Developmental methods to improve A-6E Intruder airplane single engine performance in the flaps and slats extended configuration

The purpose of this thesis is to explore and develop methods to increase single engine rate of climb performance for the A-6E airplane in the flaps and slats extended configuration. The A-6A airplane was originally developed in the late 1950's. A-6A single engine rate of climb performance in the flaps and slats extended configuration was satisfactory. Subsequent series of the A-6 have included modifications which increased aircraft weight and parasitic drag. Aircraft basic weight has grown from 25,684 to 29,944 pounds. This coupled with increases in airframe drag, has substantially degraded the single engine rate of climb performance to a point where under some normal operating conditions with the flaps and slats extended the airplane can not maintain altitude if an engine fails. Proposed solutions to this problem include decreasing weight and drag through airframe modifications and increasing the thrust of the existing engine or installing a more powerful engine. A more cost effective proposal is to decrease aircraft drag in the flaps and slats extended configuration by incorporating an intermediate flap setting between the existing 0° and 30° deflections. A 20° flap deflection angle was implemented in a test A-6E airplane with very favorable results. It is recommended that all A- 6E airplanes be modified with a 20° flap selection to improve single engine rate of climb performance in the flaps and slats extended configuration.