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  • AERODYNAMICS  (4,079)
  • 1990-1994  (2,823)
  • 1970-1974  (1,256)
  • 1
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    Summary of in-flight flow visualization obtained from the NASA high alpha research vehicle (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A summary of the surface and off-surface flow visualization results obtained in flight on the F-18 high alpha research vehicle (HARV) is presented, highlighting the extensive 3-D vortical flow on the aircraft at angles of attack up to 50 degs. The emitted fluid technique, as well as tufts and flow cones, were used to document the surface flow. A smoke generator system injected smoke into the vortex cores generated by the forebody and leading edge extensions (LEXs). Documentation was provided by onboard still and video, by air-to-air, and by postflight photography. The surface flow visualization techniques revealed laminar separation bubbles near the forebody apex, lines of separation on the forebody and LEX, and regions of attached and separated flow on the wings and fins. The off-surface flow visualization techniques showed the path of the vortex cores on the forebody and LEX as well as the LEX vortex core breakdown location. An interaction between the forebody and LEX vortices was noted. The flow over the surfaces of the vertical tail was categorized into regions of attached, unsteady, or separated flow using flow tufts.
    Keywords: AERODYNAMICS
    Type: NASA-TM-101734 , H-1686 , NAS 1.15:101734 , High Angle of Attack Technology Symposium; Oct 30, 1990 - Nov 01, 1990; Hampton, VA; United States
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  • 2
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    Enhancements to viscous-shock-layer technique (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 30; 4; p. 404-413.
    Format: text
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  • 3
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    A viscous shock-layer analysis of 2-D and axisymmetric flows (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Results are obtained for cylindrical leading edges of proposed transatmospheric vehicles by employing a 2D viscous shock-layer code for nonequilibrium and perfect gas flows. The accuracy and efficiency of the planar code is verified through detailed comparisons with other predictions. It is found to be as accurate and robust as its axisymmetric counterpart. This study includes results for nose radii ranging from 0.01 to 2.0 ft and half-angles of 5 and 6 deg for both cylindrically-blunted wedges and spherically blunted cones (included for comparison). Some results are presented as a ratio of the noncatalytic to the corresponding fully catalytic heating value to illustrate the maximum potential for a heating reduction in dissociated nonequilibrium flows. This ratio and the individual heating rates are smaller for cylindrically-blunted wedges with small nose radii, relative to the spherically-blunted cones (at the same radius). Therefore, a larger potential exists for heating reduction in cylindrically-blunted as compared with the spherically-blunted surfaces for finite-rate chemistry.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-2751 , AIAA, Thermophysics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States|; 14 p.
    Format: text
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  • 4
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    Surface pressure and streamline effects on laminar heating calculations (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 27; 9-14
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  • 5
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    Hypersonic nonequilibrium viscous solutions over slender bodies (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: An extension is undertaken of a previous numerical study in order to improve current understanding of nonequilibrium flow effects over slender bodies. Upon extension of the parametric study to encompass smaller nose radii, the downstream influence of equilibrium nonequilibrium flow is found to be much smaller than for the larger nose radii. A comparison of individual stagnation nonequilibrium heating rates demonstrates that a relative comparison of the ratios was not indicative of the actual heating reduction.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 28; 358-360
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  • 6
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    Flowfield and vehicle parameter influence on hypersonic heat transfer and drag (1990)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 27; 361-368
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  • 7
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    Effect of nose shape on three-dimensional stagnation region streamlines and heating rates (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new method for calculating the three-dimensional inviscid surface streamlines and streamline metrics using Cartesian coordinates and time as the independent variable of integration has been developed. The technique calculates the streamline from a specified point on the body to a point near the stagnation point by using a prescribed pressure distribution in the Euler equations. The differential equations, which are singular at the stagnation point, are of the two point boundary value problem type. Laminar heating rates are calculated using the axisymmetric analog concept for three-dimensional boundary layers and approximate solutions to the axisymmetric boundary layer equations. Results for elliptic conic forebody geometries show that location of the point of maximum heating depends on the type of conic in the plane of symmetry and the angle of attack, and that this location is in general different from the stagnation point. The new method was found to give smooth predictions of heat transfer in the nose region where previous methods gave oscillatory results.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-5032
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  • 8
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    Effect of nose shape on three-dimensional streamlines and heating rates (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 30; 1; p. 69-78.
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  • 9
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    Surface flow patterns on an ogive-cylinder at incidence (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: A set of photographs has been obtained which documents the oil-imaged surface flow patterns of an ogive-cylinder at angles-of-attack between 30 and 85 deg, and Reynolds number of 26,000. Attention is given to the possibility that the bistable nature of the flow within the 50-65 deg angle-of-attack range is linked to the coincident appearance of foci in the surface flow patterns, in view of the suggestion that these foci act as the anchor points allowing the forebody vortical structures to roll up and form the forebody's trailing vortex system.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 272-274
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  • 10
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    A review of near-wall Reynolds-stress (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The advances made in second-order near-wall turbulence closures are summarized. All closures examined are based on some form of high Reynolds number models for the Reynolds stress and the turbulent kinetic energy dissipation rate equations. Consequently, most near-wall closures proposed to data attempt to modify the high Reynolds number models for the dissipation rate equation so that the resultant models are applicable all the way to the wall. The near-wall closures are examined for their asymptotic behavior so that they can be compared with the proper near-wall behavior of the exact equations. A comparison of the closure's performance in the calculation of a low Reynolds number plane channel flow is carried out. In addition, the closures are evaluated for their ability to predict the turbulence statistics and the limiting behavior of the structure parameters compared to direct simulation data.
    Keywords: AERODYNAMICS
    Type: NASA-CR-4369 , NAS 1.26:4369
    Format: application/pdf
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