Author details

Yuriy D. Shevelev

Address all correspondence to: shevelev@icad.org.ru

The Institute for Computer Aided Design of RAS, Moscow, Russia

## References


[4] Problems of Aerothermoballistics, Radiation Gasdynamics, Heat and Mass Transfer for Planet Sample Return Missions. Project Technical Report of ISTC No 1549-00; 2003. http:// jan.imec.msu.ru/~avogadro/Mars/Mars1549/index.htm

and fully catalytic surfaces. The results are compared with the ones obtained in the simplified two-temperature approximation and in the one-temperature approach for weak deviations from thermal equilibrium. A considerable influence of CO2 vibration excitation on the flow parameters and transport properties in a shock layer is found. The difference between the results obtained using the accurate and simplified vibration non-equilibrium models are weak under conditions considered in the paper. This justifies the validity of the approximate twotemperature model under the re-entry conditions. It is shown that difference in reaction rate constants practically has small influence on value of a heat transfer to ideal catalytic surfaces of the vehicle. In a case of non-catalytic surfaces difference in value of the heat transfer obtained by different models can be essential up to 30%. The effect of bulk viscosity in a shock layer is studied. Including this coefficient to the fluid dynamics equations improves the accuracy of the

The heat flux to ideal catalytic surface for the considered conditions of a flow can up to four

The influence of the different chemical reactions models: (1) Mc. Kenzie and Arnold chemistry model, (2) Park's model, amd (3) model of S. Losev and others, on component concentrations and heat flux are presented. Numerical calculations of the coefficients of viscosity and heat conductivity give the close result for the heat flux for different models comparing with results obtained by exact kinetic theory. The diffusion parameters affects on the magnitude of the heat flux especially in the case of a catalytic wall. The pressure- and thermo-diffusion influence on heat flux are small. The different models of the vibration relaxation of CO2 considered. They give approximately the same values of main properties of the flow. The catalytic properties of the surface are most important for a valid determination of the heat flux to the wall. The insertion of bulk viscosity into the equations leads to the small increase of the heat fluxes.

[1] Kay RD, Netterfield MP. Thermochemical Non-Equilibrium Computation For A Mars

[2] Gupta RN, Lee KP. An Aerothermal Study of MESUR Pathfinder Aeroshell. AIAA Paper.

[3] Gallis MA, Harvey JK. Analysis of Non-Equilibrium in Mars Atmosphere Entry Flows.

heat flux calculation up to 10%.

86 Advances in Some Hypersonic Vehicles Technologies

Author details

Yuriy D. Shevelev

References

No 94-2025; 1994

AIAA Paper. No 95-2095; 1995

times surpasses a heat transfer to non-catalytic wall.

Address all correspondence to: shevelev@icad.org.ru

Entry Vehicle. AIAA Paper. No 93-2841; 1993

The Institute for Computer Aided Design of RAS, Moscow, Russia


[18] Shevelev YD, Syzranova NG, Kustova EV, Nagnibeda EA. Bulk-viscosity effect on CO2 hypersonic flow around blunt bodies. Doklady Physics, Pleiades Publishing, Ltd. 2015; 60(5):207-209

[33] Ibragimova LB, Smehov GD, Shatalov OP. Constants of dissociation reaction rates of two-atom molecules in thermal equilibrium conditions. Izv. Ross. Akad. Nauk, Mekh.

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[37] Taylor RL, Bitterman S. Survey of vibrational relaxation data for processes important in

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**Chapter 4**

Provisional chapter

**Launcher Aerodynamics: A Suitable Investigation**

DOI: 10.5772/intechopen.70757

Launcher Aerodynamics: A Suitable Investigation

This chapter deals with launcher aerodynamic design activities at phase-A level. The goal is to address the preliminary aerodynamic database of a typical launch vehicle configuration as input for launcher performances evaluations, control, sizing, and staging design activities. In this framework, different design approaches relying on both engineering and numerical methods are considered. Indeed, engineering-based aerodynamic analyses by means of a three-dimensional panel methods code, based on local surface inclination theory, were performed. Then, accuracy of design analysis increased using steady-state computational fluid dynamics with both Euler and Navier-Stokes approximations.

Keywords: launcher vehicles, aerodynamic design, subsonic, transonic, supersonic and hypersonic speed flows, computational fluid dynamics, panel methods aerodynamics

During the design phase of launchers, the aerodynamic characterization represents a fundamental contribution. Usually, it is accomplished by means a hybrid approach encompassing wind tunnel testing (WTT) and computational fluid dynamics (CFD) investigations [1]. This combined design approach (i.e., WTT and CFD analyses) is extremely reliable in providing high quality data as input for launchers' sizing, performance evaluations, control, and staging dynamics [2]. Indeed, launcher aerodynamics focuses on the assessment of the pressure and skin friction loads the atmosphere determines over the vehicle surface [3]. As well known, these loads result in a global aerodynamic force that acts at the aeroshape center of pressure (CoP) which generally does not coincide with the vehicle center of gravity (CoG) [4]. As a result, the related aerodynamic moment acting at the CoG can lead to a stable or unstable behavior of the launcher to account for in the control software [5]. Moreover, the analysis of the flowfield past the launcher is also fundamental to address the effects of aeroshape's structures

> © The Author(s). Licensee InTech. This chapter is distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/3.0), which permits unrestricted use, distribution, and eproduction in any medium, provided the original work is properly cited.

© 2018 The Author(s). Licensee InTech. This chapter is distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/3.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

**Approach at Phase-A Design Level**

Approach at Phase-A Design Level

Giuseppe Pezzella and Antonio Viviani

Giuseppe Pezzella and Antonio Viviani

http://dx.doi.org/10.5772/intechopen.70757

Abstract

1. Introduction

Additional information is available at the end of the chapter

Additional information is available at the end of the chapter

Provisional chapter
