Number: AFFDL TR 67-1
Author(s): Boone, Joseph P.
Corporate Author: Air Force Flight Dynamics Laboratory
Laboratory: AF Flight Dynamics Laboratory
Publication Date: 5/1/1967
Pages: 32
Contract: AF 33(657)-11143
Project: 1469
Task: None Given
AD Number: AD0816976
Photo Enhancement: Complete
Abstract Text:
The purpose of this report is to provide a synopsis of the data system designed to measure, record, and process High Altitude Critical Atmospheric Turbulence (HICAT) data. The HICAT Project is to measure gust velocity components in the altitude range of 40 to 70 thousand feet in several world areas. The goal is a statistical definition of the 'roughness' of the atmosphere which can be applied to design requirements for advanced aircraft structures. A Pulse Code Modulation airborne system is described. Highly accurate sensors and components, including an inertial platform, are used aboard a WU-2 test aircraft in an attempt to resolve fine scale forces, accelerations and aircraft motions in the atmospheric gust field. The magnetic tapes and other pertinent information are sent to a data processing ground station for generation of a computer-compatible tape, processing, and detailed analysis. Power spectral functions of the gust components are of major interest. Output data are correlated with meteorological and geographical data associated with the test site.
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Self-Regulated Oxygen Concentrator
Report Number: AFFDL TR 67-6
Author(s): G. L. Mrava; R. A. Wynveen
Corporate Author: TRW Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1967
Pages: 185
Features: + Foldout(s)
Contract: AF 33(615)-3392
Project: 6146
Task: 614614
AD Number: AD0808789
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Abstract Text:
A program to design, fabricate and test a model of an oxygen concentrator employing a method of control termed self regulation was successfully conducted. The stack assembly consists of three cells, where the oxygen is electrochemically separated from the air, sandwiched between two humidifier chambers. The self-regulation of the unit results from the thermal equilibrium that exists between the heat generated in the electrochemical cells during the O2 concentrating process and the evaporative cooling in the humidifiers due to the air humidification process. This mode of operation eliminates external humidifiers and associated thermal controls previously used on apparatus of this type. As a laboratory model, the three-cell unit demonstrated oxygen delivery rates up to 0.045 lb/hr while displaying oxygen purities at a level of 100%. Wide-range parametric testing conducted on the unit covered cell operating temperatures of 100-175F, air inlet pressures from 5-90 psia, air flow rates from 2-5 times theoretical, and current densities up to 166 amps/sq ft. The testing program was culminated with 200 hours of testing which successfully demonstrated the self-regulating characteristics of the unit. As a final conclusion, the data and analyses are used to specify an advanced 0.2-lb/hr oxygen concentrator utilizing self-regulation in addition to size optimization. With additional development the design will be capable of being incorporated into an aviator's oxygen supply system.
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Basis Of A Well Conditioned Force Program For Equilibrium Models Via The Southwell Slab Analogies
Report Number: AFFDL TR 67-10
Author(s): De Veubeke, Baudouin M. Fraeijs
Corporate Author: Liege Univ (Belgium) Laboratoire D'aeronautique
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1967
Pages: 28
Contract: AF 61(052)-892
Project: 1467
Task: 146705
AD Number: AD0652239
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Abstract Text:
Equilibrium models of finite elements have by definition the property of satisfying detailed equilibrium within the structure. Their usefullness lies in their ability to predict upper bounds to influence coefficients. The larger number of nodal displacements but the smaller number of selfstressing states, by comparison with displacement models, suggests the development of a force type program in preference to a stiffness program. The report shows how the Southwell slab analogies between displacement fields in conforming displacement models and stress functions in equilibrium models provide an efficient method for selecting force redundancies and particular equilibrium solutions. The method automatically reduces to a minimum the coupling between the unknowns.
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Atmospheric Turbulence Spectra From B-52 Flight Loads Data
Report Number: AFFDL TR 67-13
Author(s): Coy, Richard G.
