This quiz covers: Prandtl glauert compressibility, supercritical airfoil and supersonic airfoils application. Subsonic compressible flow over airfoils is an inviscid, compressible, and irrotational flow. This means that there is no mechanism to rotate the fluid elements. Potential flow solutions in two and three dimensions can provide accurate results for aerofoil and wing analysis if the flow Mach number is less than 0.4. In this low subsonic region, the flow is incompressible so that no density variations need to be considered in the governing equations. Compressibility strengthens the... Show more This quiz covers: Prandtl glauert compressibility, supercritical airfoil and supersonic airfoils application. Subsonic compressible flow over airfoils is an inviscid, compressible, and irrotational flow. This means that there is no mechanism to rotate the fluid elements. Potential flow solutions in two and three dimensions can provide accurate results for aerofoil and wing analysis if the flow Mach number is less than 0.4. In this low subsonic region, the flow is incompressible so that no density variations need to be considered in the governing equations. Compressibility strengthens the disturbance of the flow introduced by the airfoil. However, in subsonic flow, compressibility does not give rise to additional aerodynamic drag. Show less
This quiz covers: Prandtl glauert compressibility, supercritical airfoil and supersonic airfoils application.
Subsonic compressible flow over airfoils is an inviscid, compressible, and irrotational flow. This means that there is no mechanism to rotate the fluid elements.
Potential flow solutions in two and three dimensions can provide accurate results for aerofoil and wing analysis if the flow Mach number is less than 0.4. In this low subsonic region, the flow is incompressible so that no density variations need to be considered in the governing equations. Compressibility strengthens the disturbance of the flow introduced by the airfoil. However, in subsonic flow, compressibility does not give rise to additional aerodynamic drag.
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