Publication Date:
2019-06-28
Description:
Attention is given to the NASA Langley Research Center's testing of a 10.5 percent-scale supersonic cruiser (supercruiser) aircraft model in its V/STOL wind tunnel, in order to investigate the low speed aerodynamic characteristics of STOL enhancement devices. The STOL devices employed by the supercruiser configuration are high vector angle ramp nozzles, working in conjunction with a remote augmented lift system (RALS), in addition to a canard trim system. Also investigated were thrust reverser/ground plane interaction effects, for the evaluation of landing characteristics. It is noted that STOL approach thrust management requires the use of a partially reversing RALS nozzle which develops approximately 31 percent of main nozzle thrust, and that strong nose-up interactions during ground roll, with reverser operation, may limit dry power engine thrust for braking assistance to about 50 percent of maximum dry power.
Keywords:
AERODYNAMICS
Type:
AIAA PAPER 83-1224
Format:
text
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