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  • 1
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    Experimental Investigation of the Application of Microramp Flow Control to an Oblique Shock Interaction (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effectiveness of microramp flow control devices in controlling an oblique shock interaction was tested in the 15- by 15-Centimeter Supersonic Wind Tunnel at NASA Glenn Research Center. Fifteen microramp geometries were tested varying the height, chord length, and spacing between ramps. Measurements of the boundary layer properties downstream of the shock reflection were analyzed using design of experiments methods. Results from main effects, D-optimal, full factorial, and central composite designs were compared. The designs provided consistent results for a single variable optimization.
    Keywords: Aerodynamics
    Type: NASA/TM-2009-215630 , AIAA Paper 2009-919 , E-16942 , 47th Aerospace Sciences Meeting; Jan 05, 2009 - Jan 08, 2009; Orlando, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    CFD Results for an Axisymmetric Isentropic Relaxed Compression Inlet (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The OVERFLOW code was used to calculate the flow field for a family of five relaxed compression inlets, which were part of a screening study to determine a configuration most suited to the application of microscale flow control technology as a replacement for bleed. Comparisons are made to experimental data collected for each of the inlets in the 1- by 1-Foot Supersonic Wind Tunnel at the NASA Glenn Research Center (GRC) to help determine the suitability of computational fluid dynamics (CFD) as a tool for future studies of these inlets with flow control devices. Effects on the wind tunnel results of the struts present in a high subsonic flow region accounted for most of the inconsistency between the results. Based on the level of agreement in the present study, it is expected that CFD can be used as a tool to aid in the design of a study of this class of inlets with flow control.
    Keywords: Aerodynamics
    Type: NASA/TM-2008-215416 , AIAA Paper-2008-0092 , E-16580 , 46th AIAA Aerospace Sciences Meeting; Jan 07, 2008 - Jan 10, 2008; Reno, NV; United States
    Format: application/pdf
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