Aerodynamic Analysis of Rotor Blades using Overset Grid with Parallel Computation
The helicopter aerodynamics is simulated in hovering and forwarding flight using the unsteady Euler equations. As the steady condition, flight test of DLR-F6 and hovering flight test data of Caradonna & Tung’s rotor blades were used, and as the unsteady condition, non-lift forwarding flight test data of the rotor blades were used. The parallelized numerical solver was validated with the two of data above. By using this solver, AH-1G rotor blades to forwarding flight numerical test were conducted. In the test of forwarding flight, the numerical trim was applied to decide cyclic pitching angles using the Newton-Raphson method, and the results were good well match to the experimental data, Especially, the BVI effects were well simulated in advancing side in comparison with other numerical results. To consider the blade motion and moving effects, an overset grid technique is applied and for the boundary, Riemann invariants condition is used for inflow and outflow.
Key wordsOverset Grid Helicopter Rotor Hovering Flight Forward Flight
Unable to display preview. Download preview PDF.
- 1.Eugene Kim, J. H. Kwon and S. H. Park, ” Parallel Performance Assessment of Moving Body Overset Grid Application on PC Cluster”, pp59-66, Parallel Computational Fluid Dynamics-Parallel Computing and Its Applications 2007.Google Scholar
- 3.Y. Kim, S. H. Park and J. H. Kwon, ”Drag Prediction of DLR-F6 Using the Turbulent Navier-Stokes Calculations with Multigrid,” AIAA Paper 2004-0397, 42nd Aerospace Science Meeting and Exhibit, Reno, NV, Jan. 2004.Google Scholar
- 4.F. X. Caradonna and C. Tung, ”Experimental and Analytical Studies of a Model Helicopter Rotor in Hover,” NASA TM-81232, Sep. 1981.Google Scholar
- 5.F. X. Caradonna, F. X., G. H. Laub and C. Tung, ”An Experimental Investigation of the Parallel Blade-Vortex Interaction,” NASA TM-86005, 1984.Google Scholar
- 6.J. L. Cross and M. E. Watts, ”Tip Aerodynamics and Acoustics Test: A Report and Data Survey,” NASA-RP-1179, NASA Ames Research Center, Dec. 1988.Google Scholar
- 7.K. H. Chung, C. J. Hwang, Y. M. Park, W. J. Jeon and D. J. Lee, ” Numerical Predictions of Rotorcraft Unsteady air-loadings and BVI noise by using a time-marching free-wake and acoustic analogy”, 31th European Rotorcraft Forum, 2005.Google Scholar
- 10.W. K. Anderson, J. L. Tomas, and B. Van Leer, ”Comparison of Finite Volume Flux Vector Splittings for the Euler Equations,” AIAA Journal, Vol. 24, No. 9, pp. 1453-1460. 1986.Google Scholar
- 12.K. W. Cho, J. H. Kwon, and S. Lee., ”Development of a Fully Systemized Chimera Methodology for Steady/Unsteady Problems”, Journal of Aircraft, Vol. 36, No. 6, pp. 973-980, Nov. Dec. 1999Google Scholar