Üsaavlabs Technical Report 65-41 a Comparison of the Theoretical Determination of the Development of the Boundary Layer Momentum Thickness in an Arbitrary Pressure Gradient with Full-scale Flight Experiments on a Porous Airfoil Section with Transpiration
نویسنده
چکیده
Calculation of the turbulent boundary layer momentum thickness around a NACA 4416 airfoil section has been made by a successive approximation method developed by one of the authors for two-dimensional I and axisymmetric flows. These results are compared with experimental results obtained from flight tests with a sailplane--Schweizer TG-3— | with reasonable results. I
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