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Abstract:
A series of measurements has been made of the velocities in the near wake of an airfoil in an unsteady flow generated by rotating an elliptic cylinder near the trailing edge. Ensemble averages of the tangential and normal velocity components and of 3 Reynolds stresses were determined for reduced frequencies based on semichord up to 6.4, angles of attack of 0 and 10 degrees, Reynolds numbers of 700,000 and 1,450,000, and chordwise positions 1.025 x/c 1. 2. In this region the airfoil wake is distinct from the wake of the elliptic cylinder. The mean and unsteady velocities and Reynolds stresses diffuse rapidly so that the distinction between the contributions due to the two boundary layers on the airfoil surfaces, apparent at x/c=1.025, has largely disappeared by x/ c=1.20. (Author)
| Description: |
Interim rept. |
| Pages: |
13 |
| Report Date: |
JAN 1983 |
| Contract Number: |
AFOSR-80-0282 |
| Report Number: |
A447731 |
Report Unavailable |
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