Effect of Actuated Forebody Strakes on the Forebody Aerodynamics of the NASA F-18 HARV

Content Provider	Semantic Scholar
Author	Fisher, David F. Murri, Daniel G. Lanser, Wendy R.
Copyright Year	1996
Abstract	0radome (RS. = 60 to 124.5) yawing moment at 13= 0° from integrated pressurespressure coefficient, ( p - PO )/q_computational fluid dynamicsfuselage station, in.pressure altitude, ftHigh Alpha Research VehicleHigh-Alpha Technology ProgramMach numberlocal pressure, lb/ft 2free-stream static pressure, lb/ft 2free-stream dynamic pressure, lb/ft 2Reynolds number based on mean aerodynamic chord of 11.525 ftstrake span location divided by the local strake spanaircraft angle of attack, deg, from left wingtip angle-of-attack vane corrected forupwash and boom bendingaircraft angle of sideslip, deg, average of left- and right-wingtip sideslip vanescorrected for angle of attack, degincremental change in aircraft yawing moment coefficient due to a -30 ° deflectionof both rudderssingle strake deflection, degdifferential strake deflection, right strake deflection minus left strake deflection, degleft and right strake deflection measured from the retracted position, degforebody cross-section circumferential angle, deg (0 ° is bottom centerline, positiveis clockwise as seen from a front view, 0° to 360 °)INTRODUCTIONThe NASA High-Alpha Technology Program (HATP) was initiated to increase understanding,improve prediction techniques, provide design guidelines, and investigate new concepts for con-trois effectors on advanced, highly maneuverable aircraft at high angles of attack.
File Format	PDF HTM / HTML
Alternate Webpage(s)	https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19970001799.pdf
Alternate Webpage(s)	https://www.nasa.gov/centers/dryden/pdf/88441main_H-2136.pdf
Language	English
Access Restriction	Open
Content Type	Text
Resource Type	Article