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Sketch the CL versus angle-of-attack (a) for a symmetric airfoil, for the three freestream Mach numbers of 0.1, 0.5 and 0.7. This airfoil stalls
Sketch the CL versus angle-of-attack (a) for a symmetric airfoil, for the three freestream Mach numbers of 0.1, 0.5 and 0.7. This airfoil stalls (peak C) at 15-deg and has a CLmax = 2.0 at incompressible flow velocity. Be as quantitative as possible with the comparison of the slope of the curves. Label the stall angles (qualitative is okay) and CLmax (quantitative) with increasing Mach numbers.
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Vector Mechanics For Engineers Statics
Authors: R.C.Hibbeler
7th Edition
978-0072931105, 0072931108
