Download e-book for iPad: Aerodynamic and Aerothermodynamic Analysis of Space Mission by Antonio Viviani, Giuseppe Pezzella

By Antonio Viviani, Giuseppe Pezzella

ISBN-10: 3319139266

ISBN-13: 9783319139265

ISBN-10: 3319139274

ISBN-13: 9783319139272

Presenting an updated view at the most crucial area motor vehicle configurations, this booklet includes distinct analyses for a number of diversified form of area challenge profiles whereas contemplating vital components equivalent to aerodynamic a lot, aerodynamic heating, automobile balance and touchdown features. With that during brain, the authors offer a close review on diversified state of the art subject matters of hypersonic aerodynamics and aerothermodynamics, and think about assorted area automobile shapes precious for various house venture pursuits. those include:

· workforce go back automobile (CRV)

· staff Exploration automobile (CEV)

· pattern go back car (SRV)

· Flying try mattress (FTB).

Throughout Aerodynamic and Aerothermodynamic research of house undertaking Vehicles many examples are given, with unique 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 project to Mars closes the ebook. This paintings can be utilized as a reference for modelling and layout strategies, for college students aspiring to input aerospace commercial careers, and to aid either teachers and engineers operating within the box of house car design.

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Additional resources for Aerodynamic and Aerothermodynamic Analysis of Space Mission Vehicles

Example text

In case of oblique shock, Eq. 33) has to be modified in order to take into account for the deflection angle ™ and shock angle ˇ. When the flow is not normal to the shock, the velocity component normal to the shock is modified as if going through a normal shock, and the component parallel to the shock must be equal on either side of the shock to satisfy the continuity equation. Since an oblique shock acts as a normal shock to the component of flow normal to it, the normal shock equations, Eq. 33), given above may be applied to the oblique shock problem (see Fig.

This effect covers the shaded region labeled nitrogen dissociation. 4 Typical Hypersonic Flowfield Features Past a Vehicle in Continuum Flow. . 120 100 Lifting reentry from orbit 90% 10% 90% 10% Ionization Km 10% 90% Calorically perfect gas 10% 39 m CLS 80 50 Shuttle H 60 5000 40 20 Oxygen dissociation Vibrational excitation 0 1 2 Nitrogen dissociation 3 4 5 6 7 8 9 Km/s v Fig. 30 Altitude–velocity map with superimposed regions of vibrational excitation, dissociation, and ionization Finally, above 10 km/s, the N2 dissociation is complete, and ionization begins.

Fig. 930 The wake region flow is quite complex and is dominated by a recirculating zone behind the separation point (see Fig. 12). In addition, the vorticity diffuses from the boundary layer merging with the outer flow. The wake flow determines the base pressure and hence the base drag. In hypersonic separated base flow, a good approximation is pbase D p1 . If the flow does not separate, the wake region may be treated as a combination of the boundary layer and outer inviscid flow. Anyway, a detailed description of the flowfield that takes place past a vehicle at hypersonic speed in continuum flow regime can be obtained by integrating the flowfield governing equations.

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

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