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Naca 4412 airfoil2/13/2023 ![]() ![]() Pressure Distribution (Pressure Ported Airfoil) Relates lift and drag forces to the velocity X Chord line Chord x=0 Leading edge x=c Trailing edge Max thickness Max camber Mean camber line ObjectiveStudy the lift and drag forces on a NACA 4412 airfoil Resolve discrepancy in wind tunnel data Develop experimental techniques for an airfoil Compare wind tunnel dataForce Balance to Pressure Distribution Baylor data to published NACA dataĤ digit code used to describe airfoil shapes 1st digit - maximum camber in percent chord 2nd digit - location of maximum camber along chord line (from leading edge) in tenths of chord 3rd and 4th digits - maximum thickness in percent chord NACA 4412 with a chord of 6 Max camber: 0.24 (4% x 6) Location of max camber: 2.4 aft of leading edge (0.4 x 6) Max thickness: 0.72 (12% x 6) OverviewObjective Theory Apparatus Experimental Comparison Results Summary Recommendations Van Treuren Scholars Day January 26, 2007 Aerodynamic Characteristics of a NACA 4412 Airfoil ![]()
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