Thrust Nozzle Design Study for a Quasi-Axisymmetric Scramjet-Powered Vehicle

摘要: The design of a nozzle an unfueled quasi-axisymmetric scramjet model is optimized for minimum drag Mach 8 flight condition. approach to the develop simple force-prediction methodology in optimization study. study completed configuration, but could be used fueled configuration by including appropriate combustion modeling. effects on overall vehicle performance are included. baseline was measured T4 shock tunnel numbers ranging from 5.7 10.3, confirming suitability methodology. results nozzle-optimization show that limited area ratio can incorporated into without leading too large base diameter and increasing external vehicle. designs at different investigated parametric 6 10. confirm longer nozzles better higher numbers. Copyright © 2010 American Institute Aeronautics Astronautics, Inc.