Aerodynamic Design of Pusher Propeller for a Promising Rotorcraft
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- AND GAS-DYNAMICS OF FLIGHT VEHICLES AND THEIR ENGINES
Aerodynamic Design of Pusher Propeller for a Promising Rotorcraft V. I. Shaidakova, Yu. M. Ignatkina, A. I. Shomova, *, and P. V. Makeeva a
Moscow Aviation Institute (National Research University), Volokolamskoe sh. 4, Moscow, 125993 Russia *e-mail: [email protected] Received February 27, 2020; revised March 4, 2020; accepted March 4, 2020
Abstract—A method based on the complex application of the actuator disk and finite-blade vortex theories is presented for aerodynamic design of the pusher propeller of a promising rotorcraft for vertical takeoff and landing. The software package was created that allows us to select the propeller parameters, create its 3D model and calculate aerodynamic characteristics in semi-automatic mode. DOI: 10.3103/S1068799820020130 Keywords: aerodynamic design, pusher propeller, rotorcraft, actuator disk vortex theory, finite-blade vortex theory, 3D model, software package.
Improving the speed characteristics is one of the main tasks in creating a new generation of rotorcraft [1, 2]. In the civilian sector, the rotorcraft cruising speed is essential for medical and search-and-rescue missions, as the timing of such operations is vital. For a military rotorcraft, high cruising and maximum flight speeds can significantly increase the combat effectiveness. Currently, production helicopters have average cruising and maximum horizontal flight speeds of 280 km/h and 300 km/h, respectively. The limitation of the maximum flight speed of rotorcraft is due to the well-known features of the main rotor aerodynamics in the forward flight modes. Among the phenomena impeding the rotorcraft speed augmentation, there are transonic flow crisis at the end of the advancing blade, reverse flow and stall of the retreating blade [1–4]. These features lead to a sharp increase in the power required to rotate the main rotor, an increase in hinge moments and vibrations. Ways practiced to deal with these problems, such as reducing the rotor speed and rotor unloading by installing the wing, lead to a decrease in the propulsive ability of the main rotor. At the same time, as the speed increases, the drag of the fuselage itself increases significantly. In this regard, the promising high-speed rotorcraft requires the use of additional sources of propulsive force. The most optimal (in terms of power consumption and fuel costs) is the use of additional propellers. As an example, we can cite a number of recent developments of high-speed rotorcraft, which use propellers to create additional propulsive force [3]. These are, first of all, the S-97 Raider [5] and the Sikorsky–Boeing SB-1 Defiant, as well as the Eurocopter X3 demonstrator developed and the new concept Airbus Racer [6]. Thus, the propeller as a propulsive engine now tightly occupies its niche in the segment of development of advanced high-speed rotorcraft. In this regard, it is important to improve approaches to the aerodynamic design of propellers for various promising aircraft based on modern digit
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