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Flight Evaluation of Various Phugoid Dynamics and 1/Th1 Values for the Landing Approach Task
Report Number: AFFDL TR 66-2
Author(s): Charles Chalk
Corporate Author: Cornell Aeronutical Laboratory, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 2/1/1966
Pages: 160
Features: + Foldout(s)
Contract: AF 33(615)-1253
Project: 8219
Task: 821905
AD Number: AD0480187
Photo Enhancement: Complete
Abstract Text:
Longitudinal handling qualities in the landing approach are studied. The T-33 variable stability and variable drag airplane was used in a flight program to evaluate various short period dynamics, phugoid dynamics, drag characteristics and elevator control authority levels. The first phase of the flight program was directed mainly at longitudinal short period dynamics, drag variation with angle of attack and elevator control authority. The second phase of the flight program was directed at phugoid dynamics, short period frequency, elevator control authority and drag characteristics. Drag variations with angle of attack, airspeed and elevator deflection were considered. Pilot ratings and comments are related to the airplane characteristics tests.
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Re-Entry Vehicle Control System Design and Mechanization
Report Number: AFFDL TR 66-3
Author(s): D. K. Scharmack; M. D. Ward
Corporate Author: Honeywell, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 4/1/1966
Pages: 210
Contract: AF 33(615)-1858
Project: 8225
Task: 822501
AD Number: AD0485616
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Abstract Text:
A nonlinear optimal feedback control scheme for controlling a vehicle re-entering the earth's atmosphere from lunar return initial conditions is reported. The optimal feedback control law used in the scheme is obtained from a multi-dimensional surface fit of the control function for several optimal trajectories. Partials of the control with respect to the state vector are included in the fitting procedure. The functional minimized by the trajectories is the total (convective plus radiative) stagnation point heat. The feedback control scheme is developed, and several re-entry trajectories are simulated. Modest increasing total heat from optimal values are observed, and large (although tolerable) terminal point errors occur. It is believed that the terminal errors can be greatly reduced, if necessary. A powerful predictor scheme is developed which allows optimal a function of a parameter. This is used to extend the range of an optimal trajectory, to perform an absolute minimum test, and to map the optimal re-entry corridor. Sufficiency tests for a relative minimum are mechanized, and it is shown that the trajectories considered are minimizing paths.
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Preliminary Development of a Solid-State Matrix Display
Report Number: AFFDL TR 66-5
Author(s): B. J. Lechner, et al.
Corporate Author: Radio Corporation of America
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 1/1/1967
Pages: 150
Contract: AF 33(615)-1493
Project: 6190
Task: 619009
AD Number: AD0649553
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Abstract Text:
The use of ferroelectric transchargers as storage and control elements in an electroluminescent matrix display is reported. Research on display panel circuitry led to control circuits useful for solid-state matrix display. In these circuits, ferroelectric elements provide analog storage and control energization of electroluminescent cells in accordance with stored analog signals. The ferroelectric, in conjunction with a diode, provides a selection threshold which permits the element to be addressed in a matrix by voltage coincidence. The new circuits give greatly improved brightness and contrast compared with previous ferroelectric control circuits. Transcharger circuits with logic capability have also been developed; such circuits are especially useful for bar graph, moving pointer, and similar displays. Three experimental model displays demonstrated brightness as high as 48 ft-L; contrast ratio in excess of 100:1; geometric resolution as great as 10-elements per in.; capability for producing a gray scale; and a frame rate which allows continuity of motion without blurring or flicker. The performance of these models demonstrates the potential of using ferroelectric control circuits and electroluminescent elements for high-brightness, high-resolution, all solid-state matrix displays.
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Development of High Contrast Electroluminescent Techniques for Aircraft Displays
Report Number: AFFDL TR 66-6
Author(s): Carlton J. Peterson; Hugh A. Smith
Corporate Author: Bunker-Ramo Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 4/1/1966
Pages: 38
Contract: AF 33(657)-8600
Project: 6190
Task: 619009
AD Number: AD0637460
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Abstract Text:
This paper outlines the steps taken to develop a new display technology capable of meeting display requirements of future manned weapon systems. A description is made in the first part of this paper identifying the basic concept and resulting development of high-contrast electroluminescent (EL) displays both from an engineering and psychophysical standpoint. The problem of display legibility, quite often confused with display brightness, is also discussed with respect to its effect on the limitations of EL displays. Finally, information is presented identifying how this limitation was overcome and why such progress is considered to be an important contribution to the development of solid-state displays. The second part of this paper describes the human factors aspects of the high-contrast EL program. The inherent weakness of transilluminated displays, the variables related to readability, the effects of the anticipated upper limits of environmental lighting, and the study of one of the first high-contrast EL displays are discussed.
