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  • Aircraft Design, Testing and Performance
  • Aircraft Stability and Control
  • 1965-1969  (28)
  • 1955-1959  (158)
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  • 1
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    Progress of the X-15 Research Airplane Program (1965)
    In:  CASI
    Details
    Publication Date: 2019-09-24
    Description: This compilation consists of papers presented at the fourth conference on progress of the X-15 Research Airplane Program held at the NASA Flight Research Center, Edwards Air Force Base, California, October 7, 1965. This conference was sponsored by the Research Airplane Committee of the U.S. Air Force, the U.S. Navy, and the National Aeronautics and Space Administration. Papers were presented by representatives from the NASA Flight Research Center, the NASA Langley Research Center, the U.S. Air Force Flight Test Center, and the U.S. Air Force Aeronautical Systems Division.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-SP-90 , Progress of the X-15 Research Airplane Program; Oct 07, 1965; Edwards, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Lightning Hazards to Aircraft Fuel Tanks (1958)
    In:  CASI
    Details
    Publication Date: 2019-08-31
    Description: The hazards of lightning strokes to aircraft fuel tanks have been investigated in artificial-lightning-generation facilities specifically constructed to duplicate closely the natural lightning discharges to air craft determined through flight research programs and analysis of lightning-damaged aircraft over a period of many years. Explosion studies were made in an environmental explosion chamber using small fuel tanks under various simulated flight conditions. The results showed that there is a primary hazard whenever there is direct puncture of the fuel-tank wall, whereas the ignition of fuel by hot spots on tank walls due to lightning strikes is unlikely. Punctures of fuel-tank walls by artificial-lightning discharges produced explosions of the fuel in the mixture range from excessively lean to rich mixtures. None of the aluminum alloys, 0.081 inch thick or over, were punctured by the laboratory discharges representative of natural-lightning discharges to aircraft; however, reliance on this wall thickness for complete protection would not be justified, because occasional strokes are known to be of greater magnitude and because statistics reveal variations in the damage pattern. Data gathered by the Lightning and Transients Research Institute on lightning strokes to aircraft show that 90 percent of the strokes recorded have occurred in the temperature range of -10 to +10 C, where many of the jet fuels are flammable but where aviation gasoline is overrich. Also, 10 percent of the strokes recorded have been to the wings, which are the principal fuel-storage areas for modern aircraft. Thus, there is a hazard, particularly for jet fuels. Certain protective measures are indicated by the studies to date, such as the use of lightning diverter rods, thickening of the wing skin in areas near the most probable stroke paths, and the use of fuel-tank liners in critical areas.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-4326
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Streamlines in a Steady Flow (1966)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The author states some tentative principles in the absence of an existence theorem of sufficiently general solutions of viscous fluid equations which could be applied by engineers. These principles are used for the characterization of the singular points of flow, which can be determined and identified by experimental engineers to solve a problem of fluid mechanics by a model.
    Keywords: Aircraft Design, Testing and Performance
    Type: AD-A395523 , NASA-TT-F-405-Rev , NAS 1.77:405-Rev , La Recherche Aerospatiale; 105; 3-9
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Summary and Analysis of Horizontal-Tail Contribution to Longitudinal Stability of Swept-Wing Airplanes at Low Speeds (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Air-flow characteristics behind wings and wing-body combinations are described and are related to the downwash at specific tall locations for unseparated and separated flow conditions. The effects of various parameters and control devices on the air-flow characteristics and tail contribution are analyzed and demonstrated. An attempt has been made to summarize certain data by empirical correlation or theoretical means in a form useful for design. The experimental data herein were obtained mostly at Reynolds numbers greater than 4 x 10(exp 6) and at Mach numbers less than 0.25.
    Keywords: Aircraft Stability and Control
    Type: NASA-TR-R-49
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Summary of NASA Support of the F-111 Development Program (1966)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The F-111 is a biservice, multimission, tactical aircraft being developed for the Air Force and Navy by General Dynamics and Grumman. The general arrangement of the F-111 is shown in figure 1. This aircraft, through the use of the "variable sweep wing" concept, offers the possibility of combining a wide range of mission capabilities into a single aircraft. The F-111 is a direct outgrowth of the Langley Research Center's variable sweep research which began in 1947. The early research culminated in the X-5 variable sweep research airplane which demonstrated the advantage and feasibility of in-flight sweep variation~ The X-5 utilized the translating wing concept to offset the longitudinal stability variation with sweep changes. Later Langley research beginning in 1958 resulted in the "outboard pivot" concept which eliminated the need for wing translation and led .to the TFX (F-111) concept. A chronology of the NACA/NASA variable sweep research effort and direct su~port of the TFX up to the awarding of the contract to General Dynamics/Grumman on November 24, 1962, is presented in refer'ence 1. Since the awarding of the contract, the Langley, Ames, Lewis, and Flight Research Centers have been actively supporting the F-111 development program. Because of the strong NASA interest in this aircraft and the large magnitude of NASA support involved, it was felt desirable to document this support. The purpose of this paper therefore is to present a brief summary of the NASA support, in chronological order, through December 1965, beginning with the awarding of the contract in November 1962.
