Computational Evaluation of Quiet Tunnel Hypersonic Boundary-Layer Stability Experiments

Manning, Melissa L.; Chokani, Ndaona

doi:10.2514/1.10698

Cited by 2 publications

(2 citation statements)

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“…The computed pressure distribution agreeed well with the experiment data for Model 93-10, while there was a slight deficiency compared to the experiment data for Model 91-6. However, the present results showed a better agreement than the Manning's computations [21].…”

Section: Numerical Results Of Laminar Flowscontrasting

confidence: 41%

“…The pressure was close to each other before and after the oblique shock, yet tail pressure on Model 91-6 was notably larger than that of 93-10 through the compression waves. Surface pressure distributions along streamwise direction are plotted in Figure 3, where (a) gives the results computed by the present work, and (b) the results obtained by Manning [21]. It is seen for the present results that the wall pressure distributions remained constant on the cones and then grew sharply on the flares.…”

Section: Numerical Results Of Laminar Flowsmentioning

confidence: 57%

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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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Section: Numerical Results Of Laminar Flowscontrasting

confidence: 41%

Section: Numerical Results Of Laminar Flowsmentioning

confidence: 57%