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  • AERODYNAMICS
  • Life and Medical Sciences
  • 1970-1974  (514)
  • 1973  (514)
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Keywords
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Years
  • 1970-1974  (514)
Year
  • 1
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    Preliminary lift and drag characteristics of the F-8 supercritical wing airplane (1973)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: its Supercritical Wing Technol.: A Report on Flight Evaluation; p 59-70
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Externally blown flap dynamic loads (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Some of the principal results obtained in three series of measurements of fluctuating surface pressures induced on externally blown flaps by jet impingment are presented. Large- and small-scale models and hot- and cold-flow tests are considered. The discussion sets forth scaling parameters and consistent features of the root-mean-square values and spectra of the loading. Implications of these results with regard to sonic fatigue are indicated.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 131-142
    Format: text
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  • 3
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    Review of drag measurements from flight tests of manned aircraft with comparisons to wind-tunnel predictions (1973)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: In-flight studies of the overall and local components of drag of many types of aircraft were conducted. The primary goal of these studies was to evaluate wind-tunnel and semiempirical prediction methods. Some evaluations are presented in this paper which may be summarized by the following observations: Wind-tunnel predictions of overall vehicle drag can be accurately extrapolated to flight Reynolds numbers, provided that the base drag is removed and the boattail areas on the vehicle are small. The addition of ablated roughness to lifting body configurations causes larger losses in performance and stability than would be expected from the added friction drag due to the roughness. Successful measurements of skin friction have been made in flight to Mach numbers above 4. A reliable inflatable deceleration device was demonstrated in flight which effectively stabilizes and decelerates a lifting aircraft at supersonic speeds.
    Keywords: AERODYNAMICS
    Type: AGARD Aerodyn. Drag; 12 p
    Format: text
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  • 4
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    A summary of current research in rotor unsteady aerodynamics with emphasis on work at Langley Research Center (1973)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: The basic unsteady aerodynamic environment of the rotary wing is summarized. Some of the observed trends in the state of the art are discussed. Some of the research needs that will require attention are reported. A review of a number of research investigations as a part of a joint NASA/Army rotorcraft project is presented. The research is directed toward achieving a better understanding of rotor unsteady airfoils. The investigations include: (1) rotor maneuver loads; (2) level flight and maneuver wake prediction; (3) tip-vortex flow; (4) blade-vortex interactions; (5) dynamic stall; (6) transient Mach number air loads; and (7) development of variable geometry rotors.
    Keywords: AERODYNAMICS
    Type: AGARD Aerodyn. of Rotary Wings; 20 p
    Format: text
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  • 5
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    Integral equation for small perturbations of irrotational flows (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: An investigation is conducted concerning the validity of analytical methods which are based on deriving an integral equation, taking into account small perturbations in the case of a nonuniform but irrotational flow. The results obtained apply to a wide Mach number range, but are restricted to small amplitude motions and to nonviscous flows. It is shown that the integral equation relating the unknown velocity potential to the known normal flow velocity can be derived from the appropriate Green's identity.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Dec. 197
    Format: text
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  • 6
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    On the inviscid rolled-up structure of lift-generated vortices (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A simple form is presented of the relationships derived by Betz for the inviscid, fully developed structure of lift-generated vortices behind aircraft. An extension is then made to arbitrary span-load distributions by inferring guidelines for the selection of rollup centers for the vortex sheet. These techniques are easier to use and yield more realistic estimates of the rolled-up structure of vortices than the original form of Betz' theory when the span loading differs appreciably from elliptic loading.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 10; Nov. 197
    Format: text
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  • 7
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    Van Driest generalization applied to turbulent skin friction and velocity profiles measured on the wall of a Mach 7.4 wind tunnel (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Dec. 197
    Format: text
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  • 8
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    Effect of anisotropic turbulence on aerodynamic noise (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A model based on Lighthill's theory for predicting aerodynamic noise from a turbulent shear flow is developed. This model is a generalization of the one developed by Ribner. It does not require that the turbulent correlations factor into space and time-dependent parts. It replaces his assumption of isotropic turbulence by the more realistic one of axisymmetric turbulence. In the course of the analysis, a hierarchy of equations is developed wherein each succeeding equation involves more assumptions than the preceding equation but requires less experimental information for its use. The implications of the model for jet noise are discussed. It is shown that for the particular turbulence data considered anisotropy causes the high-frequency self-noise to be beamed downstream.
    Keywords: AERODYNAMICS
    Type: Acoustical Society of America; vol. 54
    Format: text
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  • 9
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    Three-dimensional separation for interaction of shock waves with turbulent boundary layers (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: For the interaction of shock waves with turbulent boundary layers, obtained experimental three-dimensional separation results and correlations with earlier two-dimensional and three-dimensional data are presented. It is shown that separation occurs much earlier for turbulent three-dimensional than for two-dimensional flow at hypersonic speeds.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Nov. 197
    Format: text
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  • 10
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    A graphical method for the investigation of shock interference phenomena (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Nov. 197
    Format: text
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