A Method for Obtaining Shockless Transonic Flows past Airfoils, Partially Modified from a Given Arbitrary Airfoil

摘要

A method for obtaining shockless transonic flows past two dimensional airfoils is described. The methods of calculations of transonic flows are roughly classified into two groups: the direct method, which yields the transonic flows past given arbitrary airfoils; and the inverse method, which determines shapes of airfoils. In the former method, the shock waves normally exist in the region of transonic flows, and some numerical methods are already known. In the latter, transonic flows with given pressure distribution are calculated, and several analytical methods also exist. The method described is a combination of the direct method yield, the shockless transonic flows past airfoils which are partially modified from a given arbitrary airfoil. If one puts an arbitrary airfoil into a region of free stream flows with a comparatively large free stream Mach number, the shock waves generally exist.