Computational Analyses for an Advanced Propeller Powered Theater Transport

A computational analysis with a time averaged rotor model has been performed for an advanced propeller powered transport. The transport is designed to be a super short take-off and landing vehicle, which has large diameter propellers and forward swept outboard wing. The flow solver OVERFLOW implemented with rotor model was utilized with an overset grid system to simulate the flow field at high lift conditions with trailing edge flap deflected up to 40 degrees. Computational results were compared with 10.75% semi-span wind tunnel test data. With the same blade angle and advance ratio as used in the test, computed thrust coefficients were lower than test ones, which in turn led to under-predicted lift coefficients. When collective was trimmed to achieve similar thrust level as the test, very good agreement in the lift and drag were obtained. The computational results have been used as a guide for design updates and led to reduced design cycle time.