Corporate Author: Dayton Univ OH Research Inst
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 4/1/1967
Pages: 62
Contract: AF 33(615)-5033
Project: 1367
Task: 136717
AD Number: AD0815684
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Near Field Noise Analyses of Aircraft Propulsion Systems with Emphasis on Prediction Techniques for Jets
Report Number: AFFDL TR 67-43
Author(s): H. E. Plumblee; J. R. Ballentine; B. Passinos
Corporate Author: Lockheed-Georgia Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1967
Pages: 230
Contract: AF 33(615)-2503
Project: 1471
Task: 147102
AD Number: AD0822414
Abstract Text:
Semi-empirical methods are presented for calculating sound pressure level in a jet near noise field, including temperature and Mach number effects. A digital computer program for calculating constant SPL contours for the overall and octave band frequencies is incorporated. Machine plotted contours from model jet tests for a basic jet, VTOL jet, deflected jet, and jet with ejector are featured. Results of tip-turbine fan tests are given. Cruise fan, VTOL shrouded fan, and wing mounted configurations were tested.
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The Method Of Characteristics For Three-Dimensional Real-Gas Flows Including The Digital Computer Program Details And Operating Procedures For Frozen Flows.
Report Number: AFFDL TR 67-47
Author(s): Strom, Charles R.
Corporate Author: Cornell Aeronautical Lab Inc Buffalo N Y
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 7/1/1967
Pages: 252
Contract: AF 33(657)-10423
Project: 1366
Task: 136615
AD Number: AD0661342
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Design, Fabrication, and Ground Testing of the F-4 Beryllium Rudder
Report Number: AFFDL TR 67-68
Author(s): Finn, J. M.; Koch, L. C.; Muehlberger, D. E
Corporate Author: McDonnell Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 4/1/1967
Pages: 285
Features: + Foldout(s)
Contract: AF 33(615)-2974
Project: 1368
Task: 136808
AD Number: AD0816139
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Abstract Text:
The beryllium rudder of McDonnell F-4 aircraft was designed, analyzed,fabricated, and successfully ground tested to the same loading conditions and criteria that apply to the production of aluminum rudder. An extensive element test program was conducted to obtain material properties and design data not previously available, and formulate design criteria for beryllium structures. The beryllium rudder weighs 37.59 lbs. as compared to 63.03 lbs. for the production aluminum rudder. The honeycomb trailing edge assembly for the beryllium rudder was bonded with FM-61 adhesive, phenolic/epoxy film.
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Application of Statistical Energy Analysis to Vibrations of Multi-Panel Structures
Report Number: AFFDL TR 67-79
Author(s): ungar, Eric E.; Koronaiois, Nicholas; Manning, Jerome E.
Corporate Author: Bolt Beranek and Newman, Inc.
Publication Date: 8/1/1967
Pages: 112
Project: 0
Task: 0
AD Number: AD0822086
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Abstract Text:
Experimentally determined vibratory mean square velocity distributions on a multi-panel planar structure and on a ring-and-stringer reinforced cylindrical shell are compared with predictions obtained from statistical energy analysis. Generally good agreement is observed. The flow of mechanical power between two panels that are separated by a reinforcing beam is studied, in order to uncover the important parameters and to provide information on the coefficients of proportionality between power flow and average modal energy difference, which one must know in order to apply statistical energy analysis. No analytical prediction methods are developed for these coefficients, but an empirical measurement technique is presented and is shown to yield consistent results. Analyses pertaining to dynamic response concentrations in plate and shell structures are summarized, and investigations of response characteristics and response statistics which warrant further pursuit are delineated.
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Pressure distribution Measurements on Several Rigid Hyperflo Models at Mach 3.0 and 4.0
Report Number: AFFDL TR 67-84
Author(s): Noreen, R. A.; Hosker Jr., R. P.
Corporate Author: University of Minnesota
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 9/1/1967
Pages: 112
Contract: AF 33(615)-5029
Project: 6065
Task: 606503
AD Number: AD0822549
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Considerations in the Design of Supports for Panels in Fatigue Tests
Report Number: AFFDL TR 67-86
Author(s): Ungar, Eric E.; Lee, Kyung S.
Corporate Author: Bolt Beranek and Newman, Inc.
Publication Date: 9/1/1967
Pages: 140
Project: 0
Task: 0
AD Number: AD0822899
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Effects of Gust Velocity Spatial Distributions on Lateral-Directional Response of a VTOL Aircraft
Report Number: AFFDL TR 67-93
Author(s): Robert L. Swaim; Alonzo J. Connors
Corporate Author: Air Force Flight Dynamics Laboratory
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 6/1/1967
Pages: 38
Contract: Laboratory Research - No Contract
Project: 8219
Task: 821903
AD Number: AD0657321
Photo Enhancement: Complete
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Analysis and Experiment of Radiant Heat Exchange Between Simply Arranged Surfaces
Report Number: AFFDL TR 67-94
Author(s): Viskanta, R.; Schornhorst, J. R.; Roor, J. S.
