Correlation and analysis for SH-2F 101 rotor

The SH-2F helicopter flight test data correlation has been successfully performed using a modified version of the rotorcraft flight simulation computer program €81. This modified program has the capability for either the conventional rotor control option or the servo flap control option. The analytical model of the servo flap in the analysis is treated as a control system, not a degree of freedom. The airfoil data tables are modified to have the capability to simulate the appropriate servo flap aerodynamic coefficients Q, Q, and CM as a function of servo flap deflection. The blade index angle and servo flap control feedback coefficients are included to model the blade having various combinations of servo flap design variables. The existing SH-2F fuselage characteristics and the 101 Rotor system are utilized to perform the correlation with the flight test data to verify the analysis. Results obtained from the analysis, when compared with the flight test data, such as servo flap control position, fuselage attitude, main rotor torque, and bending moment distribution, correlate very well. From both the analysis and test data results, it is shown that the modified computer program could be a viable tool for future design of the advanced Servo flap controlled main rotor helicopter.