Skin-friction measurements and calculations on a lifting airfoil

Mateer, G. G.; Monson, D. J.; Menter, F. R.

doi:10.2514/3.13055

Cited by 47 publications

(11 citation statements)

References 10 publications

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“…For all of these one-element airfoils, experimental data are available for comparison. A more challenging test case was the one-element airfoil investigated by Mateer et al [22,23]. Here, the application of the -Re t transition model became more complicated, caused by the relatively high freestream turbulence intensity.…”

mentioning

confidence: 98%

“…Here, the application of the -Re t transition model became more complicated, caused by the relatively high freestream turbulence intensity. To overcome these problems, an approach of Mateer et al [22] was considered, which avoids the decay of turbulent quantities in the far field below a certain limit. The results are compared with the standard transition prediction approach in the TAU code.…”

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confidence: 99%

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Evaluation of a Correlation-Based Transition Model and Comparison with the eN Method

Seyfert

Krumbein

2012

Journal of Aircraft

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The correlation-based -Re t transition transport model has been implemented into a hybrid Reynolds-averaged Navier-Stokes solver and evaluated on various test cases. The original model formulation and recently published approaches of different authors for relevant empirical model functions as well as different transition criteria are compared. The prediction of transition with the correlation-based model was applied to a zero pressure gradient flat plate test case and some well-known one-element airfoil test cases. A comparison with the standard approach for transition prediction in the flow solver used based on the e N method was accomplished. The simulation results in terms of transition locations and skin-friction coefficient distributions, performance, and limiting factors of both transition prediction methods for the various test cases are presented and discussed.function that controls the transition length k = turbulent kinetic energy k amb = lower bound for turbulent kinetic energy in the far field M = Mach number N = critical N factor Re x = Reynolds number based on axial coordinate x Re c = Reynolds number based on momentum thickness, critical Re t = Reynolds number based on momentum thickness at transition onset Re = Reynolds number based on momentum thickness Re = Reynolds number based on vorticity Tu = local turbulence intensity Tu 0 = turbulence intensity at the far-field boundary Tu 1 = freestream turbulence intensity U = local velocity x = axial coordinate y = distance in wall coordinates = angle of attack = model constant for the shear-stress transport k-! turbulence model = model constant for the supersonic transport k-! turbulence model = intermittency = molecular viscosity t = eddy viscosity = density ! = specific turbulent dissipation rate ! amb = lower bound for turbulent dissipation rate in the far field

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confidence: 98%

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confidence: 99%

Evaluation of a Correlation-Based Transition Model and Comparison with the eN Method

Seyfert

Krumbein

2012

Journal of Aircraft

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“…8. Figure 9 compares the skin friction calculated by the present approach and the e N method with the experiment data for incompressible flow over a supercritical airfoil [48], whose configuration results in a fairly constant favorable pressure gradient on the upper surface. The present model predicts the transition-onset location much better than does the e N method although it gives slightly higher peak value in the skin friction coefficient and longer transition region.…”

Section: Resultsmentioning

confidence: 95%

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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“…Even when such onset is calculated, the interactive nature of the calculation requires an incredible amount of computer resources. As a result, the closest thing to coupling the e n method to existing Navier-Stokes solvers 5,6 is the use of the approximate integral method of Drela and Giles. 7 In addition to the preceding, e n methods or methods based on the PSE cannot provide any information on the extent of transition.…”

Section: Introductionmentioning

confidence: 99%

Study of High-Lift Configurations Using k-? Transition/Turbulence Model

Czerwiec

Edwards

Rumsey

et al. 2000

Journal of Aircraft

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The ow over the multi-element McDonnell Douglas con guration is computed using the k-transition/turbulence model. The model is capable of calculating transition onset as part of the solution at a cost comparable to Navier-Stokes solvers that employ two-equation models. The model is rst incorporated into CFL3D and then used to calculate ows for two angles of attack, 8 and 19 deg, at a freestream Mach number of 0.2 and a Reynolds number of 9 £ 10 6 . In general, good agreement is indicated for predicting transition onset and velocity pro les over sections of the main airfoil and ap. Most of the differences between computation and experiment are in the prediction of the extent and penetration of the slat wake at the 19-deg angle-of-attack case. Even for this case relative differences were less than 5%.

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Skin-friction measurements and calculations on a lifting airfoil

Cited by 47 publications

References 10 publications

Evaluation of a Correlation-Based Transition Model and Comparison with the eN Method

Evaluation of a Correlation-Based Transition Model and Comparison with the eN Method

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

Study of High-Lift Configurations Using k-? Transition/Turbulence Model

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