Corporate Author: School of Mechanical Engineering, Purdue University
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 7/1/1967
Pages: 130
Contract: AF 33(615)-23621
Project: 6146
Task: 614616
AD Number: AD0655335
Photo Enhancement: Complete
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Identification of Selected Experimental Data on Thermal Stresses
Report Number: AFFDL TR 67-100
Author(s): Gatewood, B. E.; O'Connor, James S.
Corporate Author: Ohio State University
Publication Date: 9/1/1967
Pages: 158
Project: 0
Task: 0
AD Number: AD0820909
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Demonstration of a Supersonic Box Method for Unsteady Aerodynamics of Nonplanar Wings. Part I. General Applications.
Report Number: AFFDL TR 67-104 Part 1
Author(s): Olsen, James J.
Corporate Author: Air Force Flight Dynamics Lab Wright-Patterson AFB OH
Publication Date: 2/1/1969
Pages: 78
Project: 0
Task: 0
AD Number: AD0850647
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Abstract Text:
The report presents and interprets the calculations of the unsteady aerodynamic prediction method known as the 'Nonplanar Mach Box' method. It contains examples of data input and output for the associated computer program and explains the program's interpretation of the user's modal data. Also included are summaries of convergence properties, comparison with exact linearized theory, and a brief outline of the calculations for the Advisory Group for Aeronautical Research and Development (AGARD) planforms.
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Demonstration of a Supersonic Box Method for Unsteady Aerodynamics of Nonplanar Wings. Part II. Application to the AGARD Planforms.
Report Number: AFFDL TR 67-104 Part 2
Author(s): Olsen,James J.
Corporate Author: Air Force Flight Dynamics Lab Wright-Patterson AFB OH
Publication Date: 2/1/1969
Pages: 62
Project: 0
Task: 0
AD Number: AD0850922
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Abstract Text:
A tabulation is given of the 'Nonplanar Mach Box' results for unsteady generalized force coefficients for the planforms, Mach numbers, mode shapes, and frequencies recommended by AGARD. The tabulation uses the AGARD coordinate system and format. Not all the desired cases could be included because of the program's current limitation to supersonic trailing edges (leading edges can be supersonic or subsonic). The method was found to be fully workable and constitutes a valuable research and design tool. Convergence and accuracy were found to be comparable to steady-state, planar methods. The computer program is available with sample problems.
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Quantitative Structural Design Criteria. Volume I. A Critique of Present and Proposed Approaches to Structural Design Criteria
Report Number: AFFDL TR 67-107 Volume 1
Author(s): Innes Bouton; D. J. Trent
Corporate Author: North American Rockwell Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 6/1/1968
Pages: 158
Contract: AF 33(615)-3755
Project: 1367
Task: 136714
AD Number: AD0839441
Abstract Text:
Exploratory research, needed to develop quantitative structural design criteria for aerospace vehicles, has been conducted to relate the probabilistic nature of design, operational, and environmental experiences to the structural performance of aerospace vehicles. This design criteria is predicated on the concept of structural reliability. Volume I presents a critique of present and proposed approaches to structural design criteria. Volume II presents recommendations for a deterministic structural design criteria procedure based on statistical methods. This is a new procedure intended to overcome the problems associated with other structural design criteria procedures. The new procedure is demonstrated on the F-100 airplane by comparing the output of the computer program with actual service records. Volume III formulates two computer programs for the procedure and presents user's instructions for the programs.
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Quantitative Structural Design Criteria. Volume II. The Philosophy and Implementation of the New Procedure
Report Number: AFFDL TR 67-107 Volume 2
Author(s): Innes Bouton; Mel Fisk; D. J. Trent
Corporate Author: North American Rockwell Corporation
Corp. Rep. Number: SID 67-495-2
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 6/1/1968
Pages: 252
Contract: AF 33(615)-3755
Project: 1367
Task: 136714
AD Number: AD0839884
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Development of the Shim Joint Concept for Composite Structural Members
Report Number: AFFDL TR 67-116
Author(s): Cole, B. W.; Wong, J. P.; Courtney, A. L.
