Numerical solution of the azimuthal-invariant thin-layer Navier-Stokes equations

Nietubicz, Charles J.; Pulliam, Thomas H.; Steger, J. L.

doi:10.2514/6.1979-10

Cited by 31 publications

(13 citation statements)

References 3 publications

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“…Figure 2 shows the notation for the Cartesian coordinates x,y,z, the cylindrical coordinates x,Φ,R and the transformed coordinates ξ,η,ζ where ξ,η and ζ represent the longitudinal, the circumferential and the near normal coordinates, respectively. The transformed axisymmetric thin-layer Navier-Stokes equations can be written as 18 …”

Section: Axisymmetric Thin-layer Navier-stokes Equationsmentioning

confidence: 99%

“…To overcome these difficulties, an implicit diagonalized symmetric Total Variation Diminishing (TVD) scheme 15,16 , accompanied by a suitable grid 17 , is employed to solve the thin-layer axisymmetic Navier-Stokes equations 18 coupled with the Baldwin-Lomax turbulence model 19 . The linearized conservative implicit (LCI) form of TVD scheme 20 is adopted in this study.…”

Section: Introductionmentioning

confidence: 99%

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Computations of aerodynamic drag for spinning transonic projectiles using an implicit TVD scheme

1995

Engineering Computations

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Section: Axisymmetric Thin-layer Navier-stokes Equationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Computations of aerodynamic drag for spinning transonic projectiles using an implicit TVD scheme

1995

Engineering Computations

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“…An earlier time-marching code, which has been used to perform base flow computations including mass injection in the base region, is an extension of the azimuthal-invariant code. 4 This code is fully implicit and centrally differenced and uses the approximate factorization of Beam and Warming. 5 Projectile spin is allowed through the azimuthal-invariant assumptions.…”

Section: Codesmentioning

confidence: 99%

Applications of computational fluid dynamics to the aerodynamics of army projectiles

Sturek

Nietubicz

Sahu

et al. 1994

Journal of Spacecraft and Rockets

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The ability to predict the complete set of aerodynamic performance parameters for projectile configurations is the goal of the computational aerodynamicists at the U.S. Army Research Laboratory. To achieve this goal, predictive capabilities that use Navier-Stokes computational techniques have been developed and applied to an extensive number of projectile configurations. A summary of code validation efforts and applications for both spin-stabilized and fin-stabilized projectile configurations are described. Significant progress in the predictive capability for projectile aerodynamics has been achieved through the availability of substantial supercomputer resources and modern computational techniques. Current and future research areas of interest are described and provide an indication of computer resources and code enhancements needed to continue the progress in projectile computational aerodynamics. NomenclatureMagnus (side) force coefficient D =reference diameter of model, m d = local diameter of model, m / =mass injection parameter, / L =length, m M =Mach number m =mass flow rate of injected gas p/w/A, P =pressure normalized by p^2 (also spin rate, rad/s) PD/V =nondimensional spin rate Re = Reynolds number T = temperature, K u = velocity component in the x direction, m/s V =freestream velocity, m/s v = velocity component in the y direction, m/s x,y,z -Cartesian coordinates a = angle of attack, deg p = density, normalized by pĈ D = axial spin rate, rad/s

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“…Therefore, accurate prediction of these phenomena is of practical importance. Nietubicz, et al (1980) obtained the numerical solution of thin-layer Navier-Stokes equations for transonic flows over axisymmetric slender body. This is regarded as a pioneering work which enables Navier-Stokes analysis for flows on transonic projectiles.…”

Section: Introductionmentioning

confidence: 99%

Assessment of reynolds stress turbulence closures in the calculation of a transonic separated flow

Kim

Son

Cho

2001

KSME International Journal

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In this study, the performances of various turbulence closure models are evaluated in the calculation of a transonic flow over axisymmetric bump, k-€, explicit algebraic stress, and two Reynolds stress models, i. e., GL model proposed by Gibson & Launder and SSG model proposed by Speziale, Sarkar and Gatski, are chosen as turbulence closure models. SSG Reynolds stress model gives best predictions for pressure coefficients and the location of shock. The results with GL model also show quite accurate prediction of pressure coefficients downstream of shock wave. However, in the predictions of mean velocities and turbulent stresses, the results are not so satisfactory as in the prediction of pressure coefficients.

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Numerical solution of the azimuthal-invariant thin-layer Navier-Stokes equations

Cited by 31 publications

References 3 publications

Computations of aerodynamic drag for spinning transonic projectiles using an implicit TVD scheme

Computations of aerodynamic drag for spinning transonic projectiles using an implicit TVD scheme

Applications of computational fluid dynamics to the aerodynamics of army projectiles

Assessment of reynolds stress turbulence closures in the calculation of a transonic separated flow

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