The most advanced type of report deals with the phenomena pertaining to materials selection for high temperature purposes. Significantly these are the materials for high temperature spacecraft reentry and turbocharger for engines having operating temperatures more than 1000 °C. This is instigated by descriptions of different materials used in spacecraft such metal alloys and thermal protection system materials at elevated temperatures at regarding environments. Degrading of materials is followed by different potential materials categories. In the main stream manufacturers of high temperature materials and their products are introduced as well as thermal protection system.
Few of the major components of turbocharger likewise turbine and wheel and combustion chamber are compared with the important features of spacecraft when reenter into atmosphere. Consequently techniques of computer based materials selection using CES are explained. At the last stage the suggestion of material selection based on this report. The suggested materials are of various types used in thermal protection system RCC, HRSI, FRCI, LRSI, TUFI and FIB. Further more alloys of aluminum and copper and stainless steel, oxide dispersion strengthened steel, super alloys and Haynes.

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Table of Contents

Executive Summary
Introduction

Spacecraft reentry design considerations
Thermal protection system
Metal Alloys
Rene 41
L-605
Beryllium
Shingles

Turbocharger
Compressor
Cast aluminum alloy
Turbine
Hastalloy
Bearing and drive shaft
Aluminum bearing
Aluminum silicon alloys
Alloy 380

Design specifications of turbocharger for engine
Discussion
CES
Materials Recommended
Haynes 214
SiC
TPS
Conclusion
References