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Sonic Fatigue in Combined Environment
Report Number: AFFDL TR 66-7
Author(s): John R. Ballantine; Harry E. Plumblee; Cecil W. Schneider
Corporate Author: Lockheed-Georgia Company
Corp. Rep. Number: ER-8452
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 5/1/1966
Pages: 164
Contract: AF 33(615)-1481
Project: 1471
Task: 147101
AD Number: AD0637506
Abstract Text:
Research on sonic fatigue in combined environment is described. Emphasis is placed on determining the effects of structural curvature, low- frequency vibratory loads, and heat, both singly and collectively, on sonic fatigue. The analytical and experimental investigation is presented in two major phases: (1) An investigation of simple structural panels to determine the effect of curvature and heat cycling schemes on dynamic response and fatigue. (2) An investigation to determine the effects of high-intensity sound, heat, and low-frequency vibratory loads on curved titanium-faced honeycomb sandwich panels.
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Pressure Distribution During Parachute Opening. Phase 1. Infinite Mass Operating Case
Report Number: AFFDL TR 66-10
Author(s): Melzig, H. D.; Schmidt, P. K.
Corporate Author: Deutsche Forschungsanstalt Fuer Luft- Und Raumfahrt E V Brunswick (Germany Fr) Inst Fuer Flugmechanik
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1966
Pages: 138
Contract: AF 61(052)-681
Project: 6065
Task: 60653
AD Number: AD0482534
Photo Enhancement: Complete
Abstract Text:
An experimental investigation and correlative analysis were conducted to determine the pressure distribution over the surface of parachute canopies during the period of inflation for the infinite mass case and to correlate pressure coefficients with inflating canopy shapes. Parachute canopy models of Circular Flat, 10% Extended Skirt, Ringslot, and Ribbon designs were tested under infinite mass conditions in a 9 x 10 ft low speed wind tunnel. External and internal pressure values were measured at various locations over the surface of the model canopies throughout the period of inflation, and generalized canopy profile shapes were obtained by means of photographic analysis. Pressure coefficients derived for the steady state (fully open canopy) are quite comparable to the results of previous measurements. Peak pressure values during the unsteady period of inflation were found to be up to 5 times as great as steady state values. The relationships between the pressure distribution and time for each of the canopy models deployed at free-stream velocities between 70 and 160 ft/sec. are presented.
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Low Pressure Measurement Techniques
Report Number: AFFDL TR 66-11
Author(s): Herbert A. Painter
Corporate Author: Electro-Optical Systems, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 7/1/1966
Pages: 117
Contract: AF 33(615)-1838
Project: 1469
Task: 146907
AD Number: AD0802195
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Abstract Text:
This project was initiated to develop four prototype pressure transducers in the range of 0.0 to 0.1 psia for Wright-Patterson AFB. The design selected makes use of a convoluted diaphragm force collector to drive a cantilever beam. A semiconductor strain gage bridge bonded to the beam converts the force to an electrical signal which is amplified to provide a 0 to 5V dc output. The results presented demonstrate achievement of essentially all requirements, save high-temperature transient performance. It is apparent from the results of this project that an accurate 0.0 to 0.1 psia transducer of low weight and reasonably high natural frequency can be produced. Achievement of higher operating temperature and natural frequency is possible.
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Stiffness and Vibration Characteristics of Inflatable Delta Wing Models at Temperatures up to 650 Degrees F
Report Number: AFFDL TR 66-14
Author(s): Samuel J. Pollock
Corporate Author: Air Force Flight Dynamics Laboratory
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 6/1/1966
Pages: 108
Contract: AF 33(615)-1880
Project: 1370
Task: 137003
AD Number: AD0803266
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Abstract Text:
Stiffness and vibration data were obtained on inflatable Airmat models for various internal pressures from 2 to 10 psi and temperatures up to 650 F. The semi-span 65 deg delta wing models were woven from stainless steel monofilament wire and coated with high temperature silicone elastomer. Deflection and vibration characteristics were predicted using shear theory. Vibration predictions were also made using measured influence coefficients. Shear theory agreed with experimentation for deflections due to uniform load except near the leading edge where experimental deflections were smaller due to the stiffening effect of the rounded edges. Correlation of shear theory prediction for vibration frequencies with experiment improved as internal pressure increased to 10 psi. Vibration calculations using measured small deflection influence coefficients agreed with experimentation. Model vibration frequencies decreased as temperature was increased from 70 F to about 300 F. From 300 F to 650 F, vibration frequencies increased. At 650 F, the vibration frequency for a model without ceramic frits in the silicone elastomer coating was 32% higher than the room temperature frequency; for a model with ceramic frits the frequency was 10% lower. Mode shapes did not change appreciably with temperature. Structural damping coefficients decreased with increasing temperature.
