Pressure Distribution and Flow Visualization Tests of a 1.5 Elliptic Cone at Mach 10
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Report Number: AEDC TDR 63-163
Author(s): Palko, R. L., Ray, A. D.
Corporate Author(s): ARO, Inc.
Date of Publication: 1963-08
Pages: 55
Contract: AF 40(600)-1000
DoD Project: 1366
DoD Task: 136607
Identifier: AD0414567
Abstract:
Results are presented for tests conducted on a 1.5 elliptic cone to determine the pressure distribution, flow streamlines, and shock wave shape at high angles of attack. The tests were performed at a Mach number of 10 and a freestream unit Reynolds number of 1.6 x 10 to the 6th power per foot. The angle-of-attack range was from 0 to 60 deg. The model was oriented both with the major and the minor axis of the ellipse located in the pitch plane.
Provenance: IIT
Author(s): Palko, R. L., Ray, A. D.
Corporate Author(s): ARO, Inc.
Date of Publication: 1963-08
Pages: 55
Contract: AF 40(600)-1000
DoD Project: 1366
DoD Task: 136607
Identifier: AD0414567
Abstract:
Results are presented for tests conducted on a 1.5 elliptic cone to determine the pressure distribution, flow streamlines, and shock wave shape at high angles of attack. The tests were performed at a Mach number of 10 and a freestream unit Reynolds number of 1.6 x 10 to the 6th power per foot. The angle-of-attack range was from 0 to 60 deg. The model was oriented both with the major and the minor axis of the ellipse located in the pitch plane.
Provenance: IIT