
Accession Number : AD0746505
Title : Calculation of the Lift on Airfoils with Separated Boundary Layers,
Corporate Author : WEST VIRGINIA UNIV MORGANTOWN DEPT OF AEROSPACE ENGINEERING
Personal Author(s) : Ness,Nathan ; Gibbs,Edward H. ; Tseng,WenAn Peter
Report Date : MAY 1972
Pagination or Media Count : 108
Abstract : The report contains a method for calculating the sectional lift coefficient Cl as a function of its angle of attack alpha and free stream Reynolds number Re even at large angles of attack beyond the maximum Cl. The results of the present theory are in agreement with all known experimental data, that is, (1) the theory shows that Cl increases with alpha until stall and then decreases as alpha is increased still further (keeping Re constant), (2) the theory shows that the Reynolds number effect on Cl versus alpha is insignificant at the lower angles of attack but becomes more pronounced near and beyond the stall where viscous effects and flow separation are more important, (3) the theory shows that Cl increases with Re at constant (high) values of alpha. (Author)
Descriptors : (*AERODYNAMIC CONTROL SURFACES, LIFT), BOUNDARY LAYER, FLOW SEPARATION, ANGLE OF ATTACK, MATHEMATICAL MODELS, EXPERIMENTAL DATA, CORRELATION TECHNIQUES, AIRFOILS, COMPUTER PROGRAMS, STALLING, REYNOLDS NUMBER, THESES
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE