A Comparison of the Potential and the Euler Formulations of the Equations of Motion for Transonic Flow (Classic Reprint) - Hardcover
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Excerpt from A Comparison of the Potential and the Euler Formulations of the Equations of Motion for Transonic Flow
It is well known that the most efficient cruising speed of modern commercial aircraft lies in a range of free stream Mach numbers M0° near 7, where the fluid flow past the body may be characterized as transonic or supercritical. The flight efficiency is measured by the dimensionless parameter Moo CL C D, where C L and C D are the coefficients of lift and drag, respectively. In this range of Mach numbers a region of supersonic flow forms above the wing, which is terminated by a shock wave across which the pressure, density, and velocity of the fluid change rapidly. A rapid rise in the drag due to these shock waves, which reduces the overall flight efficiency, occurs in the transonic range. The goal of the aeronautical engineer is to design supercritical airfoils that will postpone the onset of strong shocks until a higher cruising speed can be attained.
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A Comparison of the Potential and the Euler Formulations of the Equations of Motion for Transonic Flow Classic Reprint
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A Comparison of the Potential and the Euler Formulations of the Equations of Motion for Transonic Flow Classic Reprint
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