同源图形

FIGURE 1	FORCE COMPONENTS FOR	TEST PROCEDURE FOR D
TEST PROCEDUE FOR DE	TURBINE POWERED SIMU	SIMPLIFIED ADP TURBO
POTENTIAL EFFICIENCY	PROPULSIVE EFFICIENC	TYPICAL OPERATING CH
PHOTOGRAPH OF ADP SI	EFFECT OF PRESSURE L	TREND TOWARD HIGHER
EXAMPLE FAN MAP	THE PRATT & WHITNEY	THE GENERAL ELECTRIC
THE PRATT & WHITNEY	COMPARISON OF CURREN	MECHANICAL CONSIDERA
AERODYNAMIC CONSIDER	INSTALLATION CONSIDE	CFD STATIC PRESSURE
COMPARISON OF CFD AN	COMPARISON OF CFD AN	TYPICAL TWIN-ENGINE,
TYPICAL TWIN-ENGINE,	LARGE, 4-ENGINE ARRA	TYPICAL AFT FUSELAGE
THRUST - LOW ROTOR S	THRUST - LOW ROTOR S	THRUST - FUEL FLOW C
THRUST - FUEL FLOW C	THRUST - LOW POWER T	THRUST - LOW POWER T
THRUST - LOW-POWER S	THRUST - LOW POWER S	EXHAUST NOZZLE COEFF
EXHAUST NOZZLE COEFF	EXHAUST NOZZLE COEFF	EXHAUST NOZZLE COEFF
MINIMUM TOTAL RESIDU	RESIDUAL ERROR OVERA	RESIDUAL ERROR OVERA
RESIDUAL ERROR OVERA	STATIC PRESSURE CORR	VARIATION OF ADP OPE
GLTF FAN PRESSURE CO	EXPECTED SHAPE OF EX	17 IN TURBINE POWERE
NASA 22 IN TPS	GENERAL ELECTRIC LAR	PRINCIPAL OF MATCHIN
THE APPLICATION OF A	TYPICAL VARIATION OF	VARIATION OF THRUST
VARIATION OF THRUST	TURBULENT SKIN-FRICT	DATA SOURCES FOR OVE
DATA SOURCES FOR GAS	SEPARATE FLOW EXHAUS	INLET MODEL
CROSS SECTION OF ADP	TPS CONTROL VOLUME	INSTALLED TEST MODEL
FLOW-THROUGH NACELLE	BLOWN MODEL	TURBINE POWERED SIMU
ISOLATED TEST STAND	POWERED SEMISPAN MOD	EFFECT OF POWERED NA
ADJUSTMENTS MADE TO	CORRELATION OF C-5A	FULL SCALE ENGINE TE
FLIGHT TEST ENGINE T	ALTITUDE TEST FACILI	FLIGHT TEST ENGINE T
EXAMPLE FOR CLOSURE	FLIGHT TEST DRAG CHA	CYCLE ASSUMPTIONS FO
CYCLE ASSUMPTIONS FO	CYCLE ASSUMPTIONS FO	ENGINE-OUT DRAG ERRO
ENGINE-OUT DRAG ERRO	ILLUSTRATION OF LOSS	COMPARISON OF PREDIC
ENGINE-OUT SIMULATIO	SKETCH AND PHOTOGRAP	ADP DEMONSTRATOR INS
17 IN TPS RIG VALIDA	17 IN TPS RIG VALIDA	TYPICAL REVERSE THRU
RANDOM SAMPLE OF REV	AIRPLANE RETARDING F	TYPICAL REJECTED TAK
TYPICAL FAN STREAM T	FORCE CONTRIBUTIONS	COMPUTED STREAMLINE
REVERSE THRUST DISCO	WING/PYLON/NACELLE/F	AIRPLANE AND REVERSE
EFFECT OF INSTALLATI

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