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Abstract:
An exploratory investigation was performed to examine the distribution of forces on a modern fighter-bomber aircraft at incipient spin entry. The flight condition considered is a high angle of attack (in the range of 30 to 40 degrees) at zero sideslip. The loads of principal interest are side force, yawing moment and rolling moment. The general approach involves the use of aircraft and missile nonlinear, potential flow, vortex interference methods to examine the loads on the nose, wing-body, afterbody, and tail. Calculations were made for the F-5 configuration because of the availability of static force data at flight conditions of interest.
| Description: |
Annual rept. 1 May 74-1 Apr 75 |
| Pages: |
72 |
| Report Date: |
MAY 1975 |
| Contract Number: |
N0001474C0344 |
| Report Number: |
A642310 |
Report Unavailable |
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