Using Insulation blankets in the fuselage sikin creates many problems in the aircraft. Insulation blankets abosorb moisture whch in turn increases the weight of the aircraft and corrosion of the skin. In the present work, removal of the insulaion blankets and heating the fuselage skin with hot bleed air before it enters the air conditionsing system has been suggested. The hot bleed air enters the passage between the inner panel and the skin from the floor of the cargo and is discharged into the air conditioning system of the aircraft. An analytical study was perfoprmed to investigate the variations of the air, inner panel, and the aluminum skin temperatures. In the analysis, SINDA/G~R computer model was used. The computer model was run with the simulated conditions of the aircraft flying at the cruising altitude with a Mach number of 0.8 and an ambient temperature of -45 deg C. In order to evaluate the heat transfer coefficients for the air flow and the two walls, aluminum skin and inner panel, experiments were conducted.
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