The Effects of Warhead-Induced Damage on the Aeroelastic Characteristics of Lifting Surfaces. Volume 2. Aerodynamic Effects
Final rept. 1 Feb 1979-1 Mar 1980
TEXAS UNIV AT AUSTIN DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS
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Tests were made in a subsonic wind tunnel to determine the effects of damage on the aerodynamic characteristics of a T-38 aircraft stabilator half. Six damage configurations were used, one circular and the remainder trapezoidal in planform, with areas of up to 2 percent of the stabilator area. The damage holes were all ahead of the 50 percent chord line, with centers at 43, 60, and 75 percent span. Surface pressure distributions and lift and drag coefficients were measured. The 65A004 airfoil used is subject to leading edge separation which strongly influenced the results. In the absence of separation, damage effects tended to be localized and aerodynamic degradation was modest. With extensive separation, the damage influence propagated completely across the span, with more substantial degradation. There was up to 300 percent increase on CD sub o, but at moderate lift coefficients the drag increase was generally insignificant. The decrease in C sub L was more consistent, ranging up to 10 percent for the larger damage holes.
- Training Aircraft