Development and application of GASP 2.0

McGrory, William D.; Huebner, Lawrence D.; Slack, David C.; Walters, Robert W.

doi:10.2514/6.1992-5067

Cited by 9 publications

(2 citation statements)

References 2 publications

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“…9,10 GASP is a finite volume code capable of solving the full Reynolds-averaged Navier-Stokes (RANS) equations as well as subsets of these equations, including the parabolized NavierStokes (PNS), thin-layer Navier-Stokes (TLNS) and Euler equations. Time integration in GASP is based on the integration of primitive variables, and convergence to a steady state solution is obtained by iterating in pseudo-time until the L2 norm of the residual vector has been reduced by a sufficient amount.…”

Section: Methodsmentioning

confidence: 99%

Aerodynamic performance and flow-field characteristics of two waverider-derived hypersonic cruise configurations

Cockrell¹,

Huebner²,

Finley³

1995

33rd Aerospace Sciences Meeting and Exhibit

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The component integration of a class of hypersonic high-lift configurations known as waveriders into hypersonic cruise vehicles was evaluated. A wind-tunnel model was developed which integrates realistic vehicle components with two waverider shapes, referred to as the "straight-wing" and "cranked-wing" shapes. Both shapes were conical-flowderived waveriders for a design Mach number of 4.0. Experimental data and limited computational fluid dynamics (CFD) predictions were obtained over a Mach number range of 1.6 to 4.63 at a Reynolds number of 2.0x10 6 per foot. The CFD predictions and flow visualization data confirmed the shock attachment characteristics of the baseline waverider shapes and illustrated the waverider flow-field properties. Experimental data showed that no significant performance degradations, in terms of maximum lift-to-drag ratios, occur at offdesign Mach numbers for the waverider shapes and the integrated configurations. A comparison of the fully-integrated waverider vehicles to the baseline shapes showed that the performance was significantly degraded when all of the components were added to the waveriders, with the most significant degradation resulting from aftbody closure and the addition of control surfaces. Both fully-integrated configurations were longitudinally unstable over the Mach number range studied with the selected center of gravity location and for unpowered conditions. The cranked-wing configuration provided better lateral-directional stability characteristics than the straight-wing configuration.

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Section: Methodsmentioning

confidence: 99%

Aerodynamic performance and flow-field characteristics of two waverider-derived hypersonic cruise configurations

Cockrell¹,

Huebner²,

Finley³

1995

33rd Aerospace Sciences Meeting and Exhibit

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show abstract

“…A further illustration of the TPG code flexibility and robustness is shown by comparison with a computational fluid dynamics (CFD) Euler solution (i.e., inviscid flow) obtained using the General Aerodynamic Simulation Program (GASP) 11 . GASP solves the integral form of the governing equations, including the full time-dependent Reynolds-averaged NavierStokes equations and various subsets: the ThinLayer Navier-Stokes equations, the Parabolized Navier-Stokes equations, and the Euler equations, including a generalized chemistry model and both equilibrium and non-equilibrium thermodynamics models.…”

Section: Comparisons With Cfdmentioning

confidence: 99%

Computation of thermally perfect oblique shock wave properties

Kenneth

1997

35th Aerospace Sciences Meeting and Exhibit

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SummaryA set of compressible flow relations describing flow properties across oblique shock waves, derived for a thermally perfect, calorically imperfect gas, is applied within the existing thermally perfect gas (TPG) computer code. The relations are based upon the specific heat expressed as a polynomial function of temperature. The updated code produces tables of compressible flow properties of oblique shock waves, as well as the original properties of normal shock waves and basic isentropic flow, in a format similar to the tables for normal shock waves found in NACA Rep. 1135. The code results are validated in both the calorically perfect and the calorically imperfect, thermally perfect temperature regimes through comparisons with the theoretical methods of NACA Rep. 1135. The advantages of the TPG code for oblique shock wave calculations, as well as for the properties of isentropic flow and normal shock waves, are its ease of use and its applicability to any type of gas (monatomic, diatomic, triatomic, polyatomic, or any specified mixture thereof).

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Interpretation of waverider performance data using computational fluid dynamics

Cockrell

1994

Journal of Aircraft

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A computational study was conducted to better understand experimental results obtained from wind tunnel tests of a Mach 4 waverider model and a comparative reference configuration. The experimental results showed that the performance of the reference configuration was slightly better than that of the waverider model. These results contradict waverider design theory, which suggests that a waverider optimized for maximum lift-to-drag should provide better performance than any other non-waverider configuration at a given design point, especially at hypersonic speeds. The computational results showed that the predicted surface pressure values and the integrated lift and drag coefficients from the pressure distributions were much lower for the reference model than for the flat-top model, due to the reference model bottom surface having a slight expansion. The lift-to-drag ratios for the flat-top model were higher due to a relatively low drag for the same amount of lift. These results indicate that the performance advantage of the reference model was due to the shape of the bottom surface and not due to the flat top surface. The results also showed that the reference model exhibited the same shock attachment characteristics as the waverider because the planform shapes were identical. CFD predictions show that the planform shape gives the waverider an advantage in performance over conventional hypersonic vehicles and that altering the bottom surface of a waverider does not cause significant performance degradation.

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Development and application of GASP 2.0

Cited by 9 publications

References 2 publications

Aerodynamic performance and flow-field characteristics of two waverider-derived hypersonic cruise configurations

Aerodynamic performance and flow-field characteristics of two waverider-derived hypersonic cruise configurations

Computation of thermally perfect oblique shock wave properties

Interpretation of waverider performance data using computational fluid dynamics

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