The Pre-X atmospheric re-entry experimental lifting body: program status and system synthesis

Baiocco, Paola; Guedron, Sylvain; Plotard, Patrice; Moulin, J.

doi:10.2514/6.iac-06-d2.p.2.02

Cited by 2 publications

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“…A model of the Pre-X European reentry vehicle (RV) of the lifting body type scaled at 1:15 was tested in 2006-2007 in an experimental facility (PGU-7) based at TsNIIMash within the framework of Contract No. 60134, dated May 12, 2006, between CNES (France) and TsNIIMash (Russia) [17]. The heat transfer characteristics on the surface were determined experimentally by means of infrared imaging.…”

Section: Experimental Study Of Heat Transfer On a Model Of A Reentry ...mentioning

confidence: 99%

Chapter 10: Numerical Modeling of Heat Transfer of Hypersonic Flying Vehicles Flying in the Earth's Atmosphere

2013

Hypersonic Aerodynamics and Heat Transfer

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Section: Experimental Study Of Heat Transfer On a Model Of A Reentry ...mentioning

confidence: 99%

Chapter 10: Numerical Modeling of Heat Transfer of Hypersonic Flying Vehicles Flying in the Earth's Atmosphere

2013

Hypersonic Aerodynamics and Heat Transfer

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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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The Pre-X atmospheric re-entry experimental lifting body: program status and system synthesis

Cited by 2 publications

References 0 publications

Chapter 10: Numerical Modeling of Heat Transfer of Hypersonic Flying Vehicles Flying in the Earth's Atmosphere

Chapter 10: Numerical Modeling of Heat Transfer of Hypersonic Flying Vehicles Flying in the Earth's Atmosphere

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

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The Pre-X atmospheric re-entry experimental lifting body: program status and system synthesis

Cited by 2 publications

References 0 publications

Chapter 10: Numerical Modeling of Heat Transfer of Hypersonic Flying Vehicles Flying in the Earth&apos;s Atmosphere

Chapter 10: Numerical Modeling of Heat Transfer of Hypersonic Flying Vehicles Flying in the Earth&apos;s Atmosphere

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

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Product

Resources

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Chapter 10: Numerical Modeling of Heat Transfer of Hypersonic Flying Vehicles Flying in the Earth's Atmosphere

Chapter 10: Numerical Modeling of Heat Transfer of Hypersonic Flying Vehicles Flying in the Earth's Atmosphere