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Mathematical Analysis of Heat Conduction in a Sector of a Hollow Circular Cylinder
Report Number: AFFDL TR 66-16
Author(s): None Given
Corporate Author: Martin Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 4/1/1966
Pages: 150
Features: + Foldout(s)
Contract: AF 33)615)-2385
Project: 1467
Task: None Given
AD Number: AD0485307
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Abstract Text:
The temperature distribution within a sector of a hollow circular cylinder with temperature dependent thermophysical properties was analyzed based on exact mathematical solution. The subject nonlinear differential equation was reduced to a linear differential equation by an integral transform and with the assumption that only the thermal conductivity is a function of temperature whereas the thermal diffusivity remains constant. The solution was programmed in FORTRAN 4 for application to an IBM 7094. In addition, a successive transform applicable to the solution of similar problems involving temperature dependent thermal diffusivity is illustrated and discussed.
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Fundamental Relationships for Ablation and Hyperthermal Heat Transfer
Report Number: AFFDL TR 66-25
Author(s): Robert T. Achard
Corporate Author: Air Force Flight Dynamics Laboratory
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 4/1/1966
Pages: 54
Contract: Laboratory Research - No Contract
Project: 1368
Task: 136804
AD Number: AD0633677
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Abstract Text:
A qualitative review of fundamental relationships involved in ablation engineering and aerodynamic heating is presented. This document is written for rapid reading with the primary purpose of introducing the technical area to engineers, scientists, and management personnel associated with but not intimately working in hypervelocity thermal protection.
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Analysis And Experimental Evaluation Of An Ultra-High Temperature Pyrolytic Graphite Thermocouple
Report Number: AFFDL TR 66-27
Author(s): Klein, C. A.; Lepie, M. P.; Donadio, R. N.
Corporate Author: Raytheon Co Waltham Ma Research Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 6/1/1966
Pages: 40
Contract: AF 33(615)-2650
Project: 1469
Task: 146907
AD Number: AD0802214
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Abstract Text:
This report is made up of three segments as follows: (1) A theoretical analysis of thermoelectricity along graphite layer planes. It is shown how the TEP can be derived from first principles using the Slonczewski-Weiss description of the graphite band structure. From the density of state equation we derive rigorous indications on the energy dependence of the scattering parameter, which allow us to undertake valid comparisons with experimental results. (2) Chapter II summarizes the experimental procedure. Great care was taken in order to arrive at reliable Seebeck coefficients. Thermocouple work was plagued by experimental difficulties (furnace conductance) of a similar nature as experienced by other investigators. (3) Finally, measured TEP was assessed in the light of the theory developed in Chapter I. New light is thus shed upon critical parameters such as the mobility ratio, which leads to a much improved description of transport in pyrolytic graphite and alloys of pyrolytic graphite. It is demonstrated that BPG/PG thermocouples are intrinsically capable of delivering exceptionally favorable output characteristics; a reduction to practice will require further efforts, in particular in connection with proper test-furnace design.
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Investigation Of Space Package Alightment Dynamic Load Design Criteria
Report Number: AFFDL TR 66-33
Author(s): York, K. C.; Ingels, C. R.; Maloney, J. G.
Corporate Author: General Dynamics Corp Pomona Ca Pomona Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 10/1/1966
Pages: 400
Contract: AF 33(615)-1832
Project: 1370
Task: 137008
AD Number: AD0806838
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Abstract Text:
This report presents the results of a limited parametric study of ten space package alightment systems. A state-of-the-art review in alightment dynamics was conducted prior to beginning the parametric study. Two three-dimensional digital simulations were developed for use in the parametric study. Each of these simulates a basic design concept of an alightment system. Two types of alightment systems were examined. One for a 300 pound capsule with electronic cargo and one for a 3000 pound capsule with human cargo. An experimental program was performed to permit a comparison of predicted and measured acceleration time histories during alightment. Generally, excellent correlation was shown. Energy absorbing material or techniques are shown to be a secondary consideration in determining the efficiency of an alightment system. A three-dimensional digital simulation of alightment dynamics is concluded to be mandatory in the development of an alightment system. The feasibility of an alightment system, weighing 6 percent of the total capsule weight, to alight successfully on a 35 degree slope with a 12 degree capsule inclination is shown. Such a system is capable of handling a vertical velocity of 35 feet per second and a horizontal velocity of 15 feet per second.
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Methods of Calculating Aerodynamic Loads on Aircraft Structures: Part I - Wing-Body Interference Effects
Report Number: AFFDL TR 66-37 Part 1
Author(s): Christopher J. Borland
Corporate Author: Massachusetts Institute of Technology
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1966
Pages: 212
Contract: AF 33(615)-2291
Project: 1367
Task: 136715
AD Number: AD0807297
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Methods are proposed for calculating the distribution of aerodynamic loads due to mutual interference effects between wings and bodies. The methods fall into two ranges of applicability: linear, and nonlinear, with angle of attack. Applicability of the linear loads methods to aeroelastic calculations is discussed. A computer program is presented which may be used to calculate interference loads at subsonic Mach numbers on a configuration consisting of (1) a body of any varying elliptic cross section and camber distribution, and (2) a wing with straight leading and trailing edges of any sweep angle, twist distribution, and camber distribution, located above or below the body centerline. Extension to the supersonic case is indicated. Generally good agreement with experimental data is found. Nonlinear wing-body interference loads are also considered. Several possible methods of representing the separated flow about a wing-body combination are proposed, and analyzed by the slender body theory. Numerical procedures are outlined, and some comparisons with experimental data are made.
