Accession Number : AD0701771

Title :   LEADING EDGE SEPARATION ON AN AIRFOIL DURING DYNAMIC STALL.

Descriptive Note : Final rept.,

Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE AEROELASTIC AND STRUCTURES RESEARCH LAB

Personal Author(s) : Patay,Stephen A.

Report Date : OCT 1969

Pagination or Media Count : 56

Abstract : To obtain a better understanding of the leading edge separation mechanism on a wing pitching upward with a constant angular velocity, an unsteady boundary layer calculation is performed. The analysis considers a potential flow about a Joukowsky airfoil, which then forms a basis for the boundary layer calculations. An integral technique which is similar to the Karman-Pohlhausen method is used to determine the viscous flow. The movement of the separation point is calculated for several pitching rates. A comparison with some experimental data was made for both the static and dynamic case. It was determined that the point of boundary layer separation coincides with the formation of a separation bubble for the dynamic cases considered. (Author)

Descriptors :   (*AIRFOILS, *STALLING), (*FLOW SEPARATION, STALLING), LEADING EDGES, HELICOPTER ROTORS, BOUNDARY LAYER, PITCH(MOTION), POTENTIAL THEORY

Subject Categories : Aerodynamics
      Helicopters
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE