衝撃波と境界層の3次元干渉現象の計測
研究申込者
前野 一夫 (千葉大学)
Abstract
he three-dimensional interaction between bow shock waves and boundary layer on the blunt nose and cylinder body is experimentally studied. By using the ISAS blow-down supersonic wind tunnel the supersonic experiment with a model system of two blunt bodies (main rocket and SRB) is performed. Flow visualization by multi-color schlieren method and oil flow method has carried out. The pressure measurement on the surface of main body model has also been performed. The three-dimensional interacting flow field between the bow shock wave and the boundary layer is investigated by CFD. Both results are compared.
Key words
Three-dimension, Shock-boundary layer interaction, Color schlieren, Oil flow pattern, CFD, RANS
2005年度の研究成果
日本航空宇宙学会関連講演会予定。
可視化情報情報学会予定。
利用期間
平成17年12月5日〜9日