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Methods of Calculating Aerodynamic Loads on Aircraft Structures: Part II - Nonlinear Effects
Report Number: AFFDL TR 66-37 Part 2
Author(s): Thomas E. Chamberlain
Corporate Author: Massachusetts Institute of Technology
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1966
Pages: 66
Contract: AF 33(615)-2291
Project: 1367
Task: 136715
AD Number: AD0804305
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Methods of Calculating Aerodynamic Loads on Aircraft Structures: Part III - Effects of Engines, Stores and Wing-Tail Interference
Report Number: AFFDL TR 66-37 Part 3
Author(s): David C. Chou
Corporate Author: Massachusetts Institute of Technology
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1966
Pages: 70
Contract: AF 33(615)-2291
Project: 1367
Task: 136715
AD Number: AD0804299
Photo Enhancement: Not Needed
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Aircraft Ground-Flotation Investigation: Part II - Data Report on Test Section 1
Report Number: AFFDL TR 66-43 Part 2
Author(s): W. Brabston, A. Rutledge, and W. Hill
Corporate Author: U. S. Army Engineer Waterways Experiment Station
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 4/1/1966
Pages: 36
Contract: Laboratory Research - No Contract
Project: 410-A
Task: None Given
AD Number: AD0484672
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Aircraft Ground-Flotation Investigation: Part III - Data Report on Test Section 2
Report Number: AFFDL TR 66-43 Part 3
Author(s): W. Brabston, A. Rutledge, and W. Hill
Corporate Author: U. S. Army Engineer Waterways Experiment Station
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 4/1/1966
Pages: 40
Contract: Laboratory Research - No Contract
Project: 410-A
Task: None Given
AD Number: AD0484673
Photo Enhancement: Complete
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Aircraft Ground-Flotation Investigation: Part V - Data Report on Test Section 4
Report Number: AFFDL TR 66-43 Part 5
Author(s): W. Brabston and W. Hill, Jr.
Corporate Author: U. S. Army Engineer Waterways Experiment Station
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1966
Pages: 40
Contract: Laboratory Research - No Contract
Project: 410-A
Task: None Given
AD Number: AD0809381
Photo Enhancement: Complete
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Aircraft Ground-Flotation Investigation: Part VII - Data Report on Test Section 6
Report Number: AFFDL TR 66-43 Part 7
Author(s): W. Brabston and W. Hill, Jr.
Corporate Author: U. S. Army Engineer Waterways Experiment Station
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1966
Pages: 44
Contract: Laboratory Research - No Contract
Project: 410-A
Task: None Given
AD Number: AD0809190
Photo Enhancement: Complete
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Aircraft Ground-Flotation Investigation: Part VIII - Data Report on Test Section 7
Report Number: AFFDL TR 66-43 Part 8
Author(s): W. Brabston and W. Hill, Jr.
Corporate Author: U. S. Army Engineer Waterways Experiment Station
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1966
Pages: 36
Contract: Laboratory Research - No Contract
Project: 410-A
Task: None Given
AD Number: AD0808382
Photo Enhancement: Complete
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Aircraft Ground-Flotation Investigation: Part IX - Data Report on Test Section 8
Report Number: AFFDL TR 66-43 Part 9
Author(s): A. Rutledge and W. Hill, Jr.
Corporate Author: U. S. Army Engineer Waterways Experiment Station
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 9/1/1966
Pages: 34
Contract: Laboratory Research - No Contract
Project: 410-A
Task: None Given
AD Number: AD0805290
Photo Enhancement: Complete
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Aircraft Ground-Flotation Investigation: Part X - Data Report on Test Section 9
Report Number: AFFDL TR 66-43 Part 10
Author(s): W. Brabston and W. Hill, Jr.
Corporate Author: U. S. Army Engineer Waterways Experiment Station
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 9/1/1966
Pages: 38
Contract: Laboratory Research - No Contract
Project: 410-A
Task: None Given
AD Number: AD0805295
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Aircraft Ground-Flotation Investigation: Part XI - Data Report on Test Section 10
Report Number: AFFDL TR 66-43 Part 11
Author(s): W. Brabston and W. Hill, Jr.
