Transonic Flow: Rotor Hover Test Case
This test case is from the experimental data obtained from Caradonna and Tung as given by the reference below.
In this test case, the flow field is supercritical and pockets of transonic flow appear on the rotor blade surface in hover as shown by the color density contours. The subsequent page shows the comparison in pressure distributions on the blade surface with experimental data.
Also shown in the the set of pictures below are the initial and refined mesh as well as the partitioned mesh for parallel computing.
Two-Bladed Rigid Rotor in Hover (Transonic)
Experimental data: F.X. Caradonna, C. Tung. Experimental and analytical Studies of a Model Helicopter Rotor in Hover, TR-81-A-23
Collective pitch = 8°, Tip Match = 0.877. Ct = 0.00473