Abstract: A rotorcraft with slung-load model was built for the general real-time flight simulation program. A general dynamic, distortional wake model based on the nonlinear and unsteady Peters-He inflow model was investigated and applied to the real-time wake model, it was an important part in the forward acceleration flight because the wake distortion effect and the blade unsteady aerodynamics relation to the whole aerodynamic force. The steady part of blade circulated airload was calculated by the full angle wind test data for all airfoils of the blade, but the unsteady part of the blade load was just a classical ONERA thin airfoil theory with dynamic stall. A six freedom slung load with a soft cable model was used to simulate the slung and also the helicopter motion. The control response character was analyzed in forward flight simulation under the step inputs of the collective pitch and push/pull stick control.