Experimental verification of the osculating cones method for two waverider forebodies at Mach 4 and 6 | Zendy

Rachel A. Miller | Zendy; Brian Argrow | Zendy; Kenneth Center | Zendy; Gregory J. Brauckmann | Zendy; Mattew Rhode | Zendy

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Experimental verification of the osculating cones method for two waverider forebodies at Mach 4 and 6

Author(s) -

Rachel A. Miller,

Brian Argrow,

Kenneth Center,

Gregory J. Brauckmann,

Mattew Rhode

Publication year - 1998

Publication title -

45th aiaa aerospace sciences meeting and exhibit

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.1998-682

Subject(s) - osculating circle , mach number , computer science , aerospace engineering , mechanics , physics , mathematics , geometry , engineering

The NASA Langley Research Center Unitary Plan Wind Tunnel and the 20-Inch Mach 6 Tunnel were used to test two osculating cones waverider models. The Mach-4 and Mach-6 shapes were generated using the interactive design tool WIPAR. WIPAR performance predictions are compared to the experimental results. Vapor screen results for the Mach-4 model at the on- design Mach number provide visual verification that the shock is attached along the entire leading edge, within the limits of observation. WIPAR predictions of pressure distributions and aerodynamic coefficients show general agreement with the corresponding experimental values.

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