Numerical and Experimental Investigations of Disturbed Pressures in the Vicinity of a Tandem Wing Configuration

Abstract

This paper presents the results of numerical calculations and experiments in the form of distributions of disturbed pressures generated by the tandem configuration of a schematized model of a supersonic passenger airplane on the control surface in the disturbed region. The numerical solution of the problem on the flow over a geometrical model was carried out and the necessary measurements were made in experiments at a Mach number of the free stream M = 2.03 and an angle of attack α = 3.5o. It has been shown that the pressure distribution over the azimuth coordinate has a spatial character. Comparison of numerical calculations with the results of the experiment has shown their good agreement in the part of the profile where shock waves from the nose and from the forward and the rear wings are present. Because of the design features of the model–holder coupling, the trailing shock wave and the wake were not modeled in the experiment.