A closed-form solution for the airfoil critical mach number (CROSBI ID 493034)
Prilog sa skupa u zborniku | izvorni znanstveni rad | međunarodna recenzija
Podaci o odgovornosti
Kesić, Petar ; Majić, Frane
engleski
A closed-form solution for the airfoil critical mach number
The airfoil critical Mach number is usually determined by equalizing the Prandtl-Glauert correction for the pressure coefficient and the isentropic critical pressure coefficient. The resulting equation is solved for the critical Mach number either graphically or numerically. In this paper the expression for the isentropic critical pressure coefficient is replaced with its binomial approximation. The resulting equation is transformed into a cubic equation. The cubic equation has been solved for the airfoil critical Mach number as a function of the pressure coefficient for the incompressible flow and the adiabatic coefficient k.The proposed solution is applicable not only to airflow but for other fluids including cryogenic gasses.
airfoil; critical Mach number; compressible and isentropic flow
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Podaci o prilogu
2004.
objavljeno
Podaci o matičnoj publikaciji
Proceedings of the 42-nd AIAA Ccience Meeting
2004
Reno (NV):
Podaci o skupu
42nd AIAA Aerospace Sciences Meeting and Exhibit
predavanje
05.01.2004-08.01.2004
Reno (NV), Sjedinjene Američke Države