An Approximate Method For Calculating The Compressible Laminar Boundary Layer With Continuously Distributed Suction

An Approximate Method for Calculating the Compressible Laminar Boundary Layer with Continuously Distributed Suction

An approximate method for calculating the compressible laminar boundary layer with suction was developed. The method is applicable to arbitrary distributions of potential velocity and suction velocity on adiabatic walls at a Prandtl number of unity. With zero pressure gradient, it also holds in the case of heat tr nsfer at constant wall temperature. A comparison with known exact solutions is made, and extensive and systematic computations of the laminar compressible boundary layer with suction on aerfoil sections are performed. In the subsonic range the profile NACA 0010 and in the supersonic range a symmetric biconvex profile with a thickness ratio of 10% is taken at various Mach numbers and angles of incidence. A special study is made on the influence of the location and extent of the suction area on the position of the point of separation. It is shown that a given suction quantity is most efficient in delaying separation when located on the aft part of the profile. (Author).

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