Accession Number : AD0476453

Title :   SECOND-ORDER 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 second-order problems for a uniform shear flow past an airfoil have been formulated and solved. Expressions for the first and second-order 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 second-order 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 second-order 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