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A review is presented of low-noise airplanes designed for operation in the 1980 time period. Aircraft with parametric engines covering a range of fan pressure ratios and noise levels were developed conceptually under contract with NASA Advanced Concepts and Missions Division, supported by the NASA Lewis Research Center contracts for the Quiet Clean STOL Experimental Engine (QCSEE) Study Program. Powered-lift concepts included externally blown flap, augmentor wing, internally blown flap, and over-the-wing upper surface blowing. Performance, sizing, and costs are described for 148 passenger airplanes with design field length varying from 2000-4000 ft. Techniques for reducing noise are evaluated in terms of aircraft performance, weight, and cost; experimental data on decayer nozzles are presented and assessed with respect to effectiveness in exhaust noise reduction and aircraft performance penalties.

The frequent use of large transport aircraft on soft and rough airfields in or near battle zones requires that they be fitted with landing gears having increased capability for ground flotation and shock absorption. Design and parametric studies of aircraft landing gears show feasible approaches to the problems associated with soft and rough airfields. Landing gear concepts, analytical methods, and design parameters are presented for airplanes of 110,000–750,000 lb gross weight. Landing gear weights, sizes, and configurations are compared, and their soft and rough field capabilities are evaluated. Structural and dynamic aspects of rough field operations are discussed for bare soil fields and for fields covered with landing mats.

Tactical Airlifters in the battlefield of the future will be required to operate on unprepared or damaged runways in all weather conditions without navigational or landing aids. Lockheed is addressing technologies required for these missions in an independent research and development program using a highly modified commercial C-130 aircraft as the technology integration focal point - a “Flying Laboratory.” The HTTB Program addresses the major technology areas of advanced short takeoff and Sanding, survivability, advanced cockpit, and electronic systems. The Program goal is to develop systems to support autonomous operations into a 1500-foot landing area, up to and including a 50-foot obstacle at the runway threshold.

This paper describes the comprehensive database developed by the Lockheed Aeronautical Systems Company which underscores (he critical mission needs for an Advanced Tactical Transport (ATT). A unique process was used to substantiate that an ATT must have the capability to: Deliver Army maneuver units and their fire support systems that weigh up to 55,000 lb. Operate on hot days, at night, or in bad weather from unpaved runways less than 2000 ft. In length at elevations greater than 4000 ft. Operate routinely within 20 nm of enemy Sines, and occasionally over enemy territory, and have improved survivability features. Accomplish multiple unrefueled sorties with total distances up to 1500 nm. Design implications, considering six specific alternative concepts, are discussed in terms of relative mission effectiveness, cost, supportability, survivability, technology and system programmatics.

From an analysis of a typical large airport and its growth problems, it is concluded that STOL aircraft systems are needed now-with or without high-speed ground transportation systems. It is also shown that the needed first-generation STOL aircraft can be in operation in 1975. These contemporary STOL aircraft will, however, be only a step in the evolution to improved aircraft of the future. The needs for technological improvements are discussed, and some new prospects in STOL technology are described.