국내 최대 기계 및 로봇 연구정보

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타이틀	Measured Sonic Boom Signatures Above and Below the XB-70 Airplane Flying at Mach 1.5 and 37,000 Feet
저자	Maglieri, Domenic J.;; Henderson, Herbert R.;; Tinetti, Ana F.
Keyword	B-70 AIRCRAFT;; F-104 AIRCRAFT;; FLOW DISTRIBUTION;; GROUND TESTS;; IN-FLIGHT MONITORING;; PRESSURE MEASUREMENT;; SHOCK WAVES;; SONIC BOOMS;; SUPERSONIC SPEED;; WIND TUNNEL TESTS
URL	http://hdl.handle.net/2060/20110011170
보고서번호	NASA/CR-2011-217077
발행년도	2011
출처	NTRS (NASA Technical Report Server)
ABSTRACT	During the 1966-67 Edwards Air Force Base (EAFB) National Sonic Boom Evaluation Program, a series of in-flight flow-field measurements were made above and below the USAF XB-70 using an instrumented NASA F-104 aircraft with a specially designed nose probe. These were accomplished in the three XB-70 flights at about Mach 1.5 at about 37,000 ft. and gross weights of about 350,000 lbs. Six supersonic passes with the F-104 probe aircraft were made through the XB-70 shock flow-field;; one above and five below the XB-70. Separation distances ranged from about 3000 ft. above and 7000 ft. to the side of the XB-70 and about 2000 ft. and 5000 ft. below the XB-70. Complex near-field "sawtooth-type" signatures were observed in all cases. At ground level, the XB-70 shock waves had not coalesced into the two-shock classical sonic boom N-wave signature, but contained three shocks. Included in this report is a description of the generating and probe airplanes, the in-flight and ground pressure measuring instrumentation, the flight test procedure and aircraft positioning, surface and upper air weather observations, and the six in-flight pressure signatures from the three flights.