Skin thermal response for an aircraft with supplementary skin cooling system

A skin cooling design is being implemented for heat rejection from an aircr aft containing high-power electronic equipment. In this concept, baffled du cts at the aircraft skin are used to cool the air in the aft cabin, where t he equipment is located. The heat transfer through the skin causes the temp erature of the skin to rise. To stay well within the airworthiness requirem ents of the aircraft, it is desired to maintain the skin and frame temperat ure below 50 degrees C: for all operational scenarios. This paper provides an estimate of the skin and frame temperatures for full operation scenarios. Results show that the potential hot spots remain well below 50 degrees C for all flight conditions within the mission envelope.