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AERODYNAMIC DRAG REPORT at: --------------------------- MACH 0.800 Altitude (pressure) 45000. feet KTAS 458.9 KEAS 201.9 KCAS 215.5 Reynolds number 1.200 millions per foot Delta-ISA +0. deg.C. CL 0.478 based on: Reference Area 1137.00 sq.feet (trapezoidal) Drag Coefficients based on ref.area ----------------------------------- Cd Zero-Lift 0.01537 (58.6 %) Cd Lift-Induced 0.01009 (38.4 %) Cd Compressibility 0.00059 ( 2.3 %) Cd Trim 0.00019 ( 0.7 %) Delta Cd (polar-mod) 0.00000 ( 0.0 %) ------- -------- Cd Total 0.02625 ( 100 %) Aerodynamic Boundaries: ----------------------- Divergence Mach 0.803 {at the given CL 0.478} Initial Buffet Mach 0.879 {at the given CL 0.478} Initial Buffet CL 0.775 {at the given Mach 0.800} Zero-Lift Component Breakdown (Drag Areas,= Cd*S = D/q) ----------------------------- Wing 6.398 sq.feet (36.6 %) Winglets 0.203 sq.feet ( 1.2 %) Fuselage & fairing 4.949 sq.feet (28.3 %) Stabiliser 2.257 sq.feet (12.9 %) Fin 1.206 sq.feet ( 6.9 %) (incl.dorsal) Nacelles (total) 2.466 sq.feet (14.1 %) User CdS Increment 0.000 sq.feet ( 0.0 %) ------- -------- Total Cd0*S 17.479 sq.feet ( 100 %) Overall Lift / Drag Ratio = 18.21 ================================= Total Lift Force 75000. lbf. Total Drag Force 4118. lbf. (2059.lbf. per engine) Engine / Airframe Performance: ------------------------------ Total Fuel Flow at Thrust=Drag: 2638. lb/hr Specific Fuel Consumption (SFC) 0.6406 lb/hr/lbf Specific Air Range (SAR) 0.1739 nm/lb Available Total Thrust at MCR: 4693. lbf. Available Total Thrust at MCL: 5130. lbf. Instantaneous Performance Reserves at Weight=Lift: RoC at MCR, constant Mach 0.800: 356. feet/min RoC at MCR, constant 216.KCAS: 257. feet/min RoC at MCL, constant Mach 0.800: 627. feet/min RoC at MCL, constant 216.KCAS: 452. feet/min |