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Hypersonic Flow over a Yawed Circular Cone

Tracy, Richard R. (1963) Hypersonic Flow over a Yawed Circular Cone. Hypersonic Research Project Memorandum, 69. California Institute of Technology , Pasadena, CA. (Unpublished) https://resolver.caltech.edu/CaltechAUTHORS:20151105-162933285

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Abstract

A 10° semi-apex, circular cone is tested in air at Mach 8 and at 0 yaw angles to 24°; surface pressure, heat transfer, and pitot-pressure throughout the flow field are presented. The nominal surface temperature is 40" of the free stream stagnation temperature, and the Reynolds nunber, based on cone generator length, is varied from 0.5 x 10^5 to 4.2 x 10^5 . Heat transfer is measured at higher surface temperature ratios (up to 56%) and Reynolds nunbers (up to 7.3 x 10^5) by reducing the free stream stagnation temperature. All raw data consist of continuous circumferential distributions of each quantity and are included in a supplement. The surface pressure data are compared with the theories of Stone-Kopal and Cheng; Reshotko's theory of heat transfer to the windward generator is compared with experiment. The probe data delineate the boundary between viscous and inviscid flow and determine the shape of the outer shock wave as well as the secondary shocks which appear in the flow field at large yaw. The probe data are sufficient to determine the flow field in the plane of symmetry and permit an approximate representation of the Mach number profiles of the separated viscous flow in the leeward meridian plane beyond a moderate yaw angle.


Item Type:Report or Paper (Technical Report)
Additional Information:Contract No. DA-31-124-ARO(D)-33 U.S. Army Research Office and the Advanced Research Projects Agency. This research is a part of Project DEFENDER sponsored by the Advanced Research Projects Agency. Beyond the appreciation due to those of the GALCIT faculty and staff whose continuing effort underlies every research project, and the U. S. taxpayers, through whose generosity and wisdom a portion of this research was underwritten by the Hypersonic Research Project sponsored by the U. S. Army Research Office and the Advanced Research Projects Agency, the author is particularly grateful to: Lockheed Aircraft Corporation who, through the Lockheed Leadership Foundation, contributed financially to the author's graduate studies...
Group:Hypersonic Research Project
Funders:
Funding AgencyGrant Number
Army Research Office (ARO)DA-31-124-ARO(D)-33
Advanced Research Projects Agency (ARPA)UNSPECIFIED
Lockheed Aircraft CorporationUNSPECIFIED
Series Name:Hypersonic Research Project Memorandum
Issue or Number:69
Record Number:CaltechAUTHORS:20151105-162933285
Persistent URL:https://resolver.caltech.edu/CaltechAUTHORS:20151105-162933285
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:61918
Collection:CaltechAUTHORS
Deposited By: Kristin Buxton
Deposited On:06 Nov 2015 19:55
Last Modified:03 Oct 2019 09:13

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