Local Flow Field Around a Pylon-mounted Dummy Ramjet Engine on the X-15-2 Airplane for Mach Numbers from 2.0 to 6.7 |
Common terms and phrases
40°-cone probes ablative coating agreement with wind-tunnel angle of attack angle of sideslip angle-of-attack boundary layer camera Camera-fairing shock wave center cone cone probes Data fairing diameter dummy ramjet engine dummy ramjet installed Figure 12 flight conditions flow angles flow angularity flow model flow-field parameters free-stream angle free-stream Mach number Fuselage static-pressure orifice high Mach numbers Hypersonic impact-pressure data impact-pressure ratio kN/m² local Mach number Lower 40 lower ventral fin M₂ NASA TN nose cone number and angle percent pressure coefficient pressure data pylon impact pressures pylon probe pylon-fuselage intersection ramjet and pylon ramjet region ramjet spike tip reference schlieren photograph data separation shock wave shock-wave impingement Shock-wave locations shock-wave strength showed good agreement shown in figure side-fairing shock wave Spike-flare shock wave Spike-tip shock wave static pressure ventral probe wave impingement Wind tunnel ref wind-tunnel data wind-tunnel schlieren photographs wing shock wave wing-leading-edge shock wave