Volume Title |
Aerodynamics
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Volume No |
AEROFOILS AND WINGS - Aerofoils at supersonic speeds. Critical Mach number and pressure coefficient. Flat plates.
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DATA Title |
Estimation of critical Mach number for an aerofoil from its low-speed pressure distribution. |
DATA Item |
74008 |
KEYWORD |
aerofoil, critical, distribution, mach, number, pressure, airfoil |
ISBN |
0 85679 061 3 |
ABSTRACT |
ESDU 74008 gives curves (for inviscid incompressible flow) of critical Mach number at a point on the aerofoil surface plotted against the local pressure coefficient and the surface slope at that point. The method is based on first-order calculations but is also equivalent to second-order. If an exact method is used to calculate the pressure coefficient, a method is suggested of using ESDU 74008 to provide a comparable accuracy for the predicted critical Mach number.
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