A Mach Number and Dynamic Pressure Computer for Analog Reduction of Wind Tunnel Data

Abstract

This paper describes the development of a special servo computer for wind tunnel applications to provide analog computations and indications of Mach number and dynamic pressure. Division of up to six aerodynamic variables by the dynamic pressure can also be performed. The computer uses simplified techniques as compared to usual analog computer practices which are allowable because of the special application. Multiple ranges of Mach number and dynamic pressure are used to obtain improved accuracy. The system can be used, with minor modifications, by most wind tunnel facilities. The basic techniques could also be used for an accurate air data computer for aircraft applications.