02336nam 2200517 450 991070659080332120171114105131.0(CKB)5470000002456535(OCoLC)1011356298(EXLCZ)99547000000245653520171113j200102 ua 0engurbn|||||||||txtrdacontentcrdamediacrrdacarrierSupersonic wind tunnel tests of a half-axisymmetric 12°-spike inlet to a rocket-based combined-cycle propulsion system /J.R. DeBonis and C.J. TrefnyCleveland, Ohio :National Aeronautics and Space Administration, Glenn Research Center,February 2001.1 online resource (18 pages) illustrationsNASA/TM ;2001-210567"February 2001.""Prepared for the 37th Combustion Subcommittee, 25th Airbreathing Propulsion Subcommittee, and 19th Propulsion Systems Hazards Subcommittee Joint Meeting sponsored by the Joint Army-Navy-Air Force Interagency Propulsion Committee, Monterey, California, November 13-17, 2000.""Performing organization: National Aeronautics and Space Administration, John H. Glenn Research Center at Lewis Field"--Report documentation page.Includes bibliographical references (page 5).Supersonic wind tunnel tests of a half-axisymmetric 12 degree spike inlet to a rocket-based combined-cycle propulsion systemAir breathing boostersnasatHypersonic speednasatComputational fluid dynamicsnasatWind tunnel testsnasatPropulsionnasatPressure distributionnasatAir breathing boosters.Hypersonic speed.Computational fluid dynamics.Wind tunnel tests.Propulsion.Pressure distribution.DeBonis James R.1387413Trefny Charles J.NASA Glenn Research Center,GPOGPOBOOK9910706590803321Supersonic wind tunnel tests of a half-axisymmetric 12°-spike inlet to a rocket-based combined-cycle propulsion system3444583UNINA