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![]() Steady and forced oscillation analyses will be conducted at Mach 0.7, 3° angle of attack unforced (steady) and flutter analyses will be conducted at Mach 0.74, 0° angle of attack. Using these results as a guide, cases just outside of the separated flow regime will be emphasized for AePW-2. Separation assessment was performed on the experimental data for the OTT test. Shock-induced separated flow dominates the upper surface and the aft portion of the lower surface at the Mach 0.85, 5° angle of attack cases that were simulated. The flow conditions used for AePW-1 were challenging. The test conditions for the workshop have been chosen to capture increasing complexities. The model has geometric simplicity, and the test conditions are such that the flow field has demonstrated complexities. The Benchmark Supercritical Wing (BSCW) was chosen as the configuration for the workshop. ![]() Differences between the two experiments are listed in the Experiment Differences table. ![]() Please note that the test medium is not air- it is a different heavy gas for each of the two tests due to facility modifications to the Transonic Dynamics Tunnel that occurred in 1996. Analysis input parameters are given in the Analysis Parameters table. There is experimental data to compare to each of these rigid wing solutions. For each simulation, comparing the unforced system rigid solution is also desired. Forced pitching oscillation data will be generated at a set of specified frequencies.įor each of the cases, the dynamic data type is listed in the AePW-2 Test Cases table. The steady data will be compared using pressure coefficients and integrated loads. Steady data will be generated at a fixed Mach number and angle of attack combination. Workshop simulations will include three types of data, involving three types of computations.
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