Corporate Author: U. S. Army Engineer Waterways Experiment Station
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 9/1/1966
Pages: 30
Contract: Laboratory Research - No Contract
Project: 410-A
Task: None Given
AD Number: AD0805278
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Aircraft Ground-Flotation Investigation: Part XII - Data Report on Test Section 12
Report Number: AFFDL TR 66-43 Part 12
Author(s): W. Brabston and G. Hammitt II
Corporate Author: U. S. Army Engineer Waterways Experiment Station
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 9/1/1966
Pages: 28
Contract: Laboratory Research - No Contract
Project: 410-A
Task: None Given
AD Number: AD0805279
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Aircraft Ground-Flotation Investigation: Part XIII - Data Report on Test Section 13
Report Number: AFFDL TR 66-43 Part 13
Author(s): J. Watkins and G. Hammitt II
Corporate Author: U. S. Army Engineer Waterways Experiment Station
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 10/1/1966
Pages: 38
Contract: Laboratory Research - No Contract
Project: 410-A
Task: None Given
AD Number: AD0809193
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Aircraft Ground-Flotation Investigation: Part XIV - Data Report on Test Section 14
Report Number: AFFDL TR 66-43 Part 14
Author(s): J. Watkins and G. Hammitt II
Corporate Author: U. S. Army Engineer Waterways Experiment Station
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 9/1/1966
Pages: 34
Contract: Laboratory Research - No Contract
Project: 410-A
Task: None Given
AD Number: AD0805296
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KC-135 Power Spectral Vertical Gust Load Analysis: Volume II - Supplemt Results
Report Number: AFFDL TR 66-57 Volume 2
Author(s): Robert N. Latz
Corporate Author: The Boeing Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 7/1/1966
Pages: 134
Contract: AF 33(615)-2454
Project: 1367
Task: 136702
AD Number: AD0806913
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Preliminary Development of Gust Design Procedures Based on Power Spectral Techniques: Volume I - Theoretical and General Considerations
Report Number: AFFDL TR 66-58 Volume 1
Author(s): John C. Houbolt
Corporate Author: Aeronautical Research Associates of Princeton, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 7/1/1966
Pages: 34
Contract: AF 33(615)-2144
Project: 1367
Task: 136702
AD Number: AD0801543
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Preliminary Development of Gust Design Procedures Based on Power Spectral Techniques: Volume II - Summary of Possible Procedures
Report Number: AFFDL TR 66-58 Volume 2
Author(s): John C. Houbolt
Corporate Author: Aeronautical Research Associates of Princeton, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 7/1/1966
Pages: 48
Contract: AF 33(615)-2144
Project: 1367
Task: 136702
AD Number: AD0800033
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Approximate Structural Analysis Techniques Employing Undetermined Parameters
Report Number: AFFDL TR 66-59
Author(s): I. U. Ojalvo and R. F. Russell
Corporate Author: Fairchild Hiller Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 7/1/1966
Pages: 166
Contract: AF 33(615)-2972
Project: 1467
Task: 146702
AD Number: AD0486292
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Adaptive Characteristics of the Human Controller of Time-Varying Systems
Report Number: AFFDL TR 66-60
Author(s): Jerome I. Elkind and Duncan C. Miller
Corporate Author: Bolt Beranek and Newman Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1967
Pages: 194
Contract: AF 33(657)-10124
Project: 8219
Task: 821905
AD Number: AD0665455
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Effects of Manipulator Restraints on Human Operator Performance
Report Number: AFFDL TR 66-72
Author(s): R. E. Magdaleno; D. T. McRuer
Corporate Author: Air Force Flight Dynamics Laboratory
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1966
Pages: 60
Contract: AF 33(657)-10835
Project: None Given
Task: None Given
AD Number: AD0646653
Photo Enhancement: Not Needed
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Investigation Of Friction, Wear And Failure In Aerospace Bearings
Report Number: AFFDL TR 66-75
Author(s): Staph, H. E.; Ku, P. M.
Corporate Author: Southwest Research Inst San Antonio TX
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 7/1/1966
Pages: 64
Contract: AF 33)615)-1859
Project: None Given
Task: None Given
AD Number: AD0802110
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Abstract Text:
Operation of a facility for measuring cage and inner race temperatures of lightly-loaded 20-mm angular-contact ball bearings at high speed and vacuum is described. Results of tests on 440C ball bearings with MoS2-epoxy compact cages at 300 F and with Niresist cages coated with MoS2-graphite-sodium silicate solid film at 600 F are given. The latter bearings, for the short (about 1 hour) test time, ran smoother and with less raceway damage than did the bearings with the epoxy-MoS2 cages.
