Metadata
Title
Department of Aerospace Engineering
Category
general
UUID
79672553234c477da9ac4c979ecd5323
Source URL
https://ae.iitm.ac.in/aeweb/aerospace-dynamics.php
Parent URL
https://ae.iitm.ac.in/aeweb/innerfaculty.php?fname=Sriram
Crawl Time
2026-03-17T07:05:25+00:00
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Department of Aerospace Engineering

Source: https://ae.iitm.ac.in/aeweb/aerospace-dynamics.php Parent: https://ae.iitm.ac.in/aeweb/innerfaculty.php?fname=Sriram

Combustion driven shock tunnel: Flows can be generated at Mach number ranges between 5-12 with Enthalpy levels upto 6 MJ. Both reflected and straight modes are possible, and can be used to study moving shock problems.