Steady high-Reynolds-number flowfields about a finite-span rectangular wing mounted upright in a supersonic stream were generated numerically to investigate formation of the tip vortex. Solutions were obtained by integration of the time-dependent three-dimensional compressible Euler and thin-layer laminar and mass-averaged turbulent Navier-Stokes equations. In the turbulent case, a two-equation (kappa-epsilon) closure model was employed, which included low-Reynolds-number terms and a compressibility correction. Details of the computations are summarized, and a grid resolution study is provided to assess the accuracy of the numerical results. Comparisons are made between solutions of the various governing equations, as well as with experimental data in terms of pressure and Mach-number component distributions in the vortex core.
Numerical investigation of supersonic wing-tip vortices
Numerische Untersuchung der an den Flügelspitzen gebildeten Überschallwirbel
AIAA Journal ; 34 , 6 ; 1203-1208
1996
6 Seiten, 13 Bilder, 2 Tabellen, 35 Quellen
Article (Journal)
English
Überschallströmung , Wirbelströmung , Tragflügelumströmung , Rechteck , Strömungsvorgang , Integration (Mathematik) , kompressible Strömung , Euler-Gleichung , laminare Strömung , turbulente Strömung , Navier-Stokes-Gleichung , Reynolds-Zahl , Kompressibilität , Maschennetz , Genauigkeit , Druckverteilung , Wirbelkern , Geschwindigkeitsverteilung , Finite-Differenz-Methode , Dissipation , Randbedingung , Lösung (Ergebnis) , sichtbare Strömung , kinetische Energie , Verfahrensvergleich , Wirbelbildung
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