Currently, there is considerable interest in scramjet engines for hypersonic aircraft and missiles. This paper presents preliminary calculations of the radiative heating of the walls of scramjet combustion chambers. The analysis assumes isothermal, constant property flow fields that are representative of actual combustor flow fields. The fuel is H2, and N2 is taken as inert. Temperature in the combustor is on the order of 2000-3000 K and the pressure is of the order of 5 atm. The combustion products consist mainly of H2O and OH. These gases are strong radiators in the infrared. Radiation heating can be significant because of high temperature and pressure and the strong gas emission. The radiation fluxes from H2O and OH are predicted to be as large as 24 W/cm2, depending on the size of the combustor. Larger combustors have larger radiative heating. Radiation heating is roughly 10% of the convective heating. For airplane applications, where the engine must go through many cycles between overhauls, the combustor will need thermal radiative protection. Copyright © 1996 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.


Mechanical and Aerospace Engineering

Publication Status

Full Access

International Standard Serial Number (ISSN)

1533-6808; 0887-8722

Document Type

Article - Journal

Document Version


File Type





© 2024 American Institute of Aeronautics and Astronautics, All rights reserved.

Publication Date

01 Jan 1997