@techreport{oai:jaxa.repo.nii.ac.jp:00006004,
 author = {河内, 俊憲 and 苅田, 丈士 and 富岡, 定毅 and Kochi, Toshinori and Kanda, Takeshi and Tomioka, Sadatake},
 month = {Nov},
 note = {Numerical simulations were conducted to predict the ejector pumping performance of our rocket-ramjet combined-cycle engine under a take-off condition, which will be tested in the Ramjet Engine Test Facility at Fy2006. Our code was verified by comparing the numerical pumping performance with the measured one in the rectangular ejector with constant-area mixing duct. The numerical simulations in the combined-cycle engine revealed that when the engine was driven by cold N2 gas, the suction airflow was chocked at the exit of the engine throat at the rocket chamber pressure of 3 MPa. Above the pressure of 3 MPa, the suction airflow rate was decreased because the aerodynamic chocking was induced by the underexpanded rocket plume. When the ejector-driving gas was changed from cold N2 gas to hot combustion gas, the suction performance decreased remarkably. The numerical Mach contour distributions at the combustion gas injection showed that the rocket plume was remarkably converged in the constant-area mixing duct, as a comparison of the result at the N2 gas injection. The reason why the pumping performance decreased when the ejector was driven by the combustion gas was explained by the analysis of the ejector with constant area duct including heat and mole transfers. Our analysis of the ejector revealed that the heat transfer from hot rocket plume with supersonic speed to cold airflow with subsonic speed induced the expansion of the airflow and the pressure rise. This pressure rise was the reason why the pumping performance decreased when the ejector was driven by the combustion gas., 資料番号: AA0049500020, レポート番号: JAXA-SP-06-006},
 title = {数値計算による複合エンジンの静止大気中における吸い込み性能予測},
 year = {2006}
}