Predicted aerodynamics for a proposed personnel launch vehicle

Greene, Francis A.; Weilmuenster, K. J.; Micol, John R.

doi:10.2514/6.1990-1668

Cited by 11 publications

(4 citation statements)

References 5 publications

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“…28), HL-20 (Ref. 29), Space Shuttle, 30¡32 and Reentry-F. 33 For all of the results containedwithin, LAURA was run assuming air to behave as a perfect gas, and the full Navier-Stokes equations were slightly simpli ed via the thin-layer assumption (see Ref. 34 for rationale).…”

Section: Methodsmentioning

confidence: 99%

Computational Aeroheating Predictions for X-34

Kleb

Wood

Gnoffo

et al. 1999

Journal of Spacecraft and Rockets

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Section: Methodsmentioning

confidence: 99%

Computational Aeroheating Predictions for X-34

Kleb

Wood

Gnoffo

et al. 1999

Journal of Spacecraft and Rockets

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“…The vector h under the thinlayer assumption is (7) where and = Hr hr+ *-*-«* [vx-n] 4i = (8) (9) Provisions in the code allow these thin-layer terms to be included in any of the computational directions (x = £, 17, or f). The variable s represents a Cartesian coordinate (s == x, y, z), and v. the corresponding Cartesian velocity (v = w,v,w).…”

Section: Governing Equationsmentioning

confidence: 99%

“…7, was extended to include the effects of viscosity. The viscous predictions are based on the thin-layer Navier-Stokes equations, with the shear stress and heat flux terms incorporated as documented in Ref.…”

Section: Governing Equationsmentioning

confidence: 99%

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Viscous equilibrium computations using program LAURA

Greene

Gupta

1992

Journal of Spacecraft and Rockets

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Modifications have been made to the Langley Aerothermodynamic Upwind Relaxation Algorithm (LAURA) that enable it to compute viscous airflows under the assumption of thermal and chemical equilibrium. Equilibrium thermodynamic and transport property information are input to the code via curve fits. The periodic updating of this information enables the equilibrium algorithm to perform at a computational rate that is only a small percentage larger than the rate associated with the perfect-gas algorithm. Presented in this article are the results of the initial validation of the modified code. Solutions for surface pressure and heating are presented for the flow over slender and blunt cones at realistic re-entry conditions. LAURA solutions are compared with those produced by a viscous shock-layer method, and, for one case considered, with heat transfer data from a flight experiment. For both pressure and heating, the agreement is good. In general, differences in pressures of a few percent were noted, while differences in heating rates were in the 5-10% range. NomenclatureA = Jacobian matrix of g with respect to q B -Jacobian matrix of h with respect to q E = total energy per unit mass, J/kg e = internal energy per unit mass, J/kg g = inviscid flux vector H = total enthalpy per unit mass, J/kg h = enthalpy per unit mass, J/kg h = viscous flux vector 7 = identity matrix M -right eigenvector matrix of A M~l = left eigenvector matrix of A n = outward unit normal vector of a cell face Pr = total Prandtl number p = pressure, N/m 2 Re = freestream Reynolds number Rn -nose radius, m S = arc length distance along symmetry plane, m t -time, s U = contravariant velocity normal to a cell face u = velocity component in x direction, m/s V = velocity vector, m/s v = velocity component in y direction, m/s w = velocity component in z direction, m/s 7 = h/e \ = eigenvalue matrix of A IJL = viscosity, N-s/m 2 p = density, kg/m 3 a = cell face area, m 2 12= cell volume, m 3

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Rapid Supersonic/Hypersonic Aerodynamics Analysis Model for Arbitrary Geometries

Lobbia

2017

Journal of Spacecraft and Rockets

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Predicted aerodynamics for a proposed personnel launch vehicle

Cited by 11 publications

References 5 publications

Computational Aeroheating Predictions for X-34

Computational Aeroheating Predictions for X-34

Viscous equilibrium computations using program LAURA

Rapid Supersonic/Hypersonic Aerodynamics Analysis Model for Arbitrary Geometries

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