Corporate Author: Bedix Corporation
Laboratory: AF Flight Dynamics Laboartory
Publication Date: 8/1/1967
Pages: 125
Contract: F33(615)-67-C-1263
Project: 6M26499
Task: None Given
AD Number: AD0821137
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Development And Experimental Evaluation Of A Retrieval System For Air Force Control-Display Information.
Report Number: AFFDL TR 67-119
Author(s): Debons, Anthony; Scheffler, Frederic L.; Snide, John D.
Corporate Author: Dayton Univ Ohio Research Inst
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 11/1/1967
Pages: 178
Contract: AF 33(615)-5310
Project: 6190
Task: 61907
AD Number: AD0663756
Photo Enhancement: Not Needed
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Assessment Of The Factors Affecting Advanced Lifting Entry Vehicles
Report Number: AFFDL TR 67-137
Author(s): Draper, Alfred C.; Buck, Melvin L.
Corporate Author: Air Force Flight Dynamics Lab Wright-Patterson AFB OH
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 1/1/1968
Pages: 35
Contract: Laboratory Research - No Contract
Project: 1366
Task: None Given
AD Number: AD0829193
Photo Enhancement: Not Needed
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Design Criteris for the Predition and Prevention of Panel Flutter. Volume I: Criteria Presentation
Report Number: AFFDL TR 67-140
Author(s): Clark E. Lemley
Corporate Author: McDonnell Douglas Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1968
Pages: 60
Contract: AF 33(615)-5295
Project: 1370
Task: 137003
AD Number: AD0840581
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Abstract Text:
The program described in this report was performed to bring together all available data from wind tunnel test, flight test, vibration test, thermal test and theoretical investigations to form comprehensive panel flutter design criteria. Procedures were developed which are applicable to the environment and various panel structural arrangements for transonic, supersonic, and hypersonic aircraft; aerospace re-entry vehicles, and boosters. This report (Volume I) presents a set of criteria for the design of flutter-free panels. The design procedure provides for initially establishing the required thickness at neutral stability of a flat, unstressed, unswept panel. Thickness corrections are then made to account for various parameters that are known to affect panel flutter boundaries.
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Experimental Flight Instruments
Report Number: AFFDL TR 67-143
Author(s): Schouten, Tunis H.
Corporate Author: Lear Siegler Inc Grand Rapids Mi Instrument Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1967
Pages: 26
Contract: AF 33(615)-4271
Project: 6190
Task: 619008
AD Number: AD0825831
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Investigation of Turbulent Heat Transfer at Hypersonic Speeds. Volume I. Analytical Methods.
Report Number: AFFDL TR 67-144 Volume 01
Author(s): Savage, Richard T.; Jaeck, Carl L.
Corporate Author: Boeing Company Aerospace Group, Seattle, Washington
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1967
Pages: 136
Contract: AF 33(615)-2372
Project: 1366
Task: 136607
AD Number: AD0667798
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New Approaches to Human-Pilot/Vehicle Dynamic Analysis
Report Number: AFFDL TR 67-150
Author(s): D. T. McRuer; L. G. Hofmann; H. R. Jex; G. P. Moor; A. V. Phatak; D. H. Weir; J. Wolkovitch
Corporate Author: Systems Technology, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 2/1/1968
Pages: 208
Contract: AF 33(615)-3652
Project: 8219
Task: 821904
AD Number: AD667549
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Fixed-Base Flight Simulator Studies of VTOL Aircraft Handling Qualities in Hovering and Low-Speed Flight
Report Number: AFFDL TR 67-152
Author(s): David P. Miller; Edward W. Vinje
Corporate Author: United Aircraft Research Laboratories
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 1/1/1968
Pages: 199
Contract: AF 33(615)-3736
Project: 698DC
Task: None Given
AD Number: AD0831446
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Refinement of Sonic Fatigue Structural Design Criteria
Report Number: AFFDL TR 67-156
Author(s): John R. Ballentine; Fred F. Rudder; James T. Mathis; Harry E. Plumblee
Corporate Author: Lockheed-Georgia Company
Corp. Rep. Number: ER-9546
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 1/1/1968
Pages: 254
Contract: AF 33(615)-3816
Project: 1471
Task: 147101
AD Number: AD0831118
Abstract Text:
Accurate nomographs for designing conventional skin-stringer and honeycomb sandwich construction to meet sonic fatigue requirements are presented. The nomographs were derived from the results of sonic fatigue tests of 30 skin-stringer and 30 honeycomb sandwich designs, totaling 60 test specimens for each design. Emphasis is also placed on assessing the effect of structural curvature on sonic fatigue and structural response. Nomographs for determining the curvature effects are included.
