A solution on the F-18C for store separation simulation using Cobalt(60)

Tomaro, Robert; Witzeman, Frank C.; Strang, William Z.

doi:10.2514/6.1999-122

Cited by 18 publications

(12 citation statements)

References 9 publications

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“…The system of governing equationsis solvedby an implicit,unstructuredEuler/Navier-Stokes solver, Cobalt. 18,19 The basic algorithm is based on the Godunov's Riemann formulation and implicit time stepping to yield secondorder spatial and temporal accuracy. 20,21 The numerical procedure is developed for a cell-centered, nite volume approach and is able to accommodate a single grid system that may consist of a variety of cell types, tetrahedronand hexahedron,in three-dimensionalspace.…”

Section: Numerical Analysismentioning

confidence: 99%

Jet-Spike Bifurcation in High-Speed Flows

et al. 2001

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In recent plasma injection experiments, counter ow jet interaction has been identi ed as one of the mechanisms that signi cantly reduces the drag. There is a sudden change of the dynamic state from an oscillatory to nearly steady motion of this jet-shock interaction which depends on the relative magnitude of injection and the stagnation pressure. The shock-wavebifurcation associated with a counter ow jet from a hemispherical cylinder is investigated by a side-by-side experimental and computationaleffort. Shock-wave bifurcation has been discovered by the present experiments over the entire range of tested conditionsin the Mach 6 wind tunnel. This oscillatory motionis sustained by the upstream propagationof selectively ampli ed frequencies from the free-shear layer to the Mach disk through the embedded subsonic domain. The breakdown of this feedback loop occurs when a higher injecting jet pressure creates a supersonic zone separating the interconnecting embedded subsonic domains. Nomenclature D = total drag p = air pressure Q = conservative variables q = primitive variable r = radius of hemispheric nose T = air temperature u = velocity vector, u, v, w D = standoff distance of bow shock q = air density

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Section: Numerical Analysismentioning

confidence: 99%

Jet-Spike Bifurcation in High-Speed Flows

et al. 2001

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“…AVUS has been verified on a variety of cases, ranging from the exact Riemann problem to complex, real world problems 8,9 .…”

Section: Avus Cfd Analysismentioning

confidence: 99%

Unique Stealth Unmanned Aerial Vehicle (UAV) Houck Aircraft Design Program. Volume 2: Prototype Report

Fry¹

2008

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“…There have been several challenges for aerodynamic predictions of carriage loads and trajectories of different stores by using CFD analysis. Some of them may be listed as F-16/Generic Finned Store trajectory prediction challenge [2,3,4,5,6] , F-18/Joint Direct Attack Munition (JDAM) trajectory prediction challenge [7,8,9,10] and finally F-18C/MK-83 store transonic pressure prediction challenge for which comparisons were made with Pressure Sensitive Paint (PSP) data taken from flight tests [11] . All challenges showed that, numerical methods are mature enough to predict the store trajectories even with an Euler mesh.…”

Section: Introductionmentioning

confidence: 99%

Captive Carry Analyses and Test Results of General Purpose Munition Bomb

Basoglu

Atik

Yildiz

2011

29th AIAA Applied Aerodynamics Conference

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Prediction of aerodynamic, thermal and vibrational loadings on a store, which is carried out on an aircraft is an important criterion in the design area having the objective to define flight envelope, release envelope and life cycle of the store. External stores may change maneuverability and flight envelope of the installed flight platform drastically. On the other hand, flight envelope of the aircraft may result in an excessive heating on the electronic equipment of the store and vibration forces may end up with a structural failure. Hence, to predict aerodynamic, thermal and vibrational loadings on an external store during F4 aircraft captive carriage stage, numerical studies are carried out based on simulations and military standards. A CFD based analysis tool is used to predict the pressure variations on the store during different flight regimes of the aircraft. Fully viscous, second order structured finite volume solutions are obtained for subsonic and transonic flight regimes. Change in inner and outer temperature values of the store was determined for certain flight conditions by making the heat transfer analysis of the external store with the help of 2-D and 3-D numerical methods, including radiation, convection, conduction heat transfers and the aerodynamic heating effects. An F4 fighter aircraft is instrumented for collecting the required data to verify the analysis tools and calculated data. The results of numerical predictions are compared and verified with the test data. The comparison graphs between the estimated vibration profiles by MIL-STD 810F and measured profiles are presented. Nomenclature M = pressure probe S = thermal probe PSD = power spectral density T ∞ = free stream static temperature P ∞ = free stream static pressure H = altitude above sea level (m)  = angle of attack ( o )  = angle of sideslip ( o ) M# = Mach number T ∞ = free stream temperature P ∞ = free stream pressure

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A solution on the F-18C for store separation simulation using Cobalt(60)

Cited by 18 publications

References 9 publications

Jet-Spike Bifurcation in High-Speed Flows

Jet-Spike Bifurcation in High-Speed Flows

Unique Stealth Unmanned Aerial Vehicle (UAV) Houck Aircraft Design Program. Volume 2: Prototype Report

Captive Carry Analyses and Test Results of General Purpose Munition Bomb

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