Unsteady Pressure and Boundary Layers on an 0012 Airfoil Caused by Aerodynamic Interference

Aerodynamic characteristics have been measured for a NACA 0012 airfoil in a non-uniform unsteady flow field. Test parameters studied included reduced frequencies based on semichord of 0 to 6.4 Reynolds number of 700,000 to 1,450,000, and airfoil angles of attack of 0 to 15deg. Quantities measured we...

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Bibliographic Details
Main Authors: Covert, Eugene E, Lorber, Peter F
Format: Report
Language:English
Subjects:
AERODYNAMIC CHARACTERISTICS
AERODYNAMIC FORCES
AIRFOILS
ANGLE OF ATTACK
BOUNDARY LAYER
DYNAMICS
FLOW FIELDS
FLOW SEPARATION
Fluid Mechanics
INTERFERENCE
NONUNIFORM FLOW
PE61102F
PRESSURE DISTRIBUTION
REYNOLDS NUMBER
STALLING
TURBULENT BOUNDARY LAYER
UNSTEADY FLOW
WIND TUNNEL TESTS
WUAFOSR2307A2
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Summary:Aerodynamic characteristics have been measured for a NACA 0012 airfoil in a non-uniform unsteady flow field. Test parameters studied included reduced frequencies based on semichord of 0 to 6.4 Reynolds number of 700,000 to 1,450,000, and airfoil angles of attack of 0 to 15deg. Quantities measured were upwash velocity fields, turbulent boundary layer velocities and Reynolds stresses, and attached and separated flow pressure distributions. The influence of frequency, pressure gradient, unsteady amplitude and measurement location are discussed. Results are compared with previous results and physical models for steady and unsteady flows. Superposition of unsteady and mean quantities appears to be valid for low pressure gradient attached flow, but becomes increasingly inadequate as separation is approached. Propagation of unsteady pressures in separated flow resembles a superposition of a disturbance convected downstream from the leading edge onto the standing wave patter found in attached flow, but includes numerous additional complexes.