プラグノズルのボートテールドラッグ低減に関する一考察

概要

論文の詳細を見る
Flow fields over annular plug nozzles of the air breathing engines are computationally simulated and the boat-tail drag characteristics are clarified and discussed based on the simulation results. First, the simulations are carried out for the axi-symmetric nozzle configuration using compressible Navier-Stokes equations. The result shows that primary cause of the boat-tail drag turns out to be the low pressure region downstream of the Prandtl-Meyer expansion. Next, the flow field with the axisymmetric slit injection is simulated. The computed result shows that the secondary flow injection successfully reduces the boat-tail drag. The effect of the secondary flow injection through the clustered slots with the sonic condition given at the slot exits on the boat-tail surface is next investigated and the result is compared to that of the axisymmetric slit injection. The result for the clustered slot injection shows that the boat-tail drag is reduced by about 40%. Effect of the secondary flow injection demonstrated by the simplified axisymmetric simulations is still larger for the clustered slot injection. The flow field with the secondary-flow injected directly from the inner nozzle is next investigated. Comparison of the results for the secondary flow injected directly from the inner nozzle and for the secondary flow given as a sonic condition at the exit shows that there is little difference in the flow structure and the pressure distributions over the boat-tail region.
宇宙航空研究開発機構の論文

プラグノズルのボートテールドラッグ低減に関する一考察

スポンサーリンク

概要

著者

関連論文

スポンサーリンク