Abstract: Rocket-powered models have been flown to provide an experimental comparison with linearized theoretical calculations for zero-lift drag of sweptback tapered wings having thin, symmetrical, double-wedge airfoil sections. The range of the experimental data is from a Mach number M of 1.0 to 1.8, and theoretical comparisons are made for the test range above M = 1.2. The linearized theory compared very favorably with the experimental results over most of the test range. For a given thickness and aspect ratio, taper generally increased the wing drag at low supersonic speeds but reduced the drag at higher speeds. For a given thickness and taper ratio, the wings of aspect ratio 4 had less drag below M = 1.2, but greater drag above M = 1.2, than the wings of aspect ratio 2.
| Limitations: |
 APPROVED FOR PUBLIC RELEASE |
| Description: |
Technical note |
| Pages: |
22 |
| Report Date: |
JUN 1956 |
| Report Number: |
A013773 |
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