Single rotor helicopter parasite drag estimation in the preliminary design stage

Abstract

This paper presents the methodology for the rapid estimation of the single rotor helicopter parasite drag in the forward flight in the preliminary design phase. The aerodynamic drag of fuselage, main rotor hub, landing gear and the other, non-rotating defective surfaces contribute with more than 50% of the total power required for the forward flight at higher cruising speeds and therefore requires a more approximate determination in the design stages before the prototype development. The parasite drag determination is based on the evaluation of the basic value of The Equivalent Parasite Drag Flat Plate Area and its changes depending on the fuselage angle of attack. Plenty of the statistical indicators, aerotunnel tests results and the recent CFD investigations were taken into consideration during the process of developing and testing this methodology.

Keywords

• helicopter parasite drag
• performance
• preliminary design phase
• equivalent parasite dragflat plate area
• power required
• forward flight