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Sonic Fatigue Tolerance of Glass Filament Structure: Experimental Results
Report Number: AFFDL TR 66-78
Author(s): J. A. Hayes
Corporate Author: North American Aviation, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1966
Pages: 168
Contract: AF 33(615)-2638
Project: 1471
Task: 147101
AD Number: AD0810558
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Solid-State Display Devices
Report Number: AFFDL TR 66-81
Author(s): Glen Van Winkle; Mark Debono
Corporate Author: Lear Siegler, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1966
Pages: 77
Features: + Foldout(s)
Contract: AF 33(657)-11554
Project: 6190
Task: 619009
AD Number: AD0643525
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Design Calculations on Proven Trainer and Fighter Aircraft for the Verification of a Gust Design Procedure
Report Number: AFFDL TR 66-82
Author(s): Chintsun Hwang, B. D. Kamberg, W. S. Pi, A. K. Cross
Corporate Author: Northrop Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 7/1/1966
Pages: 172
Contract: AF 33(615)-2625
Project: 1367
Task: 136702
AD Number: AD0800059
Photo Enhancement: Not Needed
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Statistical Control System Design
Report Number: AFFDL TR 66-83
Author(s): R. Reiss, J. Mendelsohn, A. Van Gelder and G. Taylor
Corporate Author: Grumman Aircraft Engineering Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 10/1/1966
Pages: 116
Contract: AF 33(615)-2431
Project: 8219
Task: 821904
AD Number: AD0648023
Photo Enhancement: Not Needed
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Development Design Methods for Predicting Hypersonic Aerodynamic Control Characteristics
Report Number: AFFDL TR 66-85
Author(s): Z. Popinski and C. F. Ehrlich
Corporate Author: Lockheed-California Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 9/1/1966
Pages: 278
Contract: AF 33(615)-2512
Project: 8219
Task: 821902
AD Number: AD0644251
Photo Enhancement: Complete
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A Prototype Peripheral Vision Aircraft Attitude Display
Report Number: AFFDL TR 66-91
Author(s): William R. Williamson
Corporate Author: Air Force Flight Dynamics Laboratory
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 10/1/1966
Pages: 20
Contract: AF 33(615)-2895
Project: 6190
Task: 619004
AD Number: AD0648585
Photo Enhancement: Complete
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Aerodynamic Noise Simulation In Sonic Fatigue Facility
Report Number: AFFDL TR 66-112
Author(s): Lyon, R. H.; Gordon, C. G.; Stern, R.; Wiener, F. M.
Corporate Author: Bolt Beranek And Newman Inc Cambridge Mass
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 11/1/1966
Pages: 72
Contract: AF 33(615)-1290
Project: 4437
Task: 443701
AD Number: AD0648022
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Abstract Text:
The possibility of simulating a turbulent boundary-layer noise environment using the air-flow capability of the RTD Sonic Fatigue Facility is investigated. The philosophy is adopted that it is the mechanical power absorbed by the structure from the environment that is to be duplicated. Calculations are developed that allow the prediction of the mechanical power injected into a structure by a turbulent boundary layer (TBL), and by a turbulent wall-jet. The possibility of replacing the power injected by the TBL by using turbulent wall-jets impinging on a structural model of a section of a supersonic transport is studied. Results indicate that high-frequency excitation (above 1kHz) can be adequately simulated, but that the air-flow capabilities of the facility would be exceeded by an attempt to excite a structure as large as the one chosen by a set of wall-jets at lower frequencies.
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Investigation of Boundary Layer Transition in Hypersonic Flow at Angle of Attack
Report Number: AFFDL TR 66-122
Author(s): A. L. Nagel; R. T. Savage; R. Wanner; R. W. Blank
Corporate Author: The Boeing Company
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1966
Pages: 204
Contract: AF 33(615)-2011
Project: 1366
Task: 136606
AD Number: AD0803781
Photo Enhancement: Complete
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Human Pilot Dynamic Response in Single-Loop Systems with Compensatory and Pursuit Displays
Report Number: AFFDL TR 66-137
Author(s): R. J. Wasicko; D. T. McRuer; R. E. Magdaleno
Corporate Author: Systems Technology, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1966
Pages: 79
Contract: AF 33(657)-10835
Project: None Given
Task: None Given
AD Number: AD0646652
Photo Enhancement: Not Needed
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Human Pilot Dynamics with Various Manipulators
Report Number: AFFDL TR 66-138
Author(s): D. T. McRuer; R. E. Magdaleno
Corporate Author: Systems Technology, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1966
Pages: 54
Contract: AF 33(657)-10835
Project: None Given
Task: None Given
AD Number: AD0645289
Photo Enhancement: Complete
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Measurement And Analyses Of The J57-P21 Noise Field
Report Number: AFFDL TR 66-147
Author(s): Hermes, P. H.; Smith, D. L.
Corporate Author: Air Force Flight Dynamics Laboratory
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 10/1/1966
Pages: 136
Contract: Laboratory Research - No Contract
Project: 1471
Task: 147102
AD Number: AD0648072
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Abstract Text:
A noise survey of a J57-P21 turbojet engine was conducted to provide a basis for the development of a refined empirical noise prediction technique. The measurements were obtained at 65 locations for 5 engine power settings. The 1/3 octave and overall sound pressure levels (SPL's) for each location and engine power setting are presented. SPL contours are presented for overall and selected 1/3 octave bandwidths. Ground reflection effects on the 1/3 octave band SPL's are evaluated. Comparisons are made with other existing data. Differences of up to 15 decibels (db) are found when comparing the 1/3 octave band levels. Velocity exponents (n), based on the Lighthill parameter, are presented for each location and compared with existing data. Poor agreement is found among the measurement programs. The effect of ground reflection on the n values is investigated and an n field is presented in which interference effects are eliminated. The effect of varying noise directional properties with jet velocity on the n values is evaluated. An n field, corrected for both ground reflection and varying noise directional properties, is presented. This essentially constant n field clearly indicates the heavy dependence of the n values on noise directional changes with jet velocity. The corrected n field equation is considered the basis of a noise prediction method which appears to be accurate for jet flows with exit Mach numbers ranging from 0.5 to 2.0
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The Development And Evaluation Of The Cal/Air Force Dynamic Wind-Tunnel Testing System. Part I. Description And Dynamic Tests Of An F-80 Model
Report Number: AFFDL TR 66-153 Part 1
Author(s): Statler, Irving C.; Tufts, Orren B.; Hirtreiter, Walter J.
