03135nam a2200397Ii 4500102893581MiAaHDL20250726000000.0m d cr bn ---auaua220427s1997 ohua bt f000 0 eng d(MiU)99187625267006381sdr-miu.99187625267006381(OCoLC)1312742692(GWLA)gwla on1312742692TRAALengrdaTRAALMAIND 301.45/57: 96-3061Josyula, Eswar,author.Computations of supersonic vortical flows around ogive-cylinders using central and upwind differences /Eswar Josyula.Wright-Patterson Air Force Base, Ohio :Flight Dynamics Directorate, Wright Laboratory, Air Force Materiel Command, United States Air Force,1997.xii, 39 pages :illustrations ;28 cm.texttxtrdacontentunmediatednrdamediavolumencrdacarrierAFWAL-TR (Air Force Wright Aeronautical Laboratories) ;96-3061"Final report for 1 July 1994 - 1 March 1996.""March 1997."Includes biblliographic references (pages 19-20).This work is part of a cooperative research, development, test and evaluation program that brings scientists and engineers from various English-speaking countries together for collaborative studies to improve technology to solve technical problems. The current TTCP work project WTP-2 KTA 2-12, 'Application of CFD to the prediction of Missile Body Vortices' focuses on the ability of the three-dimensional Navier-Stokes equations to predict flowfields about high length-to-diameter bodies at moderate angles of attack (8 deg <a <14 deg) for supersonic Mach numbers. This report documents this author's computational results for the five test cases. The five test cases are as follows. Mach 1.45 at a = 14 deg, Mach 1.8 at a = 14 deg, Mach 2.5 at a = 14 deg, Mach 3.5 at a = 8 deg, and Mach 3.5 at a = 14 deg. The experimental body is 13 diameters long with the diameter of the cylindrical afterbody of 3.7 inches. Laminar and turbulent computations are shown with comparisons to experimental data. The experimental validation data was provided by the Defence Research Agency (UK). The computations were performed with an existing Navier-Stokes code FDL3DI developed in the Wright Laboratory. The surface pressure and pitot pressure predictions matched with the experimental data reasonably well. The k-e turbulence model was found to be highly dissipative for capturing vortical flows. Local grid refinement was considered to be an important aspect of capturing the vortical flows accurately.Mode of access: Internet.Guided missilesAerodynamics.Aerodynamics, Supersonic.Computational fluid dynamics.Whirlwinds.Wright Laboratory (Wright-Patterson Air Force Base, Ohio),issuing body.Technical Report Archive & Image Library (TRAIL)3901510497564710289358120220802102019.020250726000000.020260226140657.02026-02-27T08:48:51Z2024-08-17T17:30:02ZSDR-MIUmiuALMAprepare.pl-004-009BKsdr-miu.99187625267006381MiUSDRGWLAmdp.39015104975647MIU99187625267006381MIUGWLA20260227googlemdp.390151049756471997pdbibUS fed doc