|
|||||
|
|
Hypersonic flow over a multi-step afterbody |
|
| Authors: | V Menezes S Kumar K Maruta K P J Reddy K Takayama |
| Institution: | (1) Interdisciplinary Shock Wave Research Center, TUBERO, Tohoku University, Sendai 980-8577, Japan;(2) Institute of Fluid Science, Tohoku University, Sendai 980-8577, Japan;(3) Department of Aerospace Engineering, Indian Institute of Science, Bangalore, 560-012, India |
| Abstract: | Effect of a multi-step base on the total drag of a missile shaped body was studied in a shock tunnel at a hypersonic Mach number of 5.75. Total drag over the body was measured using a single component accelerometer force balance. Experimental results indicated a reduction of 8% in total drag over the body with a multi-step base in comparison with the base-line (model with a flat base) configuration.The flow fields around the above bodies were simulated using a 2-D axisymmetric Navier–Stokes solver and the simulated results on total drag were compared with the measured results. The simulated flow field pictures give an insight into the involved flow physics. Communicated by K. Takayama PACS 47.40.Ki |
| Keywords: | Drag measurement Stepped afterbody Accelerometer balance Hypersonic |
| 本文献已被 SpringerLink 等数据库收录！ | |