THE USE OF A LEADING-EDGE AREA-SUCTION FLAP AND LEADING-EDGE MODIFICATIONS TO IMPROVE THE HIGH-LIFT CHARACTERISTICS OF AN AIRPLANE MODEL WITH A WING OF 45° SWEEP AND ASPECT RATIO 2.8

摘要

An investigation was made with an electrical heat-flow analog to determine the effect of internal modifications to a wing leading edge on the surface-temperature rise and temperature distribution for conditions of transient aerodynamic heating at high supersonic speeds.nThe study showed that when heat-absorbing material is concentrated in the wing leading-edge region, in the case of wings of large leading-edge radius, the temperature rise at the leading-edge point is determined primarily by the specific heat of the material. As the leading-edge radius is decreased, the thermal conductivity of the heat-absorbing material was shown to have an increasingly important effect. For cases of wings in which the skin is of uniform thickness in the leading-edge region, thermal conduction is of major importance in restricting the leading-edge tempera¬ture rise.nBecause of its high specific heat and thermal conductivity, beryllium appears attractive in heat-sink applications. In an example, beryllium was shown to be far superior to Inconel-X from the standpoints of leading-edge-temperature rise, temperature distribution, and weight.