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Lifting wing
FP was run at the conditions corresponding to AGARD WG07 TEST CASE 11, namely M∞ = 0.84,α= 3.06 deg. The ‘final step' values of the partially-conservative parameter and the artificial viscosity. The resulting pressure distribution over the wing surface is shown in. The lower surface is shock-free, whilst the upper surface exhibits features some what similar to those for TEST CASE 12. Again there is a peak suction followed by a re-compression near the leading edge, Cl and Cd a shock wave that moves forward in terms of relative chordwise position, CL , as increases. The value of predicted by FP is 0.286, and the value of is 0.0084. This value of is comparable with the values presented for the Euler solutions surveyed in Reference 6, which range from 0.258 to 0.290. The value of is also within the range of values submitted for the Euler solutions (which did not include a value from the ONERA/MATRA group), which extends from 0.0046 to 0.0251.
Fuel Distribution During operation, fuel flows from the aircraft fuel tank to the fuel-pump boost-stage inlet. The pressurised fuel from the boost stage of the engine-driven fu
Need help using FEA/FEM software (MSC Marc/Mentat) to model and analyze a system,then write a lab report about it, it is due tomorrow... anything you can do for me?
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