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  • Aircraft Design, Testing and Performance
  • 2025-2025
  • 1980-1984  (22)
  • 1950-1954  (68)
  • 1
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    Wind-Tunnel Investigation of the Static Lateral Stability Characteristics of Wing-Fuselage Combinations at High Subsonic Speeds (1953)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A systematic research program is being carried out in the Langley high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics of various arrangements of the component parts of research-type airplane models, including some complete model configurations. Data are being obtained on characteristics in pitch, sideslip, and during steady roll at Mach numbers from 0.40 to about 0.95. This paper presents results which show the effect of taper ratio on the aerodynamic characteristics in sideslip of wing-fuselage combinations having wings with a sweep of 45 degrees at the quarter-chord line, an aspect ratio of 4, and a NACA 65A006 airfoil section.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L53B25a
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Flight Measurements of Average Skin-Friction Coefficients on a Parabolic Body of Revolution (NACA RM-10) at Mach Numbers from 1.0 to 3.7 (1954)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Measurement of average skin-friction coefficients have been made on six rocket-powered free-flight models by using the boundary-layer rake technique. The model configuration was the NACA RM-10, a 12.2-fineness-ratio parabolic body of revolution with a flat base. Measurements were made over a Mach number range from 1 to 3.7, a Reynolds number range 40 x 10(exp 6) to 170 x 10(exp 6) based on length to the measurement station, and with aerodynamic heating conditions varying from strong skin heating to strong skin cooling. The measurements show the same trends over the test ranges as Van Driest's theory for turbulent boundary layer on a flat plate. The measured values are approximately 7 percent higher than the values of the flat-plate theory. A comparison which takes into account the differences in Reynolds number is made between the present results and skin-friction measurements obtained on NACA RM-10 scale models in the Langley 4- by 4-foot supersonic pressure tunnel, the Lewis 8- by 6-foot supersonic tunnel, and the Langley 9-inch supersonic tunnel. Good agreement is shown at all but the lowest tunnel Reynolds number conditions. A simple empirical equation is developed which represents the measurements over the range of the tests.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L54G14
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Aircraft Inlet Ducts (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: After studying three Tech Briefs reports on NASA submerged duct technology developed for high performance aircraft, Wilhelm Cashen was able to adapt the technology to the induction intercooler system of turbocharged lightplanes. In lightplane installations, the submerged ducts introduce cool "ram" air to the propulsion system for greater operating efficiency.
    Keywords: Aircraft Design, Testing and Performance
    Type: Spinoff 1984; 95
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Effects of Horizontal-Control Planform and Wing-Leading-Edge Modification on Low-Speed Longitudinal Aerodynamic Characteristics of a Canard Airplane Configuration (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation at low subsonic speeds has been conducted in the Langley 300-MPH 7- by 10-foot tunnel. The basic wing had a trapezoidal planform, an aspect ratio of 3.0., a taper ratio of 0.143, and an unswept 80-percent-chord line. Modifications to the basic wing included deflectable full-span and partial-span leading-edge chord-extensions. A trapezoidal horizontal control similar in planform to the basic wing and a 60 deg sweptback delta horizontal control were tested in conjunction with the wing. The total planform area of each horizontal control was 16 percent of the total basic-wing area. Modifications to these horizontal controls included addition of a full-span chord-extension to the trapezoidal planform and a fence to the delta planform.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-X-549 , L-1372
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Longhorn Business Jets (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Developed in NASA's Aircraft Energy Efficiency program and manufactured by Gates Learjet Corporation, the winglet is an aerodynamic innovation designed to reduce fuel consumption and improve airplane performance. Winglets are lifting surfaces designed to operate in the "vortex" or air whirlpool which occurs at an airplane's wingtip. Complex flow of air around wingtip creates drag which retards the plane's progress. Winglet reduces strength of vortex and thereby reduces strength of drag. Additionally, winglet generates its own lift, producing forward thrust in the manner of a boat's sail. Combination of reduced drag and additional thrust adds up to significant improvement in fuel efficiency.
    Keywords: Aircraft Design, Testing and Performance
    Type: Spinoff 1980; 60
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Hang Gliders (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Francis M. Rogallo and his wife Gertrude researched flexible controllable fabric airfoils with a delta, V-shaped, configuration for use on inexpensive private aircraft. They were issued a flex-wing patent and refined their designs. Development of Rogallo wings, used by U.S. Moyes, Inc. substantially broadened the flexible airfoil technology base which originated from NASA's reentry parachute. The Rogallo technology, particularly the airfoil frame was incorporated in the design of a kite by John Dickenson. The Dickenson kite served as prototype for the Australian Moyes line of hang gliders. Company no longer exists.
    Keywords: Aircraft Design, Testing and Performance
    Type: Spinoff 1981; 79
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Temperature stabilized linkage (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A temperature compensated passive linkage for interconnecting two members having different coefficients of expansion. Preferably the linkage is utilized for interconnecting the stabilizer of a plane with its elevator. The stabilizer may be a graphite epoxy composite while the elevator may consist of aluminum-fiberglass. The differences in the rate of expansion of the two members is compensated by the linkage of the invention which in turn will move a side load hinge fitting to minimize aerodynamic and mechanical problems.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Composite aircraft structure having lightning protection (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A lightning protection system for advanced composite aircraft structures consisting of a sandwich structure including two layers of aluminum foil separated by a layer of dielectric material. The sandwich structure is applied to the surface of the composite aircraft structure desired to be protected from lightning strike damage thereby confining damage to the sandwich structure which can be removed and replaced.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Flow Over Inclined Bodies (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: It has been shown that the circumferential pressure distributions for the inclined body and circular cylinder deviate from their respective theoretical inviscid distributions on the lee or downstream side in the same manner. With the aid of visual flow techniques, it has been shown that there is a shedding of vortices within the crossflow field of the inclined body. It has also been found that the vortex configuration depoends to a large extent on the shape of the nose of the body. To illustrate this, vapor screen pictures were made and results are discussed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA Conference on Aerodynamic Design Problems of Supersonic Guided Missiles; Oct 02, 1951 - Oct 03, 1951; Moffett Field, CA; United States|Aerodynamic Characteristics of Bodies at Supersonic Speeds: A Collection of Three Papers; 31-44; NACA-RM-A51J25
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Helicopter Design Analysis (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Design of military and civil helicopters, produced by Bell Helicopter Textron, and aided by the use of COSMIC'S computer program VASP enables performance of more accurate analyses to insure product safety and improved production efficiency.
    Keywords: Aircraft Design, Testing and Performance
    Type: Spinoff 1982; 56
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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