Dynamic Ground-effect Measurements on the F-15 STOL and Maneuver Technology Demonstrator (S/MTD) ConfigurationNational Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990 - Short take-off and landing aircraft - 28 pages |
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1.5 h/b Figure acceleration aerodynamic loads approach and rollout approach procedure axial balance canard comparison configuration at three data base predictions differences dj,l drag coefficient dynamic ground Effect of model flow field ft/sec ground board ground boundary layer ground effect ground plane ground vortex horizontal portion horizontal stabilizer inertial loads jet vector angles jets were vectored Kemmerly Langley Research Center less nose-down pitching lift coefficient linear longitudinal aerodynamics lower jet vector Maneuver Technology Demonstrator minimum ground height minimum height model height moment of inertia NASA pitching-moment coefficient plenum plotted procedure were adopted rate of descent rate-of-descent modeling reverser vector angles rollout configuration rollout phases S/MTD aircraft S/MTD approach configuration simulation data base steady-state STOL and Maneuver strain gauge Technology Demonstrator S/MTD three rates thrust reverser thrust vector angles U.S. Air Force upwash vectored farther forward vectored jets vectored thrust simulator VRF testing wheel touchdown height