| A helicopter with a fixed geometry rotor, operating at a fixed rotational speed, performs sub-optimally over the vehicle’s flight envelope. On the other hand, if the rotor geometry and RPM can be varied from one flight condition to another, the aircraft performance can be substantially improved over the operating envelope. The geometry change considered in this study is the variation of rotor chord over a spanwise section of the blade. Simulations are based on a UH-60A Blackhawk helicopter with an effective chord increase of 20% realized by extending a Trailing-Edge Plate (TEP) through a slit in the trailing-edge between 63–83% blade span. Rigid and elastic blade models are studied. Since TEP extension changes the baseline SC-1094R8 airfoil profile, 2D aerodynamic coefficients of the modified profile from Navier-Stokes CFD calculations are used, coupled with 12x12 dynamic inflow and Leishman-Beddoes dynamic stall model in the Rotorcraft Comprehensive Analysis System (RCAS). From the simulations, reductions of up to nearly 18% in rotor power requirement are observed for operation at high gross weight and altitude. Further, increases of around 18 kts in maximum speed, 1,500 lbs in maximum gross weight capability, and 1,800 ft in maximum altitude are observed. Moreover, maneuvering flights can benefit from an extended chord. Required power for a steady level turn could be reduced nearly 7% at the maximum turn rate. Vibratory loads also reduce with TEP. Hub vertical shear, in-plane shear, and in-plane moment 4/rev component are reduced up to 47%, 29.6% and 51%, respectively, in a stall dominant condition. Furthermore, rotor speed variations of ±15% nominal RPM are considered in combination with TEP. Rotor speed reduction alone is most beneficial during low and light flight conditions. However, increasing rotor speed to 105% nominal RPM along with TEP offers additional 2,000 lbs payload capability, 5,000 ft gain in maximum altitude and up to 60 kts increase in maximum flight speed. |
