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
MISSISSIPPI STATE UNIV MISSISSIPPI STATE DEPT OF AEROPHYSICS
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Calculation of the turbulent boundary layer momentum thickness around a NACA 4416 airfoil section was made by a successive approximation method developed for two-dimensional and axisymmetric flows. These results are compared with experimental results obtained from flight tests with a sailplane--Schweizer TG-3--with reasonable results.