42nd AIAA Aerospace Sciences Meeting and Exhibit 2004
DOI: 10.2514/6.2004-530
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Computational Study of Axisymmetric Off-Design Nozzle Flows

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Cited by 18 publications
(10 citation statements)
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References 8 publications
(3 reference statements)
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“…With 0:25, Eqs. (24) and (25) show that the diffusion coefficients will become four times smaller than the standard values when the turbulent length scale becomes very large in comparison to the potential core width, and will result in increased turbulent diffusion in such regions.…”
Section: E Variable Diffusion Modelmentioning
confidence: 96%
See 1 more Smart Citation
“…With 0:25, Eqs. (24) and (25) show that the diffusion coefficients will become four times smaller than the standard values when the turbulent length scale becomes very large in comparison to the potential core width, and will result in increased turbulent diffusion in such regions.…”
Section: E Variable Diffusion Modelmentioning
confidence: 96%
“…The SST model has been found to provide very good calculations of wall bounded flows even with highly separated regions. One example of this may be found in [25] where the SST model was found to provide the best predictions of several one-and two-equation models in the Wind code for separated nozzle flows. The details of the complete SST model are provided in [18,19], but here we only consider the outer equation set, which is in effect for jet calculations.…”
Section: B Menter Shear Stress Modelmentioning
confidence: 96%
“…For a fixed nozzle expansion ratio of 1.5, their experimental study showed the best mixing was achieved when the NPR was in the range of 1.4-1.6. In a numerical study conducted on CDN with Mach number in the range 0.9 < < 1.2 and NPR of 4 and 6, DalBello et al [15] found that the SST − model could match well with experimental measurements.…”
Section: Introductionmentioning
confidence: 96%
“…A 8 = nozzle throat area A 9 = nozzle full expansion area C fg = gross (or uninstalled) thrust coefficient = actual thrust / ideal thrust C T-D = installed thrust coefficient = (actual thrust -drag) / ideal thrust D max = vehicle outer diameter = 19 in. NPR = nozzle pressure ratio = nozzle stagnation pressure / freestream static pressure R max = vehicle outer radius R 9 = nozzle exit radius corresponding to full expansion area y+ = wall normal coordinate θ = nozzle divergence angle…”
Section: Nomenclaturementioning
confidence: 99%
“…NPR = nozzle pressure ratio = nozzle stagnation pressure / freestream static pressure R max = vehicle outer radius R 9 = nozzle exit radius corresponding to full expansion area y+ = wall normal coordinate θ = nozzle divergence angle…”
Section: Nomenclaturementioning
confidence: 99%