INTRODUCTION This Item provides a means of estimating a number of aerodynamic characteristics for a wide range of aerofoils in compressible inviscid airflow from a knowledge only of the thickness and camber line parameters shown in Sections 2.3 and 2.4. It is stressed that the data given herein apply only to non-viscous flow and that in a real (viscous) flow the effects of viscosity must be taken into account*. These effects can be large at all Mach numbers@ and increasingly so near the critical value where@ for example@ reductions of 25 per cent or more in lift coefficient are possible at wind-tunnel Reynolds numbers. The particular aerodynamic characteristics considered are lift-curve slope at zero lift@ a1@ zero-lift incidence@a0 @ zero-lift pitching moment coefficient@Cm0@ and chordwise position of the aerodynamic centre@ xa/c. The geometrical parameters (see Sections 2.3 and 2.4) required to obtain estimates for the aforementioned characteristics from this Item are given below@ together with the numbers of the relevant Figures to be used. * See Item Nos 97020 (Reference 13) and 98011 (Reference 14).
ESDU 72024 C-1986 history
1986ESDU 72024 C-1986 AERODYNAMIC CHARACTERISTICS OF AEROFOILS IN COMPRESSIBLE INVISCID AIRFLOW AT SUBCRITICAL MACH NUMBERS