    Keywords: Aircraft Design, Testing and Performance
    Type: LWP-246
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Aeroelastic Problems of Airplane Design (1956)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The technical memorandum briefly summarizes the growth of interest in aeroelastic phenomena as aircraft speed increased and wing designs changed for faster aircraft. Different types of aircraft vibrations are then introduced, and the mathematical basis for the theory behind them is described. Special attention is given to static oscillations, wing flutter, and the flutter of skin panels. The last section of the memorandum deals with the prevention of flutter by design specifications.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1402 , Zeitschrift fuer Flugwissenschaften 3 Jahrgang, Heft 1; 1-18
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Investigation of Low-Subsonic Flight Characteristics of a Model of a Flat-Bottom Hypersonic Boost-Glide Configuration Having a 78 deg Delta Wing (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation of the low-subsonic stability and control characteristics of a model of a flat-bottom hypersonic boost-glide configuration having 78 deg sweep of the leading edge has been made in the Langley full-scale tunnel. The model was flown over an angle-of-attack range from 10 to 35 deg. Static and dynamic force tests were made in the Langley free-flight tunnel. The investigation showed that the longitudinal stability and control characteristics were generally satisfactory with neutral or positive static longitudinal stability. The addition of artificial pitch damping resulted in satisfactory longitudinal characteristics being obtained with large amounts of static instability. The most rearward center-of-gravity position for which sustained flights could be made either with or without pitch damper corresponded to the calculated maneuver point. The lateral stability and control characteristics were satisfactory up to about 15 deg angle of attack. The damping of the Dutch roll oscillation decreased with increasing angle of attack; the oscillation was about neutrally stable at 20 deg angle of attack and unstable at angles of attack of about 25 deg and above. Artificial damping in roll greatly improved the lateral characteristics and resulted in flights being made up to 35 deg angle of attack.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-X-201 , L-452
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Analysis of Acceleration, Airspeed, and Gust-Velocity Data From a Four-Engine Transport Airplane Operating Over a Northwestern United States Alaska Route (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Acceleration, airspeed, and altitude data obtained with an NACA VGH recorder from a four-engine commercial transport airplane operating over a northwestern United States-Alaska route were evaluated to determine the magnitude and frequency of occurrence of gust and maneuver accelerations., operating airspeeds, and gust velocities. The results obtained were then compared with the results previously reported in NACA Technical Note 3475 for two similar airplanes operating over transcontinental routes in the United States. No large variations in the gust experience for the three operations were noted. The results indicate that the gust-load experience of the present operation closely approximated that of the central transcontinental route in the United States with which it is compared and showed differences of about 4 to 1 when compared with that of the southern transcontinental route in the United States. In general, accelerations due to gusts occurred much more frequently than those due to operational maneuvers. At a measured normal-acceleration increment of 0.5g, accelerations due to gusts occurred roughly 35 times more frequently than those due to operational maneuvers.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-1-17-59L
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    A Flight Investigation of the Low-Speed Handling Qualities of a Tailless Delta-Wing Fighter Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Carrier landing-approach studies of a tailless delta-wing fighter airplane disclosed that approach speeds were limited by ability to control altitude and lateral-directional characteristics. More detailed flight studies of the handling-qualities characteristics of the airplane in the carrier-approach configuration documented a number of factors that contributed to the adverse comments on the lateral-directional characteristics. These were: (1) the tendency of the airplane to roll around the highly inclined longitudinal axis, so that significant sideslip angles developed in the roll as a result only of kinematic effects; (2) reduction of the rolling response to the ailerons because of the large dihedral effect in conjunction with the kinematically developed sideslip angles; and (3) the onset of rudder lock at moderate angles of sideslip at the lowest speeds with wing tanks installed. The first two of the factors listed are inseparably identified with this type of configuration which is being considered for many of the newer designs and may, therefore, represent a problem which will be encountered frequently in the future. The results are of added significance in the demonstration of a typical situation in which extraneous factors occupy so much of the pilot's attention that his capability of coping with the problems of precise flight-path control is reduced, and he accordingly demands a greater speed margin above the stall to allow for airspeed fluctuations.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-15-59A
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    An Analysis of Flight-Test Measurements of the Wing Structural Deformations in Rough Air of a Large Flexible Swept-Wing Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An analysis is made of wing deflection and streamwise twist measurements in rough-air flight of a large flexible swept-wing bomber. Random-process techniques are employed in analyzing the data in order to describe the magnitude and characteristics of the wing deflection and twist responses to rough air. Power spectra and frequency-response functions for the wing deflection and twist responses at several spanwise stations are presented. The frequency-response functions describe direct and absolute response characteristics to turbulence and provide a convenient basis for assessing analytic calculation techniques. The wing deformations in rough air are compared with the expected deformations for quasi-static loadings of the same magnitude, and the amplifications are determined. The results obtained indicate that generally the deflections are amplified by a small amount, while the streamwise twists are amplified by factors of the order of 2.0. The magnitudes of both the deflection velocities and the twist angles are shown to have significant effects on the local angles of attack at the various stations and provide the main source of aerodynamic loading, particularly at frequencies in the vicinity of the first wing-vibration mode.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-12-3-58L
    Format: application/pdf
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