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:

1969-10-01

Pagination or Media Count:

56.0

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