Aerodynamic and Aerothermodynamic Analysis of Space Mission by Antonio Viviani, Giuseppe Pezzella

By Antonio Viviani, Giuseppe Pezzella

Presenting an up to date view at the most crucial house motor vehicle configurations, this e-book includes particular analyses for numerous various kind of house challenge profiles whereas contemplating very important components akin to aerodynamic lots, aerodynamic heating, car balance and touchdown features. With that during brain, the authors offer a close evaluate on diversified state of the art subject matters of hypersonic aerodynamics and aerothermodynamics, and think about various house car shapes invaluable for various area venture goals. those include:

· group go back car (CRV)

· workforce Exploration automobile (CEV)

· pattern go back automobile (SRV)

· Flying try out mattress (FTB).

Throughout Aerodynamic and Aerothermodynamic research of area project Vehicles many examples are given, with distinct computations and effects for the aerodynamics and aerothermodynamics of all such configurations. additionally, a last bankruptcy on destiny launchers is supplied and an Appendix on a potential manned undertaking to Mars closes the e-book. This paintings can be utilized as a reference for modelling and layout ideas, for college kids meaning to input aerospace commercial careers, and to aid either teachers and engineers operating within the box of area car design.

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37) for compression and for expansion. M1. T1 Po1 V1 M2. T2 θ 1 Po2 = Po1 To2 = To1 2 Expansion M2. v(M2) P1. P1. P2. T2 V2 Mach lines M1. v(M1) V1 Po2 = Po1 θ 1 2 To1 1 Compression Fig. T2 K-2 Right Running Characteristic Fig. 26 Method of characteristics Since the expansion process is isentropic and we are considering only isentropic compression here, the stagnation conditions are unchanged. Hence, the local flow properties can be determined from Eq. 32). It has been already said that the steady-state Euler equations in supersonic flow are hyperbolic.

Let us start considering, as reported in Fig. 8, the variety of flow regimes and thermochemical phenomena encountered in the nose region by an orbital reentry vehicle [7]. As shown, at the beginning of the atmospheric re-entry, the space vehicle encounters free molecular flow conditions up to about 120 km altitude. Then the vehicle flies through transitional flow regime up to reach continuum flow conditions at about 70 km altitude, where spacecraft velocity ranges from 7 to about 5 km/s. When considering from subsonic to supersonic vehicles, the fluid is studied as a continuum, but for hypersonic regime, it is not always possible to apply such hypothesis.

Ow through a shock wave where the characteristic dimension would be the thickness of the shock wave. So, not only is important, but also Lref which depends on the particular case studied. The characteristic length could be a dimension of a flowfield characteristic or of the body. Indeed, for a blunt cone, the base radius may be appropriate. For a lifting body, the mean aerodynamic chord of the lifting surface may be the correct choice. On the other hand, for flows past flat plates, the boundary layer thickness or the distance from the leading edge may be the appropriate characteristic dimension.

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