Theoretical development of the velocity potential equation for compressible flow and its various consequences has been presented. The geometrical interpretation of potential equation and conformal mapping technique are discussed where the mappings link the flow around a circular cylinder of a slender airfoil. The lift and drag coefficients are determined for the slender airfoils based on the Mach number and compressibility effects. The calculated lift coefficients show that with the increasing of attack angle it increases linearly and a higher lift coefficient is found for a smaller Mach number for any certain attack angle. Similarly, the drag profiles are determined which are exponentially decreased with the increasing of Mach number for any fixed attack angle. The calculated and experimental data on the lift and drag coefficients over the slender airfoil surface are compared and found in good agreement.
Hoque, Abrar; Rahman, Masudar; and Hoque, Ashabul
Theoretical Study of Mach number and Compressibility Effect on the Slender Airfoils,
Applications and Applied Mathematics: An International Journal (AAM), Vol. 16,
1, Article 30.
Available at: https://digitalcommons.pvamu.edu/aam/vol16/iss1/30