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  • AERODYNAMICS  (11)
  • 1985-1989  (11)
  • 1945-1949
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  • 1
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    TRANDESNF: A computer program for transonic airfoil design and analysis in nonuniform flow (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The use of a transonic airfoil code for analysis, inverse design, and direct optimization of an airfoil immersed in propfan slipstream is described. A summary of the theoretical method, program capabilities, input format, output variables, and program execution are described. Input data of sample test cases and the corresponding output are given.
    Keywords: AERODYNAMICS
    Type: NASA-CR-4044 , NAS 1.26:4044 , KU-FRL-602-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Transonic analysis and design of axisymmetric bodies in nonuniform flow (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An inviscid nonuniform axisymmetric transonic code was developed for applications in analysis and design. Propfan slipstream effect on pressure distribution for a body with and without sting was investigated. Results show that nonuniformity causes pressure coefficient to be more negative and shock strength to be stronger and more rearward. Sting attached to a body reduced the pressure peak and moves the rear shock forward. Extent and Mach profile shapes of the nonuniformity region appeared to have little effect on the pressure distribution. Increasing nonuniformity magnitude made pressure coefficient more negative and moved the shock rearward. Design study was conducted with the CONMIN optimizer for an ellipsoid and a body with the NACA-0012 counter. For the ellipsoid, the general trend showed that to reduce the pressure drag, the front portion of the body should be thinner and the contour of the rear portion should be flatter than the ellipsoid. For the design of a body with a sharp trailing edge in transonic flow with an initial shape given by the NACA-0012 contour, the pressure drag was reduced by decreasing the nose radius and increasing the thickness in the aft portion. Drag reduction percentages are given.
    Keywords: AERODYNAMICS
    Type: NASA-CR-4101 , NAS 1.26:4101 , CRINC-FRL-602-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Calculation of aerodynamic characteristics of airplane configurations at high angles of attack (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Calculation of longitudinal and lateral directional aerodynamic characteristics of airplanes by the VORSTAB code is examined. The numerical predictions are based on the potential flow theory with corrections of high angle of attack phenomena; namely, vortex flow and boundary layer separation effects. To account for the vortex flow effect, vortex lift, vortex action point, augmented vortex lift and vortex breakdown effect through the method of suction analogy are included. The effect of boundary layer separation is obtained by matching the nonlinear section data with the three dimensional lift characteristics iteratively. Through correlation with results for nine fighter configurations, it is concluded that reasonably accurate prediction of longitudinal and static lateral directional aerodynamics can be obtained with the VORSTAB code up to an angle of attack at which wake interference and forebody vortex effect are not important. Possible reasons for discrepancy at higher angles of attack are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-CR-4182 , NAS 1.26:4182 , CRINC-FRL-730-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Calculation of symmetric and asymmetric vortex seperation on cones and tangent ogives based on discrete vortex models (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An inviscid discrete vortex model, with newly derived expressions for the tangential velocity imposed at the separation points, is used to investigate the symmetric and asymmetric vortex separation on cones and tangent ogives. The circumferential locations of separation are taken from experimental data. Based on a slender body theory, the resulting simultaneous nonlinear algebraic equations in a cross-flow plane are solved with Broyden's modified Newton-Raphson method. Total force coefficients are obtained through momentum principle with new expressions for nonconical flow. It is shown through the method of function deflation that multiple solutions exist at large enough angles of attack, even with symmetric separation points. These additional solutions are asymmetric in vortex separation and produce side force coefficients which agree well with data for cones and tangent ogives.
    Keywords: AERODYNAMICS
    Type: NASA-CR-4122 , NAS 1.26:4122 , CRINC-FRL-426-4
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    An experimental investigation of dynamic ground effect (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 60-degree delta wing, an F-106B, and an XB-70 model with and without flap deflections were tested in static and dynamic ground effect in the 36-by 51-inch subsonic wind tunnel at the University of Kansas. Dynamic ground effect was measured with movable sting support. For flow visualization, a tufted wire grid was mounted on the movable sting behind the model. Test results showed that lift and drag increments in dynamic ground effect were always lower than static values. Effect of the trailing edge flap deflections on lift increments was slight. The fuselage reduced the lift increments at a given ground height. From flow visualization under static conditions, the vortex core was seen to enlarge as the ground was approached.
    Keywords: AERODYNAMICS
    Type: NASA-CR-4105 , NAS 1.26:4105 , CRING-FRL-717-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Experimental investigation of dynamic ground effect (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: A 60-degree delta wing, an F-106B, and an XB-70 model with and without flap deflections were tested in static and dynamic ground effect in the 36-by-51-inch subsonic wind tunnel at the University of Kansas. Dynamic ground effect was measured with movable sting support. For flow visualization, a tufted wire grid was mounted on the movable sting behind the model. Test results showed that lift and drag increments in dynamic ground effect were always lower than static values. Effect of the trailing edge flap deflections on lift increments was slight. The fuselage reduced the lift increments at a given ground height. From flow visualization under static conditions, the vortex core was seen to enlarge as the ground was approached.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 497
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Calculation of aerodynamic characteristics at high angles of attack for airplane configurations (1987)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The primary objective is to determine how an airplane configuration should be modeled to predict both longitudinal and lateral aerodynamic characteristics at high angles of attack. A generic fighter model, an F-16 and an F-18 configuration with leading edge flap deflection and an F-106B configuration were investigated. Furthermore, the F-16XL and X-29 configurations were examined. Some calculated results are given.
    Keywords: AERODYNAMICS
    Type: NASA-CR-180678 , NAS 1.26:180678
    Format: application/pdf
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  • 8
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    An experimental investigation of dynamic ground effect (1986)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Experimental studies were conducted to determine the longitudinal force and moment aerodynamic coefficients for a 1/48 scale model of an F-106 aircraft and a 0.01 scale model of an XB-70-1 aircraft. The two airplanes and one 60 degree delta wing model were designed and fabricated to satisfy the specific test conditions of the Kansas University wind tunnel with a 3 by 4.3 test section. Results of the tests are given
    Keywords: AERODYNAMICS
    Type: NASA-CR-180305 , NAS 1.26:180305 , CRINC-FRL-717-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Calculation of asymmetric vortex separation on cones and tangent ogives based on a discrete vortex model (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: The boundary value problem for vortex separation at zero sideslip on cones and tangent ogives is set up by means of a discrete vortex model. The nonlinear algebraic equations for the boundary value problem admit multiple, physically feasible solutions, including the symmetric and asymmetric vortex solutions. Multiple solutions are proposed as an alternative explanation of the existence of asymmetric vortex separation at zero sideslip.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 27; 1824-182
    Format: text
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  • 10
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    Effect of a round airfoil nose on leading-edge suction (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Kulfan (1979) assumed that the angle of attack for initial vortex separation on a slender wing with rounded leading edges could be obtained by equating the leading-edge suction (LES) and nose drag coefficients. In the present study, this assumption is examined and is shown to predict reasonably well the initial angle of attack at which laminar separation occurs near the airfoil nose. However, the assumption is shown to be slightly less accurate for thick or cambered airfoils. Attainable LES estimated by Kulfan's method seemed to agree well with that obtained from an airfoil aerodynamics code and experimental data on a NACA 64A009 airfoil at M = 0.4 and Re = 0.86 x 10 to the 6th.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 472-474
    Format: text
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