A Panel Method to Determine Loads on Oscillating Airfoils in Transonic Flow with Embedded Shock Waves

摘要

A two dimensional panel method which combines supersonic and subsonic linear lifting surface theories is based on the velocity potential panel approach and accounts for the effect of the moving shock. A simplified representation of a mean steady symmetric flow field which is divided into a supersonic constant Mach number region separated by a straight normal shock is used. For a NACA 64A006 airfoil, transonic results are presented and compared with results of an improved version of the LTRAN2 code. A 95% saving in computer run time is realized.