Experimental Investigation of the Application of Microramp Flow Control to an Oblique Shock Interaction

By: Administration (Nasa), National Aeronaut

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. Hirt, Stefanie M. and Anderson, Bernhard H. Glenn Research Center NASA/TM-2009-215630, AIAA Paper 2009-919, E-16942 WBS 984754.02.07.03.13.02 OBLIQUE SHOCK WAVES; BOUNDARY LAYERS; SHOCK WAVE INTERACTION; EXPERIMENT DESIGN; FACTORIAL DESIGN; SUPERSONIC WIND TUNNELS; SPACING

• Format: Paperback
• Language: English
• ISBN: B08F6CG87D
• ISBN13: 9798672363851
• Release Date: January 1
• Publisher: Independently Published
• Length: 34 Pages
• Weight: 0.23 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"