Technical Memorandum of National Aerospace Laboratory
巻
185
ページ
27
発行年
1970-09
抄録（英）
Some results of low-speed performance tests with a smaIl-scale model for turbo- fan engine are presented and discussed. The results are as follows: 1) At zero flight speed, the total pressure recovery with a given opening area of the auxiliary inlet ports decreased as the mean axial flow velocity V2 at the fan face increased. 2) In the test range of flight speed Vo, the total pressure recovery with a given opening area of the auxiliary inlet ports increased up to 99% and more as the value of Vo/V2 increased. 3) At any tested combination of Vo with V2, the total pressure recovery increased as the number of the closed auxiliary inlet ports decreased. 4) The observed upstream flow behavior, inlet distortion, and surface static pressure distribution as the function of the value of Vo/V2 are presented and discussed taking the effects of ground clearance and attack angle also into consideration.
推進エンジン用空気取入口の予備実験
naltm00185.pdf
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