Accession Number : AD0528629

Title :   Variable Camber Wing - Phase I.

Descriptive Note : Final rept. 15 Mar 71-15 Sep 73,

Corporate Author : BOEING AEROSPACE CO SEATTLE WASH RESEARCH AND ENGINEERING DIV

Personal Author(s) : Gould,Douglas K.

Report Date : 01 OCT 1973

Pagination or Media Count : 416

Abstract : The objectives of this ONR sponsored investigation have been to design a variable camber system, establish its performance capabilities and provide data to support a decision for flight demonstration. The variable camber wing consists of leading and trailing edge flaps that can be deflected to match the camber requirements of any flight condition. Wing leading and trailing edge flaps with flexible skins, combined with a simple internal mechanism, are used to achieve smoothly curved upper surfaces so that an optimum wing shape can be provided throughout the flight spectrum. The variable camber system combines the resulting improved aerodynamic characteristics with an automatic flight control system that deploys the flaps in response to airplane flight requirements without adding to pilot workload. This system achieves outstanding transonic combat, subsonic cruise and low speed performance without degrading supersonic performance capability. (Author)

Descriptors :   (*Jet fighters, Wings), (*Variable incidence wings, Camber), (*Leading edge flaps, Camber), (*Flaps(Control surfaces), Camber), (*Wings, Camber), Trailing edge, Variations, Aerodynamic characteristics, Deployment, Flight control systems, Automation, Supersonic flight, Transonic flight, Performance(Engineering), Costs, Wind tunnels, Tables, Mach number (U) Aircraft landings, Flight stability, Lift, Takeoff, Drag, Maneuverability, Pitch(Motion), Yaw, Roll, Fuel consumption, Weight

Subject Categories : Attack and Fighter Aircraft
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE