Transition onset prediction for high speed flow

McDaniel, Ryan; Hassan, H. A.; Nance, Robert P.

doi:10.2514/6.1999-3792

Cited by 7 publications

(18 citation statements)

References 13 publications

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“…Thus far, Tollmien-Schlichting, crossflow, and second-mode mechanisms have been implemented into the model, with generally good results having been achieved for a variety of flowfields. [1][2][3][4] , This paper reports on the application" of these ideas to one-equation "eddy viscosity transport" turbulence models. Initial attention is focused on the popular Spalart-Allmaras oneequation model, [6] but the procedures as developed should be applicable to other models of this type.…”

Section: Introductionmentioning

confidence: 99%

“…Earlier works [1][2][3][4] have detailed the development of a unified modeling approach for transitional / turbulent flows based on the combination of the k -~turbulence model [5] with a model for non-turbulent fluctuation growth. [1,2] Linear stability theory is used to guide the modeling of the non-turbulent fluctuation growth process which leads to transition.…”

Section: Introductionmentioning

confidence: 99%

“…If second-mode mechanisms are included, the constant b is assigned a value of 0.06, slightly Klgher than the range of values used in Ref. 3 (0.053 to 0.056). Otherwise, b is set to zero.…”

mentioning

confidence: 99%

“…In this, W1represents the frequency of the firstmode disturbance having the maximum amplification rate and is correlated as a function of surface distances by the following [3]:…”

mentioning

confidence: 99%

“…To account for compressibility effects, the kinematic viscosity v. in Eq. 5 is evaluated at a reference temperature Z'*, defined as [3] …”

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confidence: 99%

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Development of one-equation transition/turbulence models

Edwards

Roy

Blottner

et al. 2000

38th Aerospace Sciences Meeting and Exhibit

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This paper reports on the development of a unified one-equation model for the prediction of transitional and turbulent flows. Am eddy viscosity -transport equation for nonturbulent fluctuation growth based on that proposed by Warren and Hassan (Journal of Aircraft, Vol. 35,No. 5 . 20, 1999equations is accomplished through a multidimensional intermittence function based on the work of Dhawan and Narasimha (Journal of Fluid Mechanics, Vol. 3,No. 4).. The model predicts both the onset and extent of transition. Lowspeed test cases include transitional flow over a flat plate, a single element airfoil, and a multielement airfoil in landing configuration. Highspeed test cases include transitional Mach 3.5 flow over a 5°cone and Mach 6 flow over a flaredcone configuration. Results are compared with experimental data, and the grid-dependence of selected predictions is analyzed.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

“…If second-mode mechanisms are included, the constant b is assigned a value of 0.06, slightly Klgher than the range of values used in Ref. 3 (0.053 to 0.056). Otherwise, b is set to zero.…”

mentioning

confidence: 99%

“…In this, W1represents the frequency of the firstmode disturbance having the maximum amplification rate and is correlated as a function of surface distances by the following [3]:…”

mentioning

confidence: 99%

“…To account for compressibility effects, the kinematic viscosity v. in Eq. 5 is evaluated at a reference temperature Z'*, defined as [3] …”

mentioning

confidence: 99%

See 3 more Smart Citations

Development of one-equation transition/turbulence models

Edwards

Roy

Blottner

et al. 2000

38th Aerospace Sciences Meeting and Exhibit

Self Cite

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Development of an Intermittency Equation for the Modeling of the Supersonic/Hypersonic Boundary Layer Flow Transition

Wang

2011

Flow Turbulence Combust

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An intermittency transport equation is developed in this study to model the laminar-turbulence boundary layer transition at supersonic and hypersonic conditions. The model takes into account the effects of different instability modes associated with the variations in Mach numbers. The model equation is based on the intermittency factor γ concept and couples with the well-known SST k-ω eddyviscosity model in the solution procedures. The particular features of the present model approach are that: (1) the fluctuating kinetic energy k includes the nonturbulent, as well as turbulent fluctuations; (2) the proposed transport equation for the intermittency factor γ triggers the transition onset through a source term; (3) through the introduction of a new length scale normal to wall, the present model employs the local variables only avoiding the use of the integral parameters, like the boundary layer thickness δ, which are often cost-ineffective with the modern CFD methods; (4) in the fully turbulent region, the model retreats to SST model. This model is validated with a number of available experiments on boundary layer transition including the incompressible, supersonic and hypersonic flows past flat plates, straight/flared cones at zero incidences, etc. It is demonstrated that the present model can be successfully applied to the engineering calculations of a variety of aerodynamic flow transition with a reasonably wide range of Mach numbers.

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A Favré averaged transition prediction model for hypersonic flows

Song

Lee

2010

Sci. China Technol. Sci.

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Transition prediction is crucial for aerothermodynamic and thermal protection system design of hypersonic vehicles. The compressible form of laminar kinetic energy equation is derived based on Favré average formality in the present paper. A closure of the equation is deduced and simplified under certain hypotheses and scaling analysis. A laminar-to-turbulent transition prediction procedure is proposed for high Mach number flows based on the modeled Favré-averaged laminar kinetic energy equation, in conjunction with the Favré-averaged Navier-Stokes equations. The proposed model, with and without associated explicit compressibility terms, is then applied to simulate flows over flared-cones with a free-stream Mach number of 5.91, and the onset locations of the boundary layer transition under different wall conditions are estimated. The computed onset locations are compared with those obtained by the model based on a compressibility correction deduced from the reference-temperature concept, together with experimental data. It is revealed that the present model gives a more favorable transition prediction for hypersonic flows. transition prediction, laminar fluctuation, hypersonic, compressibility Citation: Song B, Lee C H. A Favré averaged transition prediction model for hypersonic flows.Boundary layer transition profoundly affects the aerodynamic and thermal characteristics of hypersonic vehicles, thus the transition prediction is crucial for aerothermodynamic and thermal protection system design [1]. Although stability and transition of boundary layers of supersonic and hypersonic speeds has been studied for a century, no comprehensive theory on boundary layer transition process is established, especially for hypersonic flows for their extreme complexity. Transition is influenced by many factors, such as the local Mach number, Reynolds number per unit length, pressure gradients, nosetip bluntness (including the entropy swallowing effects), crossflow effects, surface roughness, wall cooling, suction and blowing effects, even high temperature/nonequilibrium effects if the flow is pyrochemical [2]. The effects of these factors are coupled and difficult to analyze.Among the common engineering approaches for transition prediction, the e N method can describe the initial linear growing stage of small disturbances reliably, but it is unable to cover the entire course of the transition. Furthermore, it is impossible to correlate the experiment data with a unique N for hypersonic flows. The empirical formulations are relatively simple and easy to execute, but each of them is restricted within certain types of flows, and can not function universally. For example, the criterion Re θ /M e = constant deduced from hypersonic flights was proven to fail when it is used to correlate the wind tunnel data [3]. Transition criteria based on the skin friction and heat transfer rate distributions are affected by the quality of computational grids near the wall, yet they are not applicable under the presence of pressure gradients.Numerica...

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Transition onset prediction for high speed flow

Cited by 7 publications

References 13 publications

Development of one-equation transition/turbulence models

Development of one-equation transition/turbulence models

Development of an Intermittency Equation for the Modeling of the Supersonic/Hypersonic Boundary Layer Flow Transition

A Favré averaged transition prediction model for hypersonic flows

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