
Accession Number : AD0476453
Title : SECONDORDER THEORY FOR AIRFOILS IN UNIFORM SHEAR FLOW.
Descriptive Note : Technical rept.,
Corporate Author : RUTGERS  THE STATE UNIV NEW BRUNSWICK NJ DEPT OF MECHANICAL INDUSTRIAL AND AEROSPACE ENGINEERING
Personal Author(s) : Chen, C. F.
Report Date : NOV 1965
Pagination or Media Count : 23
Abstract : The first and secondorder problems for a uniform shear flow past an airfoil have been formulated and solved. Expressions for the first and secondorder pressure coefficients have been obtained. The lift and moment coefficients are given in integral form. Once the airfoil shape is known, the force coefficients can be obtained by integration. Numerical calculations have been carried out to obtain lift coefficients on a symmetric Joukowsky airfoil, a circular arc, and a cambered Joukowsky airfoil for different values of stream vorticity. It is found that, in general, if the nondimensional stream vorticity (with respect to the airfoil chord and a reference velocity) is limited to one or less, the secondorder theory will give lift coefficients within 5% of the exact theory up to 30 deg angle of attack. The uniformly valid pressure distributions correct to the secondorder along a symmetric Joukowsky airfoil at 10 deg incidence are presented to exhibit the effect of stream shear. (Author)
Descriptors : *WAKE), (*AIRFOILS, SHEAR STRESSES, VORTICES, PRESSURE, DISTRIBUTION, MOMENTS, LIFT, AERODYNAMIC LOADING, CAMBER, ANGLE OF ATTACK, FLOW FIELDS, PERTURBATION THEORY, MATHEMATICAL ANALYSIS, SERIES(MATHEMATICS), FORCE(MECHANICS), EQUATIONS.
Subject Categories : Aircraft
Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE