The PARC distinction - A practical flow simulator

Cooper, G. K.; Sirbaugh, J. R.

doi:10.2514/6.1990-2002

Cited by 24 publications

(4 citation statements)

References 3 publications

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“…Calculations were performed using the NPARC finite difference code [7,8], which solves the conservation law form of the Reynoldsaveraged Navier-Stokes equations. Steady-state solutions were obtained with an approximate factorization algorithm and second order accurate central differencing for the spatial derivatives.…”

Section: Computational Algorithmmentioning

confidence: 99%

Quadrant Analysis of a Mixer-Ejector Nozzle for Supersonic Transport Applications

Yoder

Georgiadis

Wolter

2007

Journal of Propulsion and Power

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Section: Computational Algorithmmentioning

confidence: 99%

Quadrant Analysis of a Mixer-Ejector Nozzle for Supersonic Transport Applications

Yoder

Georgiadis

Wolter

2007

Journal of Propulsion and Power

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“…The code incorporates a semi-automatic time-step control function which helps to maintain the stability for the flow solution being calculated. Additional details about the code can be found in [13].…”

Section: Parc31) Codementioning

confidence: 99%

“…The screen BC and the mass BC were specified at the inlet propeller face and at the nacelle exit, respectively. Mathematical formulations of free-stream, no-slip, and mass BC's are reported in [13].…”

Section: Computational Gridmentioning

confidence: 99%

3-D viscous flow CFD analysis of the propeller effect on an advancedducted propeller subsonic inlet

Iek

Boldman

Ibrahim

1993

29th Joint Propulsion Conference and Exhibit

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A time marching Navier-Stokes code called PARC31) was used to study the 3-D viscous flow associated with an advanced ducted propeller (ADP) subsonic inlet at take-off operating conditions. At a free stream Mach number of 0.2, experimental data for the inlet-with-propeller test model indicated that the airflow was attached on the cowl windward lip at an angle of attack of 25°, became unstable at 29°, and separated at 30°. An experimental study with a similar inlet and with no propeller (through-flow) indicated that flow separation occurred at an angle of attack a few degrees below the value observed when the inlet was tested with the propeller. This tends to indicate that the propeller exerts a favorable effect on the inlet performance. During the through-flow experiment a stationary blockage device was used to successfully simulate the propeller effect on the inlet flow field at angles of attack. In the present numerical study, this flow blockage was modeled via a PARC3D computational boundary condition (BC) called the screen BC. The principle formulation of this BC was based on the one-and-half dimension actuator disk theory. This screen BC was applied at the inlet propeller face station of the computational grid. Numerical results were obtained with and without the screen BC. The application of the screen BC in this numerical study provided results which are similar to the results of past experimental efforts in which either the blockage device or the propeller was used.

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“…At the same time, management and engineers at AEDC and NASA LeRC realized that there were complementary development efforts at each Center focused on the PARC CFD code. 1 The result was the creation of the NPARC Alliance. 2 The NPARC Alliance draws on the unique talents and qualifications of its partners while at the same time soliciting the experience and insights of government, industrial, and academic users to ensure that code development proceeds in a cost-effective, customer-responsive manner.…”

Section: The Nparc Alliancementioning

confidence: 99%