Fuselage and nozzle pressure distributions of a 1/12-scale f-15 propulsion model at transonic speeds: effect of fuselage modifications and nozzle variables
Odis C. Pendergraft, George T. Carson, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1984 - Technology & Engineering
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16-Foot Transonic Tunnel A/B power nozzle A/B vents afterbody angle of attack Boom,top Boom.top p.boom bottom of fuselage bottom of nacelle boundary-layer rakes comparing figure Concluded Continued distributions on bottom distributions on nozzle distributions on top dry power nozzle engine bay cooling F-15 propulsion model Figure 70 flight tests forebody full-scale aircraft fuselage along centerline fuselage engine interfairing fuselage modifications horizontal-tail deflection Integrated axial-force coefficient interfairing along centerline Intermediate A/B power intermediate afterburning power Langley 16-Foot Transonic left-hand nozzle left-hand rake Mach number model with nose NACA nacelle and nozzle nose boom nozzle axial-force coefficient nozzle boattail angle nozzle exit nozzle pressure coefficients nozzle pressure ratio nozzle steps power settings presented in figure PTRl/Pt right-hand rake static-pressure orifices Static-pressure-coefficient distributions steps no rakes tail boom top of fuselage top of nacelle top of tail unmodified model X/L X/L f X/L X/L X/L X/L