Comparison of measured and predicted flows through conical supersonic nozzles, with emphasis on the transonic region

Back, L. H.; Gier, H. L.; Massier, P. F.

doi:10.2514/3.3216

Cited by 75 publications

(11 citation statements)

References 7 publications

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“…The JPL (Jet Propulsion Laboratory) nozzle used had half-angles of convergence and divergence of 45° and 15°, respectively. The ratio (rc/rt) is equal to 0.625 [24][25][26][27]. In simulation, at t= 0 second the flow starts after the rupture of a diaphragm situated at the nozzle inlet that separates two regions of quiescent air.…”

Section: Results and Discusionsmentioning

confidence: 99%

Detached eddy simulation of compressible flow with rapid expanded divergent contour

Bensayah¹,

Mahfoudi²

2018

IJHT

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Due to the large number of correlations and relationships between variables and the physical phenomena involved, compressible flow simulations become very difficult or impossible if all the necessary scales and mechanisms are included and solved. Several research efforts have been made toward a more accurate flow field predictions and the current study aims to add to that knowledge base by exploring the capability of Delayed Detached Eddy Simulation employing the SST turbulence model to simulate the transonic region of over-expanded nozzle with small radius of curvature. An analysis was made of the transonic flow in axisymmetric nozzle, the paper shows the potential for using DES turbulence model to identify important internal radial flow downstream the throat region, where most RANS models fail to predict with high accuracy and in detail the structure of the flow. With small radius of curvature, the sonic line begins upstream of the throat and ends downstream due to turning flow near the wall transonic region. Comparison of the computational results with experimental data and some developed prediction methods are presented and good agreements are obtained.

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Section: Results and Discusionsmentioning

confidence: 99%

Detached eddy simulation of compressible flow with rapid expanded divergent contour

Bensayah¹,

Mahfoudi²

2018

IJHT

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“…Provided that Ru is not less than about 2 (nozzle of fig. 1), the computation and existing 2-D flow theories [22][23][24] adequately predict the transonic flow field as indicated by the wall static pressure calculation and measurements [4] However, for nozzles with tighter throats (Ru < 1), such as are found in some rocket engines, these theories do not apply. This configuration presents some internal flow in the transonic region of a nozzle with a small ratio of Ru = 0.625.…”

Section: Validation Of Sst-v Turbulence Modelmentioning

confidence: 92%

“…It is to be clarified by which parameters the compressible turbulent boundary-layer and the heat transfer through it is influenced. A few authors have been already worked on that problem [4][5][6][7][8], but there is no systematically investigation referring to whole phenomena and suitable methods are still missing. To full part of this gap we try in this study to investigate numerically the heat transfer associated with the turbulent flow of heated air through a converging-diverging nozzle.…”

Section: Introductionmentioning

confidence: 99%

Numerical prediction of compressible heat flow with complex wall temperature in supersonic rocket nozzles

Bensayah¹,

Mahfoudi²

2018

THERM SCI

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Wall heat transfer coefficients and static wall pressures are determined over wide ranges of stagnation pressures and stagnation temperatures under large pressure gradients in a cooled convergent-divergent nozzle. The effects of specific heat ratio, turbulent Prandtl number and wall temperature value on the heat transfer and on the position of separation flow are not yet discussed accurately. Computing correct boundary-layer under adverse pressures gradients is of a particular importance to the accurate modeling of separated flow. This numerical investigation is conducted to assess the accuracy of the SST-V turbulence model when computing boundary-layer separation in supersonic nozzle with heat transfer. It is concluded that the wall heat transfer coefficients and the position of separation point are influenced by the variation of many parameters as heat specific ratio, wall temperature, and turbulent Prandtl number.

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“…The empirical constants in the equations (4), (5) and 6are given by Rodi [19] and Kays and Moffat [13]: Numerous modifications of two-equation turbulence models to account for compressibility effects are given in the literature (i.e. [11], [9], [12]).…”

Section: Heat Transfer Calculationsmentioning

confidence: 99%

“…The free-stream boundary conditions for k and a are calculated with the Eqs. (5) and (6) neglecting the gradients in the y-direction. The resulting ordinary differential equations for k. and e_ are integrated in the x-direction.…”

Section: Boundary Conditionsmentioning

confidence: 99%

Comparison of Calculated and Measured Heat Transfer Coefficients for Transonic and Supersonic Boundary-Layer Flows

Hurst

Schulz

Wittig

1994

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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The present study compares measured and computed heat transfer coefficients for high speed boundary layer nozzle flows under engine Reynolds-number conditions (U∞ = 230 ÷ 880 m/s, Re* = 0.37 ÷ 1.07 · 106). Experimental data have been obtained by heat transfer measurements in a two-dimensional, non-symmetric, convergent-divergent nozzle. The nozzle wall is convectively cooled using water passages. The coolant heat transfer data and nozzle surface temperatures are used as boundary conditions for a three-dimensional finite-element code which is employed to calculate the temperature distribution inside the nozzle wall. Heat transfer coefficients along the hot gas nozzle wall are derived from the temperature gradients normal to the surface. The results are compared with numerical heat transfer predictions using the low Reynolds-number k-ε turbulence model by Lam and Bremhorst. Influence of compressibility in the transport equations for the turbulence properties is taken into account by using the local averaged density. The results confirm that this simplification leads to good results for transonic and low supersonic flows.

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Comparison of measured and predicted flows through conical supersonic nozzles, with emphasis on the transonic region

Cited by 75 publications

References 7 publications

Detached eddy simulation of compressible flow with rapid expanded divergent contour

Detached eddy simulation of compressible flow with rapid expanded divergent contour

Numerical prediction of compressible heat flow with complex wall temperature in supersonic rocket nozzles

Comparison of Calculated and Measured Heat Transfer Coefficients for Transonic and Supersonic Boundary-Layer Flows

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