http://swrc.ontoware.org/ontology#TechnicalReport
スクラムジェットノズル流の数値シミュレーション
ja
露木 太郎
保坂 康
東野 文男
Tsuyuki Taro
Hosaka Yasushi
Higashino Fumio
航空宇宙技術研究所
National Aerospace Laboratory(NAL)
航空宇宙技術研究所特別資料
16
165-172
1991-12
The objective of this paper is to compute the expansion of a supersonic flow through an internal-external nozzle and its interaction with the supersonic flow of free stream air. Furthermore, we are also attempting to calculate thrust and lift for a scramjet nozzle. The governing equations are the Navier-Stokes equations for two-dimensional flows. The finite difference scheme employs an implicit upwind scheme. A turbulent model is adapted to the Baldwin-Lomax model. The diffusion, reaction and radiation of gas is neglected. Calculations are performed for the cases that have Mach number, temperature and pressure range at the combustor exit of 3,200 degrees K and 1 to 2 atmospheres respectively. The values on the outside of the afterbody and cowl are 3,500 degrees K and 0.1 to 1 atmospheres respectively. The effects on the flow field, thrust and lift due to change of pressure, velocity and nozzle shape are studied. The results of the numerical calculations give different flow fields for underexpansion or overexpansion at the cowl exit. Consequently, we found that the patterns of an asymmetric nozzle flow were fixed by the degree of expansion at the cowl exit and that no perfect correct expansion existed in these flows. Furthermore, we found that the internal flow of the nozzle in case of the overexpansion was largely influenced by the flow of free stream air.
0289-260X
AN10097345
資料番号: NALSP0016026
レポート番号: NAL SP-16