Corporate Author: Cornell Aeronautical Lab Inc Buffalo N Y
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 2/1/1967
Pages: 155
Features: + Foldout(s)
Contract: AF 33(616)-8034
Project: None Given
Task: None Given
AD Number: AD0651438
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Abstract Text:
The Cornell Aeronautical Laboratory (CAL) system provides a unique mounting through which a model can be forced precisely in any desired planar sinusoidal motion. The versatility and overall accuracy of the CAL/Air Force dynamic testing system was demonstrated during a series of wind-tunnel tests. These tests permitted, for the first time, a measurement of the separate components of the rotary damping moment. The moment due to rate of change of angle of attack was measured by oscillating the model in pure plunging motion. The moment due to pitch rate was measured during pitching motion. The sum of these is compared with the total rotary damping moment as measured in rotation. Comparisons of data taken at two frequencies and four Mach numbers indicate that the components are accurate to within plus or minus ten percent of the total rotary damping moment. The results are compared with theory, flight test data, and other wind-tunnel measurements on the same and similar models. Future applications of this equipment are reviewed, particularly with regard to its use as a research tool to support basic investigations for the development of theoretical or semiempirical methods for predicting dynamic stability characteristics of aircraft at transonic speeds.
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The Development And Evaluation Of The Cal/Air Force Dynamic Wind-Tunnel Testing System. Part II. Dynamic Tests Of An F-104 Model.
Report Number: AFFDL TR 66-153 Part 2
Author(s): Statler, Irving C.
Corporate Author: Cornell Aeronautical Lab Inc Buffalo N Y
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 2/1/1967
Pages: 42
Contract: AF 33(616)-8034
Project: None Given
Task: None Given
AD Number: AD0651437
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Abstract Text:
The F-104 model was designed and fabricated by the Air Force Flight Dynamics Laboratory and incorporated an unusual force and motion sensing system utilizing an internal dummy model with duplicate mass, inertia, and c.g. location. Longitudinal dynamic tests were performed with this model up through the transonic speed range. The results are evaluated with respect to the operation of the dynamic testing system and to the performance of the dummy model for measuring motion and canceling inertial loads.
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Low Pressure Type Expandable Aircraft Tire Characteristics
Report Number: AFFDL TR 66-170
Author(s): Wagner, Paul M.
Corporate Author: Air Force Flight Dynamics Laboratory
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 3/1/1967
Pages: 94
Contract: Laboratory Research - No Contract
Project: 1369
Task: 136903
AD Number: AD0815460
Photo Enhancement: Complete
Abstract Text:
Type 3 (low pressure) expandable aircraft tires of the 9.50-16 and 23.00-20 sizes were investigated. These tires with their 30 to 50 percent outside diameter expansion capabilities were subjected to simulated landing taxi and taxi takeoff conditions. Results indicate that the load capacity and life of the expandable tires are equivalent to standard tires of the same size. Takeoff speeds on the order of 200 MPH were obtained on tires of both sizes.
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Format II - Second Version of Fortran Matrix Abstraction Technique: Volume II, Supplement I,: Description of Digital Computer Program
Report Number: AFFDL TR 66-207 Volume 2 Supplement 1
Author(s): W. J. Lackey; R. E. Wild
Corporate Author: McDonnell Douglas Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1968
Pages: 88
Contract: F33615-67-C-1258
Project: 1467
Task: 146705
AD Number: AD0683781
Photo Enhancement: Not Needed
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Format - Fortran Matrix Abstraction Technique. Volume V. Engineering User And Technical Report.
Report Number: AFFDL TR 66-207 Volume 5
Author(s): Pickard, J.
Corporate Author: Douglas Aircraft Co Inc Long Beach Calif Aircraft Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1968
Pages: 700
Contract: F33615-67-C-1258
Project: 1467
Task: 146705
AD Number: AD0683261
Photo Enhancement: Not Needed
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Format-Fortran Matrix Abstraction Technique. Volume V - Supplement 1. Engineering User and Technical Report - Extended.
Report Number: AFFDL TR 66-207 Volume 5 Supplement 1
Author(s): Pickard, J.
