Hypersonic CFD (Computational Fluid Dynamics) analysis is made for blunt nosed, ramped flat plates. Heat transfer and flow field around compression ramp have been investigated numerically. The present work correspond to the experimental study using the NAL 1.27 m and ONERA (Office National d'Etudes et de Recherches Aerospatiales) S4MA hypersonic wind tunnels, where the infrared thermography measurements are made at M(sub infinity) = 10.0 and angles of attack 0 deg, 20 deg, 30 deg and 35 deg. Heat transfer distributions and shock-shock interaction patterns are compared in detail, changing angles of attack and Reynolds numbers. Comparisons with CFD simulation using NAL and ONERA Navier-Stokes Codes were also made.
ONERA-NALマッハ10平板模型対応風試CFD解析
nalsp0037029.pdf
(648.29KB)
