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Influence of Combustion-chamber Length on Afterburner Performance (1954)
NASA Technical Reports Server (NTRS) · leaf 17
NACA EM E54E06 … Probe depth Passage depth (b) Fuel-air ratio profile at flame holder. Figure 3. - Typical mass-flow and fuel-air ratio profiles obtained during stoichiometric afterburning. Flight Mach number, 1.0, altitude, 35,000 feet; afterburner-inlet pres sure, 1600 pounds per square foot absolute.NASA Technical Reports Server (NTRS)
Internet Archive · NASA Technical Reports · Public domain (US government work). Free to use for anything.
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