Development and Preliminary Assessment of the Open-Source CFD toolkit SU2 for Rotorcraft Flows

TL;DR

This paper presents the development and initial testing of the open-source SU2 CFD toolkit for rotorcraft flow analysis, demonstrating its ability to accurately predict rotor performance in hover and forward flight.

Contribution

It introduces the SU2 code for rotorcraft aerodynamics, incorporating steady and unsteady RANS models, and validates its performance predictions against experimental data.

Findings

SU2 accurately predicts rotor pressure distributions.

The code effectively models steady and unsteady rotor flows.

Validation shows good agreement with experimental measurements.

Abstract

Computational aerodynamic analyses of rotorcraft main rotor blades are performed in both hover and forward flight. The open-source SU2 code is used for rotor performance prediction. The core of the code is the set of RANS equations, which are solved for determining the flow. In hover, both steady-state and time-accurate modelling techniques of varying complexity are used and assessed. Simulation specific parameters which have a significant influence on the solution are also addressed. In forward flight, the code is developed to include the main rotor blade kinematics which is a prerequisite for modelling a trimmed rotor. Two databases are used for the validation of the rotor performance prediction. The renowned Caradonna-Tung experimental tests of a model rotor are used to evaluate the pressure distribution along the blade during hover. The extensive aerodynamic and aeroacoustic data survey of the AH-1G Cobra helicopter is used to assess the pressure distribution at different advancing and retreating azimuth angles during forward flight. The prediction capabilities of the solver in terms of rotor performance are demonstrated and are overall in good agreement with the measured data.