Investigation On Wing-Rotor Aerodynamic Interaction Of The Compound Helicopter In Hover

Research on the aerodynamic interaction between the rotors and components of rotorcraft have been a very important aspect and a very challenging subject in Rotorcraft Aerodynamics. This thesis is aimed the wing-rotor aerodynamic interaction of the compound helicopter in hover. When the compound helicopter is in hover, the aerodynamic download from rotor imposes on the wing. In this time, there is a severe aerodynamic interaction between wing and rotor. Based on a vortex-tube wake model and a wing source panel method, the wing-rotor aerodynamic interaction model is developed. In Chapter 2, a vortex-tube wake model is developed, and is used to calculate and analyze some examples and the capability of the present model is demonstrated. Some new results are acquired. In Chapter 3,a wing source panel method is developed, is used to calculate and analyze some examples and the capability of the present model is demonstrated. In Chapter 4, the wing-rotor aerodynamic interaction model is developed by employing the vortex-tube wake model in chapter 2 and a wing source panel method in chapter 3, and is used to calculate and analyze some examples; secondly, the influence of many parameters on the wing-rotor aerodynamic interaction model is calculated and analyzed; finally, many important results is acquired.