G. Bowen-Davies, I. Chopra

The comprehensive analysis UMARC has been modified to include a model for dynamic stall in the reverse flow region for high advance ratio helicopter. The reverse flow stall model adapts the Leishman-Beddoes dynamic stall model with concepts from a flat plate in accelerating flow. The model is evaluated against airloads data from the reverse flow region of the UH-60A slowed rotor test at high advance ratios between µ = 0.4?1.0. The dynamic stall model predicts dynamic stall in the reverse flow for all the test cases, but does not have a significant impact on the advancing side of the rotor. At lower advance ratios (µ = 0.4 and 0.6), the azimuth of dynamic stall is well predicted and the correlation with the measured airloads in the reverse flow is improved. At µ = 1.0, the model predicts multiple vortex shedding, which are present in the test, but the phase agreement is not satisfactory.

41th European Rotorcraft Forum 2015

Conference Paper

englisch

21,0 x 29,7 cm, 13 Seiten

DGLR-Bericht, 2016, 2016-01, 41st European Rotorcraft Forum 2015; S.-; 2016; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aerodynamic loads;aerodynamic stalling;azimuth;flat plates;helicopters;rotors;vortex shedding

Bestellbar

2016