Numerical solutions of forward-flight rotor flow using an upwind method

Chung-Lung Chen, W. J. McCroskey, S. Obayashi

Research output: Contribution to conferencePaperpeer-review

7 Scopus citations

Abstract

A finite-volume upwind algorithm for solving the 3-D Euler equations with a moving grid has been developed for computing helicopter forward-flight rotor flows. The computed pressure distributions and shock positions of high-speed rotor flow are compared with various experimental data as well as with other numerical results, and the agreement is encouraging. A comparison of quasi-steady solutions with unsteady solutions reveals that when a shock occurs in the flowfield, the assumption of quasi-steady flow may fail due to the time-lag of the shock motion. Similarly, three-dimensional effects cannot be neglected. Sufficient subiterations for each time step are required to avoid numerical lag effects in using the present method. The redistribution of the residual due to the coordinate transformation is discussed. For high-order MUSCL-type schemes, a coordinate-independent solution can be obtained by interpolating primitive variables.

Original languageEnglish
DOIs
StatePublished - 1 Jan 1989
EventAIAA 20th Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1989 - Buffalo, United States
Duration: 12 Jun 198914 Jun 1989

Conference

ConferenceAIAA 20th Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1989
CountryUnited States
CityBuffalo
Period12/06/8914/06/89

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