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  • 1
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    A low speed wind tunnel investigation of Reynolds number effects on a 60-deg swept wing configuration with leading and trailing edge flaps (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A low-speed wind tunnel test was performed to investigate Reynolds number effects on the aerodynamic characteristics of a supersonic cruise wing concept model with a 60-deg swept wing incorporating leading-edge and trailing-edge flap deflections. The Reynolds number ranged from 0.3 to 1.6 x 10 to the 6th, and corresponding Mach numbers from .05 to 0.3. The objective was to define a threshold Reynolds number above which the flap aerodynamics basically remained unchanged, and also to generate a data base useful for validating theoretical predictions for the Reynolds number effects on flap performance. This report documents the test procedures used and the basic data acquired in the investigation.
    Keywords: AERODYNAMICS
    Type: NASA-CR-181684 , NAS 1.26:181684
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A formulation for the boundary-layer equations in general coordinates (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This is a working paper in which a formulation is given for solving the boundary-layer equations in general body-fitted curvilinear coordinates while retaining the original Cartesian dependent variables. The solution procedure does not require that any of the coordinates be orthogonal, and much of the software developed for many Navier-Stokes schemes can be readily used. A limited number of calculations has been undertaken to validate the approach.
    Keywords: AERODYNAMICS
    Type: NASA-TM-100079 , A-88114 , NAS 1.15:100079
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Application of a semianalytical technique for sensitivity analysis of unsteady aerodynamic computations (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: A semianalytical approach is developed for the sensitivity analysis of linear unsteady aerodynamic loads. The semianalytical approach is easier to implement than the analytical approach. It is also computationally less expensive than the finite difference approach when used with panel methods which require a large number of panels. The semianalytical approach is applied to an isolated airfoil in a two-dimensional flow and rotating propfan blades in three-dimensional flow. Sensitivity coefficients with respect to nonshape-dependent variables are shown for some cases.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-2377 , Structures, Structural Dynamics and Materials Conference; Apr 18, 1988 - Apr 20, 1988; Williamsburg, VA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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