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aerodynamic Aeronautics aerosols angle APPENDIX bearing body calculated CALL Center coefficients combustor Comparison compressor concentration configuration Continued Contraction density determined distribution edge effects elements engine equations exhaust exit experimental Figure filter flaps flight flow FORMAT front fuel heating horizontal increase indicated inlet input ı ı ı located Mach numbers measurements mounted NASA obtained operation orbiter panel Performing position presented pressure range RATE ratio reference relative Report Research roof rotor shown in figure shows solids soot SPACE spanwise species speeds static station supports surface TECHNICAL temperature tile tunnel turbine units V/STOL values vane vertical walls wind wing
Page 13 - No. 645-25-05-01 11. Contract or Grant No. 12. Sponsoring Agency Name and Address National Aeronautics and Space Administration Washington, DC 20546 13. Type of Report and Period Covered Technical Note 14.
Page 27 - National Aeronautics and Space Administration Washington, DC 20546 14. Sponsoring Agency Code 15. Supplementary Notes 16. Abstract The engine was tested at altitude with various patterns and levels of total-pressure distortion created by screens.
Page 45 - Ohio 44135 11. Contract or Grant No. 13. Type of Report and Period Covered Sponsoring Agency Name and Address Technical Memorandum National Aeronautics and Space Administration Washington, DC 20546 14.
Page 25 - CSCL 14B The results of a series of flow quality and performance tests on several inlet and exit configurations for nonreturn wind tunnels are presented. Test section flow angularities, local dynamic pressure variations, and total-pressure-loss variations are presented as functions of wind-to-test-section dynamic pressure ratio. The results show that a nonreturn wind tunnel should have end treatments...