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  • Aerodynamics
  • Aircraft Stability and Control
  • 2020-2024
  • 1960-1964  (5)
  • 1945-1949
  • 1963  (5)
Collection
Keywords
Years
  • 2020-2024
  • 1960-1964  (5)
  • 1945-1949
Year
  • 1
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    Effects of Mass Addition on the Stability of Slender Cones at Hypersonic Speeds (1963)
    In:  Other Sources
    Details
    Publication Date: 2017-03-07
    Description: The effect of mass addition on the flow over bodies moving at hypersonic speeds has been studied by several investigators (e.g., Cresci and Libby). In most of this work, primary attention logically has been directed toward the effects of foreign-gas injection on heat transfer and pressure distributions, and, principally for this reason, most of the work ha been done at zero angle of attack. The foreign gas can be provided either by some active injection system or by the action of an ablation heat shield. With increasing rates of injection, the basic flow about the body can be affected significantly. One such effect was observed in the paper by Cresci and Libby, where it was shown that the shockwave standoff distance can be increased by gas injection at the nose of a body.
    Keywords: Aerodynamics
    Type: AIAA Journal; Volume 1; No. 4; 939-940
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Application of Dorodnitsyn's Integral Method to Nonequilibrium Flows over Pointed Bodies (1963)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Dorodnitsyn's integral method is used to obtain an approximate solution to the supersonic nonequilibrium flow over pointed bodies with attached shock waves. The partial differential equations governing the flow are converted to an approximate set of ordinary equations, which are solved by numerical integration starting at the body tip. Detailed analytical and numerical results for the first approximation are presented, considering the vibrational relaxation of a diatomic gas over a wedge or cone. It is shown that the first approximation yields: (1) The exact flow-variable gradients at the wedge tip (2) Expressions for the flow-variable gradients at the cone tip which are in agreement with extrapolations of characteristics calculations (3) A good approximate algebraic solution for frozen or equilibrium conical flow (4) An approximate expression for the nonequilibrium-flow stream function which affords a means of obtaining variations across the shock layer of the temperature and vibrational energy. Numerical results for both the wedge and cone compare favorably with identical cases computed by the method of characteristics.
    Keywords: Aerodynamics
    Type: NASA-TN-D-1942
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Some Effects of Sweep and Aspect Ratio on the Transonic Flutter Characteristics of a Series of Thin Cantilever Wings Having a Taper Ratio of 0.6 (1963)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: An investigation of the flutter characteristics of a series of thin cantilever wings having taper ratios of 0.6 was conducted in the Langley transonic blowdown tunnel at Mach numbers between 0.76 and 1.42. The angle of sweepback was varied from 0 degrees to 60 degrees on wings of aspect ratio 4, and the aspect ratio was varied from 2.4 to 6.4 on wings with 45 degrees of sweepback. The results are presented as ratios between the experimental flutter speeds and the reference flutter speeds calculated on the basis of incompressible two-dimensional flow. These ratios, designated the flutter-speed ratios, are given as functions of Mach number for the various wings. The flutter-speed ratios were characterized, in most cases, by values near 1.0 at subsonic speeds with large increases in the speed ratios in the range of supersonic speeds investigated. Increasing the sweep effected increases in the flutter-speed ratios between 0 degrees and 30 degrees followed by progressive reductions of the speed ratios to nearly 1.0 as the sweep was increased from 30 degrees to 60 degrees. Reducing the aspect ratio from 6.4 to 2.4 resulted in progressively larger values of the flutter-speed ratios throughout the Mach number range investigated.
    Keywords: Aerodynamics
    Type: NASA-TN-D-1594
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Full-Scale Wind-Tunnel Investigation of the Drag Characteristics of an HU2K Helicopter Fuselage (1963)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An investigation was conducted in the Langley full-scale tunnel to determine the drag characteristics of the HU2K helicopter fuselage. The effects of body shape, engine operation, appendages, and leakage on the model drag were determined. The results of the tests showed that the largest single contribution to the parasite drag was that of the rotor hub installation which produced about 80 percent of the drag of the sealed and faired production body. Fairings on the rotor hub and blade retentions, or a cleaned-up hub and retentions, appeared to be the most effective single modifications tested. The total drag of all protuberances and air leakage also contributed a major part of the drag - an 83-percent increase over the drag of the sealed and faired production body. An additional increment of drag was caused by the basic shape of the fuselage - 19 percent more than the drag obtained when the fuselage shape was extensively refaired. Another sizable increment of drag was caused by the engine oil-cooler exit which gave a drag of 8 percent of that of the sealed and faired production body.
    Keywords: Aerodynamics
    Type: NASA-TM-SX-848 , L-3338 , N-AM-110
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Full-Scale Wind-Tunnel Investigation of the VZ-5 Four-Propeller Deflected-Slipstream VTOL Airplane (1963)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The investigation was conducted to determine the static stability and control characteristics of the VZ-5 VTOL air-plane over the speed range from hovering to forward flight. Force and moment data were taken over a range of angles of attack of 0 to 15 deg and a range of sideslip of +/-10 deg for flap deflections from 0 to 77 deg. The longitudinal stability and trim characteristics were found to be quite unacceptable and it did not seem that they could be corrected with any reasonable modifications to the airplane.
    Keywords: Aerodynamics
    Type: NASA-TM-SX-805 , L-3059
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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