Rans analysis of hl-crm at landing configuration with different flap deflections and engine representations

High Lift-Common Research Model (HL-CRM) was derived from the transonic high speed CRM using differing slat and flap deployments to represent the take-off and landing phase of aircraft analysis. Numerical Simulations based on RANS methodology are performed on the HL-CRM using the DLR-TAU flow solver. Flap deflection study is conducted on three different flap settings using the landing configuration, as formulated in the High Lift Prediction Workshop (HLPW-4) test case. A detailed flow comparison study is made between the flow through nacelle used in the HLPW-4 workshop test case and a recently developed nacelle configuration with powered engine boundary condition, using the nominal landing configuration. The main flow characteristics are analysed and compared to each other.