Computational analysis of laminar boundary layer separation on a slender cone at angle of attack

Joseph Stecher, Graham V Candler

Research output: Contribution to conferencePaper

Abstract

In this paper we compare the experimental results of a Mach 14.2 flow over a series of blunt cones at angle of attack with computational results of the same flow over the same cone. The experimental results come from a 1971 test by Stetson at the Aerospace Research Laboratories. The computational analysis was done with the Data Parallel Line Relaxation method. Surface pressure results on the leeward side of the cone, Pitot pressure surveys and surface streamlines all agreed with the experimental results. The computations under-predict the surface pressures on the wind side and in regions of strong cross flow for all cases. The source of this difference is unknown; several potential explanations are offered.

Original languageEnglish (US)
Pages7263-7273
Number of pages11
StatePublished - Dec 1 2005
Event43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: Jan 10 2005Jan 13 2005

Conference

Conference43rd AIAA Aerospace Sciences Meeting and Exhibit
CountryUnited States
CityReno, NV
Period1/10/051/13/05

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    Stecher, J., & Candler, G. V. (2005). Computational analysis of laminar boundary layer separation on a slender cone at angle of attack. 7263-7273. Paper presented at 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States.