Flight and wind-tunnel calibrations of a flush airdata sensor at high angles of attack and sideslip and at supersonic Mach numbers
作者： Timothy R. Moes , Stephen A. Whitmore , Frank L. Jordan
DOI:
关键词: Pressure measurement 、 Mach number 、 Transonic 、 Mathematical model 、 Engineering 、 Potential flow 、 Wind tunnel 、 Angle of attack 、 Supersonic speed 、 Aerospace engineering
摘要: A nonintrusive airdata-sensing system was calibrated in flight and wind-tunnel experiments to an angle of attack 70 deg angles sideslip +/- 15 deg. Flight-calibration data have also been obtained Mach 1.2. The sensor, known as the flush airdata installed on nosecap F-18 aircraft for tests a full-scale forebody tests. Flight occurred at NASA Dryden Research Facility, Edwards, California, using High Alpha Vehicle. Wind-tunnel were conducted 30- by 60-ft wind tunnel LaRC, Hampton, Virginia. sensor consisted 23 flush-mounted pressure ports arranged concentric circles located within 1.75 in. tip nosecap. An overdetermined mathematical model used relate measurements local quantities. based potential flow over sphere empirically adjusted data. For quasi-steady maneuvering, worked well throughout subsonic, transonic, low supersonic regimes. angles-of-attack -sideslip regions studied.
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