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  • AERODYNAMICS  (114)
  • 2005-2009
  • 2000-2004
  • 1985-1989  (114)
  • 1980-1984
  • 1986  (114)
  • 1
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    Transonic, turbulent boundary-layer separation generated on an axisymmetric flow model (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Experimental data describing the transonic, turbulent, separated flow generated by an axisymmetric flow model are presented. The model consisted of a circular-arc bump affixed to a straight, circular cylinder aligned with the flow direction. Measurements of the mean velocity, turbulence intensity, and Reynolds shear-stress profiles were made in the separated flow. These data revealed dramatic changes in the shear-stress levels as the flow passed through the interaction to reattachment. Behavior of the turbulence reaction to the imposed pressure gradients was examined in terms of the mixing length and the excursions of the turbulence from equilibrium.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 437-443
    Format: text
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  • 2
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    Basic studies on delta wing flow modifications by means of apex fences (1986)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effectiveness of apex fences on a 60-deg delta wing at low speeds was experimentally investigated. Resembling highly swept spoilers in appearance, the fences are designed to fold out of the wing apex region upper surface near the leading edges, where they generate a powerful vortex pair. The intense suction of the fence vortices augments lift in the apex region, the resulting positive pitching moment being utilized to trim trailing edge flaps for lift augmentation during approach and landing at relatively low angles of attack. The fences reduce the apex lift at high angles of attack, leading to a desirable nose-down moment. The above projected functions of the apex fence device were validated and quantified through low speed tunnel tests, comprising upper surface pressure surveys on a semispan model and balance measurements on a geometrically similar fully span wing/body configuration. Fence parameters such as area, shape, hinge position and deflection angle were investigated. Typical results are presented indicating the apex fence potential in controlling the longitudinal characteristics of a tail-less delta.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Vortex Flow Aerodynamics, Vol. 1; p 203-217
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Computation of transonic flow about helicopter rotor blades (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: An inviscid, nonconservative, three-dimensional full-potential flow code, ROT22, has been developed for computing the quasi-steady flow about a lifting rotor blade. The code is valid throughout the subsonic and transonic regime. Calculations from the code are compared with detailed laser velocimeter measurements made in the tip region of a nonlifting rotor at a tip Mach number of 0.95 and zero advance ratio. In addition, comparisons are made with chordwise surface pressure measurements obtained in a wind tunnel for a nonlifting rotor blade at transonic tip speeds at advance ratios from 0.40 to 0.50. The overall agreement between theoretical calculations and experiment is very good. A typical run on a CRAY X-MP computer requires about 30 CPU seconds for one rotor position at transonic tip speed.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 722-727
    Format: text
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  • 4
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    Vent modification of large ribbon parachutes to enhance cluster performance (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Due to uneven load sharing and lagging inflation rates, the design of the Large Main Parachute (LMP) cluster, used to recover the Space Shuttle steel case Solid Rocket Boosters, had to be modified. The cause of the problem was excessive variation in effective porosity in the crown area of the LMP during first stage inflation. The design modification consisted of adding horizontal ribbons above the existing vent band to reduce the vent porosity and better control the position and attitude of the vent lines. Performance of modified LMP's since introduction indicates that the load sharing between the clustered chutes has been significantly improved.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-2433
    Format: text
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  • 5
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    The flowfield structure of the 3-D shock wave - Boundary layer interaction generated by a 20 deg sharp fin at Mach 3 (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The three-dimensional oblique shock wave-turbulent boundary layer interaction generated by a sharp fin attached to a flat plate is investigated experimentally and theoretically for Mach 3 and Reynolds number 9 x 10 to the 5th using two different models. Both models employ the three-dimensional compressible Navier-Stokes equations in mass-averaged variables; one model utilizes the algebraic turbulent eddy viscosity model of Baldwin and Lomax (1978), while the other model employs the two-equation turbulence model of Jones and Launder (1972) coupled with the wall function model of Viegas and Rubesin (1985). The computed surface pressure, surface streamlines, pitot pressure, and yaw angle profiles are found to be in good agreement with experimental data. The three-dimensional velocity fields computed by both models are in close agreement, although the eddy viscosity profiles differ significantly within the three-dimensional interaction. This result indicates that the overall structure of this three-dimensional sharp fin interaction is insensitive to the turbulence model.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-0343
    Format: text
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  • 6
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    Comparison of analytical and experimental performance of a wind-tunnel diffuser section (1986)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Wind tunnel diffuser performance is evaluated by comparing experimental data with analytical results predicted by an one-dimensional integration procedure with skin friction coefficient, a two-dimensional interactive boundary layer procedure for analyzing conical diffusers, and a two-dimensional, integral, compressible laminar and turbulent boundary layer code. Pressure, temperature, and velocity data for a 3.25 deg equivalent cone half-angle diffuser (37.3 in., 94.742 cm outlet diameter) was obtained from the one-tenth scale Altitude Wind Tunnel modeling program at the NASA Lewis Research Center. The comparison is performed at Mach numbers of 0.162 (Re = 3.097x19(6)), 0.326 (Re = 6.2737x19(6)), and 0.363 (Re = 7.0129x10(6)). The Reynolds numbers are all based on an inlet diffuser diameter of 32.4 in., 82.296 cm, and reasonable quantitative agreement was obtained between the experimental data and computational codes.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88795 , E-3130 , NAS 1.15:88795 , Annual Conference of the National Technical Association; Jun 23, 1986 - Jun 28, 1986; Washington, DC; United States
    Format: application/pdf
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  • 7
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    Euler calculations for multielement airfoils using Cartesian grids (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 353-358
    Format: text
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  • 8
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    The response of airfoils to periodic disturbances - The unsteady Kutta condition (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Two cases of unsteady flowfields over a NACA 0012 airfoil at an angle of attack are examined. The first is the classical pitching motion about the airfoil's quarter chord. The second is the flow over a fixed airfoil immersed in the wake of the pitching airfoil. Large reduced frequencies are examined. Measurements were obtained in a water tunnel by laser Doppler velocimetry. Ensemble-averaged velocity measurements were obtained in the vicinity of the trailing edges of both the pitching and the fixed airfoil. The results indicate that the classical unsteady Kutta condition is clearly not valid. An extension of this condition earlier proposed by Giesing and Maskell is examined and some evidence is provided for its support.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0050 , AIAA Journal (ISSN 0001-1452); 24; 193-199
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  • 9
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    Experimental and numerical investigation of supersonic turbulent flow through a square duct (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1508-151
    Format: text
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  • 10
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    Identification of linearized equations of motion for the fixed wing configuration of the rotor systems research aircraft (1986)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The purpose of this report is to establish linear, decoupled models of rigid body motion for the fixed wing configuration of the Rotor Systems Research Aircraft (RSRA). Longitudinal and lateral control surface fixed linear models were created from aircraft time histories using current system identification techniques. Models were obtained from computer simulation at 160 KCAS and 200 KCAS, and from flight data at 160 KCAS. Comparisons were performed to examine modeling accuracy, variation of dynamics with airspeed and correlation of simulation and flight data results. The results showed that the longitudinal and lateral linear models accurately predicted RSRA dynamics. The flight data results showed that no significant handling qualities problems were present in the RSRA fixed wing aircraft at the flight speed tested.
    Keywords: AERODYNAMICS
    Type: NASA-CR-176977 , NAS 1.26:176977
    Format: application/pdf
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