9 research outputs found
On the second-order tunnel-wall-constriction corrections in two-dimensional compressible flow
A method for determining the aerodynamic characteristics of two-and three-dimensional shapes at hypersonic speeds
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NACA Technical Notes
The results of calculations of the viscous and pressure drags of some two-dimensional supersonic airfoils at zero lift are presented. The results indicate that inclusion of viscous drag alters many previous results regarding the desirability of certain airfoil shapes for securing low drags at supersonic speeds. At certain Reynolds and Mach numbers, for instance, a circular-arc airfoil may theoretically have less drag than the previously advocated symmetrical wedge-shape profile; although under different conditions, the circular-arc airfoil may have a higher drag
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NACA Technical Notes
From Summary: "Solutions of the first- and second-order Prandtl-Busemann iteration equations are obtained for the flow past thin, sharp-nose, symmetric, two-dimensional bodies in closed channels. With the use of these solutions an expression is derived from the tunnel-wall interference. The tunnel-wall correction for a parabolic-arc airfoil is calculated to indicate the effects of compressibility, ratio of the tunnel height to the airfoil chord, and airfoil thickness coefficient.
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NACA Research Memorandums
Report presenting an investigation of two 10-foot-diameter three-blade propellers to determine the effect of swept-back blade tips on propeller aerodynamic characteristics. Results regarding the effect of swept-back tips on maximum efficiency and constant-power propeller operation are provided
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NACA Technical Notes
Report presenting a method for calculating the pressures on aerodynamic shapes at very high supersonic speeds in dense air with the ratio of specific heats equal to 1. It is applicable to any body of revolution at zero angle of attack and to any two-dimensional profile. Some aerodynamic characteristics of several shapes are calculated, and lift and drag coefficients are shown to be dependent on thickness ratio, thickness distribution, and angle of attack