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41st Aerospace Sciences Meeting and Exhibit
The low-speed, laminar flowfield for a 70 o -sweep delta wing is investigated. Solutions to the unsteady, three-dimensional, compressible Navier-Stokes equations were obtained on an unstructured grid to match results from an experiment performed in a water tunnel. The experiment was conducted with the delta wing at an angle of attack of 35 o and the freestream flow at a root-chord Reynolds number of 40,700. The computational results are analyzed and compared with the experimental results indoi:10.2514/6.2003-1102 fatcat:gkoqpq6azjdkbn7ymayzfnqfzm