Configuration Design Studies and Wind Tunnel Tests of an Energy Efficient Transport with a High-aspect-ratio Supercritical Wing1982 - 195 pages |
Contents
INTRODUCTION | 3 |
CONFIGURATION DEFINITION | 11 |
TEST PLAN AND MODEL DESCRIPTION | 19 |
3 other sections not shown
Common terms and phrases
aerodynamic aircraft angle approximately aspect ratio ATMR body boundary layer transition buffet CALCULATED AND EXPERIMENTAL CHARACTERISTICS OF WING chord CHORDWISE PRESSURE DISTRIBUTIONS compared COMPARISON OF CALCULATED compressibility Configuration criteria cruise DIMENSIONS divergence Mach number Douglas drag divergence Mach drag increment Effect of Nacelle fan exit FIGURE five flap linkage fairing fuel full scale fuselage geometry high-speed horizontal tail inboard included increased indicated lift coefficient LOAD COMPENSATOR longitudinal lower surface maximum measured nacelle/pylon obtained panel PERCENT PERCENT SEMISPAN performance Phase PITCHING MOMENT CHARACTERISTICS planform position presented pylon reduction REFERENCE NOTE AMES Report Reynolds number shown shown in Figure significant span spanwise stability station studies supercritical wing Symbol Run Mach TAIL-OFF test data thickness trailing edge TRANSITION FIXED TRANSITION FREE transition-free upper surface vertical WING W WING W₁ wing/body