Aerodynamic drag and fuel spreading measurements in a simulated scramjet combustion module
- Author
- Povinelli, L. A.
- Published
- May 1, 1974.
- Physical Description
- 1 electronic document
Online Version
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- Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access - Summary
- The drag of a simulated scramjet combustion module was measured at Mach 2, 2.5, and 3. The combustor was rectangular in cross section and incorporated six swept fuel injector struts. The effect of strut leading edge radius, position of maximum thickness, thickness ratio, sweep angle, and strut length on the drag was determined. Reduction in thickness ratio had the largest effect on drag reduction. Sweeping the struts upstream yielded the same drag as sweeping the struts downstream and potentially offers the advantages of increased mixing time for the fuel. Helium injection was used to simulate hydrogen fuel. The interstrut spacing required to achieve good distribution of fuel was was found to be about 10 jet diameters. The contribution of helium injection to drag reduction was small.
- Other Subject(s)
- Collection
- NASA Technical Reports Server (NTRS) Collection.
- Note
- Document ID: 19740014809.
Accession ID: 74N22922.
E-7849.
NASA-TN-D-7674. - Terms of Use and Reproduction
- No Copyright.
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