CFD rebuilding of USV-DTFT1 vehicle in-flight experiment

Roncioni, Pietro; Rufolo, Giuseppe C.; Marini, Marco; Borrelli, Salvatore

doi:10.1016/j.actaastro.2009.10.015

Cited by 6 publications

(5 citation statements)

References 5 publications

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“…Sketch of the PRORA-USV vehicle (earlier shape) with top, side, front and 3-D view, [62]. The right part of this figure exhibits the vortex formations along the wing leading edge, the wing tip and the fuselage as they were predicted by a Navier-Stokes simulation of the flow field with M ∞ = 0.70, α = 10 • , Re = 6.5 · 10 6 , [67,68] [62,66]. 6.140 (left), [61,62].…”

Section: Aerodynamic Data Of Steady Motionmentioning

confidence: 99%

Aerodynamic Data of Space Vehicles

Weiland¹

2014

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Section: Aerodynamic Data Of Steady Motionmentioning

confidence: 99%

Aerodynamic Data of Space Vehicles

Weiland¹

2014

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“…[1][2][3] Similar applications are not easy to find in the literature, since all the tools developed at industrial level are hardly ever published with sufficient details.…”

Section: Introductionmentioning

confidence: 95%

“…CIRA have a past experience in the generation of engineering database tools, with the work performed in the frame of the USV national program, where the tools have been also partially validated by flight data. [1][2][3] Similar applications are not easy to find in the literature, since all the tools developed at industrial level are hardly ever published with sufficient details.…”

Section: Introductionmentioning

confidence: 99%

European Space Agency intermediate experimental vehicle: Development of an independent aerothermodynamic database tool

Benedetto

Rufolo

Marini

2013

Proceedings of the Institution of Mechanical Engineers, Part G:

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In the frame of the European Space Agency (ESA) Intermediate eXperimental Vehicle (IXV) project, ESA is coordinating a series of technical assistance activities aimed at verifying and supporting the IXV industrial design and development process. The technical assistance is operated by the Italian Space Agency, by means of the technical support of the Italian Aerospace Research Centre. One of the purposes of the activity is to develop an independent capability for the assessment and verification of the industrial results with respect to the aerothermodynamic characterization of the IXV vehicle. To this aim, CIRA have developed an independent aerothermodynamic database, intended as a tool generating in output the time histories of local quantities for each point of the IXV vehicle surface and for each trajectory, together with an uncertainties model. The whole procedure followed for the definition of the numerical tool and the main results achieved will be presented in this article.

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“…Bow shock grid adaptation (by means of Mach isosurface grid generation process) and carbuncle phenomenon reduction methods have been necessary to obtain high-quality CFD results [6]. The numerical code has been widely used in the past and validated by means of comparisons with both WT and in-flight data [5].…”

mentioning

confidence: 99%

“…The analysis has been performed by using the CIRA code H3NS [4] that solves the Reynolds-averaged Navier-Stokes equations on multiblock structured grids in the frame of a finite volume cell centered approach. A two-equation compressible k-" turbulence model [5] has been used for eddy viscosity calculation while the laminar-to-turbulence transition has been imposed at the body-flap hinge line. Bow shock grid adaptation (by means of Mach isosurface grid generation process) and carbuncle phenomenon reduction methods have been necessary to obtain high-quality CFD results [6].…”

mentioning

confidence: 99%

Experimental and Numerical Investigation of Aerothermal Characteristics of Hypersonic Intermediate Experimental Vehicle

Roncioni

Ranuzzi

Marini

et al. 2011

Journal of Spacecraft and Rockets

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The main results of the aerothermodynamic hypersonic characterization of the intermediate experimental vehicle, by means of both computational fluid dynamics simulations and wind-tunnel measurements, have been reported and analyzed in this work, developed in the frame of ESA Future Launcher Preparatory Program. A test campaign has been carried out at the von Kármán Institute Free Piston Longshot wind tunnel in a cold hypersonic regime. The numerical simulations, rebuilding the von Kármán Institute wind-tunnel conditions, have been performed by the Italian Aerospace Research Center, the goal being to support the procedure of extrapolation-to-flight of the measurements and the general aerothermal characterization. A detailed comparison of all measured and predicted hypersonic relevant phenomena and aerothermodynamic parameters, such as surface pressure and heat flux, is reported in the paper, together with a detailed description of the configuration, freestream conditions, and model attitude effects. The reproducibility of flight conditions in the von Kármán Institute Longshot test campaign is qualitatively very good, both in terms of flow features and surface properties as indicated by wind-tunnel numerical simulations. The comparisons of numerical and experimental results indicate a good agreement in terms of external flow structure, i.e., bow shock, shock layer, expansion at the junction on windward side, shock-wave boundary-layer interaction in the flap area, and multiple-shock interaction above the flap. Sideslip, angle-of-attack, and flapdeflection effects are correctly reproduced by computational fluid dynamics in terms of pressure coefficient and heat flux. Nomenclature C p = pressure coefficient h = altitude, km k = transition tripping device height, mm L = vehicle length, m M = Mach number P = pressure, pa q = convective heat flux, kW=m 2 Re = Reynolds number T = temperature, k X = distance along vehicle forebody running from nose, m Y = spanwise vehicle coordinate, m = angle of attack, deg = angle of side slip, deg = surface control deflection angle, deg " = emissivity coefficient Subscripts a = aileron e = elevon flap = body flap L = reference length left = left body flap right = right body flap sp = stagnation point 0 = reservoir conditions 1 = freestream conditions

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CFD rebuilding of USV-DTFT1 vehicle in-flight experiment

Cited by 6 publications

References 5 publications

Aerodynamic Data of Space Vehicles

Aerodynamic Data of Space Vehicles

European Space Agency intermediate experimental vehicle: Development of an independent aerothermodynamic database tool

Experimental and Numerical Investigation of Aerothermal Characteristics of Hypersonic Intermediate Experimental Vehicle

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