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x - Aerospace Computing Lab - Stanford University

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Aerodynamic Sensitivities: FLO82<br />

RAE 2822 Airfoil<br />

α = 3.0 o , M∞ = 0.70<br />

Cp<br />

1.20 0.80 0.40 0.00 -0.40 -0.80 -1.20 -1.60 -2.00<br />

+<br />

+<br />

++ +++++++++++++++++++++++++<br />

+<br />

+ + + +<br />

+<br />

+ + +<br />

+<br />

+<br />

+<br />

+<br />

+<br />

+<br />

+<br />

+<br />

+<br />

• 2D, cell-centered, finite volume Euler solver.<br />

• Multigrid.<br />

• Implicit residual smoothing.<br />

+<br />

+<br />

+<br />

+<br />

+<br />

+<br />

+<br />

+<br />

+<br />

+<br />

+ +++<br />

+<br />

+<br />

+<br />

+++ ++++++++++++++++++++++++<br />

• Artificial dissipation options: JST, CUSP, ECUSP<br />

and HCUSP.<br />

• Same numerical schemes as FLO87 and FLO107.<br />

– Joaquim Martins – January 12, 2000 – 14<br />

+ +++++ ++++++++++++++++++++++

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