The spectral intensity emitted by various aluminized solid propellant flames has been measured. The pressure during combustion has been varied from atmospheric to 7. 2 MPa. From the intensity measurements effective blackbody temperatures for emission as high as 4000K have been obtained which are significantly in excess of the overall adiabatic flame temperatures (1400 to 3000K). These extremely high intensities can be attributed to the combusting Al/Al//20//3 droplets present in the gas phase flame region. This evidence indicates that radiant heat feedback to the burning solid propellant may be much larger than previously estimated. This finding could have significant impact on solid propellant burn rate modelling, acoustic combustion stability modelling and aluminum agglomeration modelling as now being practiced in the solid propellant industry.
|Original language||English (US)|
|Title of host publication||Heat Transfer, Proceedings of the International Heat Transfer Conference|
|Editors||Chang L. Tien, Van P. Carey, James K. Ferrell|
|Publisher||Hemisphere Publ Corp|
|Number of pages||6|
|State||Published - 1986|
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