Investigation of the Boundary Condition at a Wind Tunnel Test Section Wall for a Lifting Wing Body Model at Low Supersonic Speed. Phase 1. Test Preparations, Revision of Computer Program and Exploratory Computations.

摘要

The purpose of this investigation is to study experimentally and theoretically the flow field at locations around a lifting wing-body model, where wind-tunnel walls are normally situated. During Phase 1, which this report covers, the preparations for the experimental investigation have been carried out. The delta-wing-body model, the sting and support arrangement, a balance and a miniature flow inclination probe have been designed and manufactured. For the theoretical calculations a relaxation method based on the transonic small perturbation equation has been used. The computer program has been revised for supersonic free stream Mach numbers. The pressure and flow deflection angle have been calculated in the field near the wing-body configuration at Mach number 1.2 and at incidences of 0 deg and 5 deg. (Author)