Affiliation of Author(s):航空学院
Journal:Kung Cheng Je Wu Li Hsueh Pao
Abstract:There is a shock wave in the supercritical airfoil when the inflow velocity is faster than the critical Mach number, which leads to the wave drag increase rapidly. In order to reduce the wave drag for different flow fields, the shock control bump are studied in this thesis. An optimization platform was developed consisting of a genetic algorithm optimiser, a NURBS curve module and a CFD simulation module and the different flow states were optimized by using this platform. A calculation for RAE2822 airfoil has been done, and the computation results demonstrate that the optimized bump configuration can reduce the wave drag of the airfoil greatly and improve the performance for off-design conditions. To overcome the problem of narrow effective regions of significant drag reduction for one-point designed bumps, a design of two-dimensional adaptive bump based on shape memory alloy is proposed. Shock wave in different flow condition can be controlled through adjusting the appearance of SMA bump by temperate. © 2017, Science Press. All right reserved.
ISSN No.:0253-231X
Translation or Not:no
Date of Publication:2017-09-01
Co-author:聂瑞,jihongli,赵玲,zl
Correspondence Author:聂瑞,裘进浩,Jinhao Qiu