Corporate Author: Douglas Aircraft Company, Long Beach, California
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1970
Pages: 76
Contract: F33615-68-C-1633
Project: 1467
Task: 146705
AD Number: AD0713727
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Format-Fortran Matrix Abstraction Technique. Volume VI. Description Of Digital Computer Program - Phase I.
Report Number: AFFDL TR 66-207 Volume 6
Author(s): Cogan, J. P., Jr.; Morris, R. C.; Serpanos, J. E;. Wells, J. R.
Corporate Author: McDonnell Douglas Corp Long Beach Calif Douglas Aircraft Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 12/1/1968
Pages: 746
Contract: F33615-67-C-1258
Project: 1467
Task: 146705
AD Number: AD0683262
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Format-Fortran Matrix Abstraction Technique. Volume VI. Supplement I. Description of Digital Computer Program. Phase I. Extended.
Report Number: AFFDL TR 66-207 Volume 6 Supplement 1
Author(s): Morris, R.C.
Corporate Author: Douglas Aircraft Company, Long Beach, California
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1970
Pages: 70
Contract: F33615-68-C-1633
Project: 1467
Task: 146705
AD Number: AD0713149
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Format-Fortran Matrix Abstraction Technique. Volume VII - Suppelment I. Description of Digital Computer Program - Phase III - Extended.
Report Number: AFFDL TR 66-207 Volume 7 Supplement 1
Author(s): Frank, J. A.
Corporate Author: Douglas Aircraft Company, Long Beach, California
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 8/1/1970
Pages: 46
Contract: F33615-68-C-1633
Project: 1467
Task: 146705
AD Number: AD0713840
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Application Of The Subdomain (Biezeno-Koch) Method To Circular Plate Bending
Report Number: AFFDL TR 66-215
Author(s): Adams, O. E., Jr
Corporate Author: Air Force Flight Dynamics Laboratory
Laboratory: Flight Dynamics Laboratory
Publication Date: 6/1/1967
Pages: 66
Contract: Laboratory Research - No Contract
Project: 1467
Task: 146702
AD Number: AD0819182
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Measurement Of The Diffraction Correction Of The Gulton Model P420m-6 Microphone
Report Number: AFFDL TR 66-223
Author(s): Ortega, Jose C.
Corporate Author: Western Electro-Acoustic Lab Inc Santa Monica CA
Laboratory: Flight Dynamics Laboratory
Publication Date: 5/1/1967
Pages: 42
Contract: AF 33(615)-3746
Project: 1472
Task: 147203
AD Number: AD0816179
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Abstract Text:
The methods and instrumentation used to obtain the diffraction correction for the Gulton P420M-6 microphone are described. The diffraction correction was measured for two microphone mounting configurations at several angles of sound incidence over the frequency range 400 cps to 25K cps. In addition, the random incidence response for the Gulton P420M-6 microphone was obtained over the same frequency range. Analysis of the measured data shows that the precision of the measurements is very good below 15K cps (standard deviation being within plus or minus .6 db) and gradually decreases at higher frequencies (standard deviation being plus or minus 1.2 db at 20K cps and +3.9 db, -7.4 db at 25K cps). The pressure calibration for the Gulton P420M-6 microphone was obtained using the well known coupler method and also using an electrostatic actuator. The results of these measurements show that the electrostatic actuator method of calibration produces reliable results when used with the Gulton microphone.
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Investigation Of Ablation Effects On Hypersonic Dynamic Stability Of A 10 Deg. Cone.
Report Number: AFFDL TR 66-230
Author(s): Moore, Dave R.; Stalmach,Charles J. , Jr.; Pope, Thomas C.
Corporate Author: LTV Aerospace Corp Dallas Tex LTV Vought Aeronautics Div
Laboratory: Air Force Flight Dynamics Laboratory
Publication Date: 1/1/1967
Pages: 88
Contract: AF 33(615)-2902
Project: 8219
Task: 821902
AD Number: AD0656492
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Abstract Text:
An experimental program has been conducted in the LTV Hypervelocity Wind Tunnel at M = 17 to investigate the effects of ablation product characteristics and thermal lags on re-entry vehicle dynamic stability. The free oscillation method of dynamic stability measurement was used and the ablation processes were simulated by the controlled mass injection through four sections of the porous model skin. The flow rates through the top and bottom quadrants were oscillated at the same frequency and at an amplitude proportional to the model motion. The thermal lag effect was investigated with nitrogen injection into nitrogen tunnel flow at several different mass flow rates and phase angles between the oscillating mass flow and the body motion. The ablation product study was conducted by injecting gases other than nitrogen with specific heat ratio and molecular weight being the test parameters in addition to mass flow rate. The results obtained from these tests indicate significant effect on dynamic stability with both injection phase angle and some characteristics of the injected gas. The effects of model frequency, Reynolds number and mass injection distribution were also investigated and some static pressure measurements were made near the aft of the model. Appendices to the report contain tabulations of the pertinent data and discussions of supporting analytical studies and data analysis.
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