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Automated CFD for Generation of Airfoil Performance Tables
 Created on Sunday, 01 November 2009
A method of automated computational fluid dynamics (CFD) has been invented for the generation of performance tables for an object subject to fluid flow. The method is applicable to the generation of tables that summarize the effects of twodimensional flows about airfoils and that are in a format known in the art as “C81.” (A C81 airfoil performance table is a text file that lists coefficients of lift, drag, and pitching moment of an airfoil as functions of angle of attack for a range of Mach numbers.) The method makes it possible to efficiently generate and tabulate data from simulations of flows for parameter values spanning all operational ranges of actual or potential interest. In so doing, the method also enables filling of gaps and resolution of inconsistencies in C81 tables generated previously from incomplete experimental data or from theoretical calculations that involved questionable assumptions.
The method can be implemented by use of any of a variety of digital processors comprising hardware and software subsystems capable of simulating flows. The hardware subsystem could be, for example, a microprocessor, a mainframe computer, a digital signal processor, or a portable computer. The software subsystem can include any of a number of flow solvers — that is, computer programs that solve the governing equations of flow. One such program that is particularly suitable for use in this method is ARC2D, which utilizes finitedifference techniques to numerically solve the Reynoldsaveraged NavierStokes equations of twodimensional compressible flow.
At the beginning of a process using this method, the processor receives a description of the airfoil and a preinput file, which contains parameters representative of the ranges of flow conditions in which the airfoil is to be tested via computational simulations. The processor can perform steadystate and/or timeaccurate calculations for simulating flows. Steadystate calculations are typically applicable to such conventional flow conditions as small angles of attack with fully attached flows for which the solutions are independent of time. Timeaccurate calculations model the temporal behaviors of timevarying flows.
The upper part of the figure illustrates steadystate calculations according to this method. After reading the preinput file, the processor determines whether the steadystate calculations specified by that file have been completed. If the calculations have not been completed, the processor generates a flowsolver input file, then the processor executes the flow solver using this input file. If the output of the flow solver includes a negative density or pressure, which is physically impossible, then the pseudotime step used in the flow solver is reduced and the flow solver is run again using the same inputs. This subprocess is repeated, if necessary, until neither the pressure nor the density in the output of the flow solver is negative, at which point the output of the flow solver is concatenated into an output file. Next, the processor analyzes the residual history of forces and pitching moments and increments the run count. The processor then returns to the step in which it determines whether the steadystate calculations have been completed. If the calculations are found to have been completed, the processor determines whether satisfactory results were obtained. If satisfactory results were not obtained, the processor switches to timeaccurate mode.
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