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超音速引射喷管的理论计算方法 被引量:1

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作者 王洪烈
出处 《航空发动机》 1991年第5期30-41,共12页 Aeroengine
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  • 1何慧姗,钱翼稷.引射喷管的气动性能和传热计算[J].北京航空航天大学学报,1996,22(4):415-420. 被引量:2
  • 2Huddleston S C,Wilsted H D, Ellis C W. Performance of several air ejectors with conical mixing sections and small secondary flow rates[R]. NACA RM ESD23,1948.
  • 3Ellis C W, Hollister D P, Sargent A F, et al. Preliminary investigation of cooling-air ejector performance at pressure ratios from 1 to 10[R]. NACA RM E51H21,1951.
  • 4Greathouse W K, Hollister D P. Preliminary air-flow and thrust calibrations of several conical cooling-air ejectors with a primary to secondary temperature ratio of 1.0: I diameter ratios of 1,21 and 1,10[R]. NACA RM E52E21, 1952.
  • 5Greathouse W K, Hollister D P. Preliminary air-flow and thrust calibrations of several conical cooling-air ejectors with a primary to secondary temperature ratio of 1.0: lI diameter ratios of 1.06 and 1.40[R]. NACA RM E52F26, 1952.
  • 6Greathouse W K, Hollister D P. Air-flow and thrust char- acteristics of several cylindrical cooling-air ejectors with a primary to secondary temperature ratio of 1.0[R]. NACA RM E52L24,1953.
  • 7Huntley S C,Yanowitz H. Pumping and thrust characteris- tics of several divergent cooling-air ejectors and compari- son of performance with conical and cylindrical ejectors [R]. NACA RM E53J13,1954.
  • 8Trout A M,Papell S S,Povolny J H. Internal performance of several divergent-shroud ejector nozzles with high diver- gence angles[R]. NACA RM E57F13, 1957.
  • 9Anderson B H. Computer program for calculating the flow field of supersonic ejector nozzles[R]. NASA TN D-7602, 1974.
  • 10Ludwig C B, Malkmus W, Reardon J E, et al. Handbook of infrared radiation from combustion gases[R]. NASA-SP- 3080,1973.

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