Publisher: Cambridge University Press
E-ISSN: 2059-6464|117|1192|639-646
ISSN: 0001-9240
Source: The Aeronautical Journal, Vol.117, Iss.1192, 2013-06, pp. : 639-646
Disclaimer: Any content in publications that violate the sovereignty, the constitution or regulations of the PRC is not accepted or approved by CNPIEC.
Abstract
The present paper presents oil flow visualisations and pressure measurements over a hemisphere-cylinder body attached with a forward facing spike at Mach 6 and Reynolds number of 1·38 × 108 at 0° and 5° angle-of-attack. The oil flow pictures depict the separation region in the vicinity of the spike on the hemisphere-cylinder body. The oil flow visualisations will help to locate the reattachment shock wave on the hemisphere-cylinder body and also understand the flow field behavior on the blunt-nosed spike configuration. The pressure measurements over the hemisphere-cylinder body depend on the shape and the length of the spike. The pressure distributions over the blunt-nosed body show significant influence of the angle-of-attack. The maximum pressure coefficient on the hemisphere-cylinder body is a function of the spike length, shape of the aerodisk and angle-of-attack. The windward and leeward sides pressure variations show dependence of the geometrical parameters of the spike and shape of the spike. The hemisphere and the flat-faced aerodisk cause considerable reduction of pressure leading to decrease of aerodynamic drag compared to the conical spike.
Related content
By Ansari A.B. Nassab S.A. Gandjalikhan
International Journal of Numerical Methods for Heat & Fluid Flow, Vol. 23, Iss. 2, 2013-03 ,pp. :
By Zhao Jianjun Zhang Hongyan Zhang Zhengxiang Guo Xiaoyi Li Xuedong Chen Chun
Remote Sensing, Vol. 7, Iss. 8, 2015-08 ,pp. :
Steady and unsteady pressure measurements on a swept-wing aircraft
The Aeronautical Journal, Vol. 118, Iss. 1200, 2014-02 ,pp. :
International Journal of Numerical Methods for Heat & Fluid Flow, Vol. 25, Iss. 4, 2015-05 ,pp. :