The Influence of Wing Loading on Turbofan Powered STOL Transports with and Without Externally Blown FlapsThe effects of wing loading on the design of short takeoff and landing (STOL) transports using (1) mechanical flap systems, and (2) externally blown flap systems are determined. Aircraft incorporating each high-lift method are sized for field lengths of 2,000 feet, 2,500 feet, and 3,500 feet, and for payloads of 40, 150, and 300 passengers, for a total of 18 point-design aircraft. An assumed 1975 level of technology is applied to both concepts in terms of propulsion, weights, active controls, supercritical wing methodology, and acoustics. Low-wing-loading STOL configurations with mechanical flaps are found to be competitive with externally blown flap STOL configurations over wide ranges of payload and field length for the airworthiness rules and technology improvements assumed. Because the results of design studies like this one are sensitive to the ground rules assumed, careful attention is paid to describing the assumptions. These assumptions must be understood before the results are compared with other STOL airplane studies. |
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1.00 ELECTRONICS 1.00 OPERATIONAL EMPTY 1.00 PASSENGER ACCOMMODATIONS 1.12 AIR CONDITIONING 150 passengers aircraft airplane blown flap CARGO ACCOMMODATION CHORD THICKNESS RATIO Climb gradient crosswind landing cruise drag coefficient drag polar EBF EBF configuration ENGINE STARTING SYSTEM ENGINE STRUTS ENGINE F.A. R. field length field length ASAMP FIXED EQUIPMENT INSTRUMENTS FIXED EQUIPMENT WEIGHT FLIGHT DECK ACCOMMODATIONS go-around GROUP WEIGHT PRIMARY GROUP WEIGHT STATEMENT GROUP WING HORIZONTAL High speed drag induced drag LEADING EDGE SWEEP lift coefficient Mach number MANUFACTURERS EMPTY WEIGHT MEAN AERODYNAMIC CHORD OPERATIONAL EMPTY WEIGHT OPERATIONAL ITEMS PAYLOAD PROPULSION GROUP WEIGHT PROPULSION WEIGHT INCREMENT RATIO TAPER RATIO ROOT CHORD speed drag polar STANDARD AND OPERATIONAL STATEMENT MF configuration STOL STRUCTURE WEIGHT INCREMENT STRUCTURES GROUP WING STRUTS ENGINE NACELLES supercritical wing tail area takeoff THICKNESS RATIO ROOT THICKNESS RATIO TIP THRUST REVERSERS TOTAL FIXED EQUIPMENT TOTAL PROPULSION GROUP TOTAL STRUCTURE WEIGHT WEIGHT PRIMARY ENGINES wind tunnel wing loading