PRESSURE DISTRIBUTION ACROSS THE UH-60 ROTOR RADIUS AT A FIXED SPEED

Abstract

This paper examines the pressure distribution along the radius of a UH-60 helicopter main rotor blade under steady-state conditions and a fixed RPM of 258. The analysis is based on dimensionless aerodynamic coefficients, which allows for the evaluation of local pressure differences, their gradient, and their impact on overall thrust and power parameters. A method for approximating the ΔP(r/R) function in the range of 0.3–1.0 R is proposed using polynomial and power-law models, ensuring high accuracy of description in the tip zone. The obtained results show that a decrease in the pressure gradient at the blade tips leads to a decrease in the power coefficient Cₚ while maintaining the thrust coefficient Cₜ, which corresponds to an increase in the integral efficiency index FM. The results of the study can be used to optimize blade geometry and improve the energy efficiency of propeller systems.