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Wind Tunnel Studies Of The Pressure Distribution And The Flow Field In The Wake Of The Lockheed C-141A Starlifter Jet Transport Aircraft
Report Number: AFFDL TR 67-163
Author(s): Goodrick, T. F.
Corporate Author: Minnesota Univ Minneapolis Dept Of Aeronautics And Engineering Mechanics
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 5/1/1968
Pages: 54
Contract: F33615-67-C-1010
Project: 6065
Task: 606503
AD Number: AD0835380
Photo Enhancement: Complete
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Prediction Of Boundary Layer Pressure Fluctuations
Report Number: AFFDL TR 67-167
Author(s): Lowson, Martin V.
Corporate Author: Wyle Labs Inc Huntsville AL Testing Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 4/1/1968
Pages: 40
Contract: F33615-67-C-1287
Project: 1471
Task: 147102
AD Number: AD0832715
Photo Enhancement: Not Needed
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Parametric Performance Analysis Of Crew Escape Concepts In The Vtol And Conventional Take-Off And Landing Situations
Report Number: AFFDL TR 67-178
Author(s): Brown, Dean W.; Standish, David B.
Corporate Author: North American Rockwell Corp Los Angeles CA Los Angeles Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 1/1/1968
Pages: 375
Features: + Foldout(s)
Contract: AF 33(615)-5332
Project: 0
Task: 0
AD Number: AD0828080
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Analysis of VTOL Handling Qualities Requirements: Part I. Longitudinal Hover and Transition
Report Number: AFFDL TR 67-179 Part 1
Author(s): Samuel J. Craig; Annthony Campbell
Corporate Author: Systems Technology, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 10/1/1968
Pages: 198
Contract: AF 33(615)-3736
Project: 698DC
Task: None Given
AD Number: AD0845165
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Analysis of VTOL Handling Qualities Requirements: Part II. Lateral-Directional Hover and Transition
Report Number: AFFDL TR 67-179 Part 2
Author(s): Samuel J. Craig; Anthony Campbell
Corporate Author: Systems Technology, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 2/1/1970
Pages: 210
Contract: AF 33(615)-3736
Project: 698DC
Task: None Given
AD Number: AD0867306
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Analytical Design Methods for Aircraft Structural Joints
Report Number: AFFDL TR 67-184
Author(s): W. F. McCombs; J. C. McQueen; J. L. Perry
Corporate Author: LTV Aerospace Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 1/1/1968
Pages: 235
Contract: F33615-67-C-1339
Project: 1467
Task: 146704
AD Number: AD0831711
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Optimal Control Method For Predicting Control Characteristics And Display Requirements Of Manned-Vehicle Systems
Report Number: AFFDL TR 67-187
Author(s): Elkind, Jerome I.; Falb, Peter L.; Kleinman, David; Levison, William H.
Corporate Author: Bolt Beranek And Newman Inc Cambridge Mass
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 6/1/1968
Pages: 172
Contract: AF 33(615)-5160
Project: 8219
Task: 821910
AD Number: AD0672272
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Establishment Of An Unsymmetrical Wake Test Capability For Aerodynamic Decelerators. Volume III. Experimental Wake Survey And Body Surface Pressure Data
Report Number: AFFDL TR 67-192 Volume 3
Author(s): Henke, Daniel W.
Corporate Author: Goodyear Aerospace Corp Akron Ohio
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1968
Pages: 354
Contract: AF 33(615)-3595
Project: 6065
Task: 606507
AD Number: AD0675182
Photo Enhancement: Not Needed
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Iterative Method For The Analysis Of Large Structural Systems
Report Number: AFFDL TR 67-194
Author(s): Venkayya, V. B.
Corporate Author: Air Force Flight Dynamics Lab Wright-Patterson AFB Ohio
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 4/1/1968
Pages: 50
Contract: Laboratory Research - No Contract
Project: 1467
Task: 146705
AD Number: AD0670846
Photo Enhancement: Not Needed
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