Investigations were conducted in the Langley 16-Foot Transonic Tunnel to provide data on a 0.10-scale model of the prototype F-18 airplane and a 0.047-scale model of the F-15 three-surface configuration (canard, wing, and horizontal tails). Test data were obtained at static conditions and at Mach numbers from 0.6 to 1.2 over an angle-of-attack range from 2 deg to 15 deg. Nozzle pressure ratio was varied from jet off to about 8.0.
Effect of Simulated in-Flight Thrust Reversing on Vertical-Tail Loads of F-18 and F-15 Airplane Models
1981
53 pages
Report
Keine Angabe
Englisch
Engineering Index Backfile | 1960
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