Specific Impulse Of Hydrogen Burned In Nitrogen-Oxygen Mixtures
Report Number: WADD TN 60-254
Author(s): Lawler, James H. L.
Corporate Author(s): Aeronautical Systems Div Wright-Patterson AFB Ohio Directorate Of Advanced Systems Technology
Date of Publication: 1960-11
Pages: 321
DoD Task:
Identifier: AD0265361
Abstract:
Specific impulse curves are presented for O-N mixtures of 90, 85, 80, 75, 70, and 60% by weight O being burned with H. The chamber pressures were 1000 psia and 500 psia and various exhaust pressures from 7.35 psia to 0.005 psia were used. Expansion ratio vs impulses for the several conditions is plotted. The specific impulse is a function of expansion ratio and is independent of the chamber pressure in the range of 500 to 1000 psia chamber pressure. It is desirable to burn a H rich mixture as the specific impulse is highest with slightly more H than storchiometric. This is theorized to be due to the average molecular weight being lowered faster than the temperature drop.
Provenance: Lockheed Martin Missiles & Fire Control
Author(s): Lawler, James H. L.
Corporate Author(s): Aeronautical Systems Div Wright-Patterson AFB Ohio Directorate Of Advanced Systems Technology
Date of Publication: 1960-11
Pages: 321
DoD Task:
Identifier: AD0265361
Abstract:
Specific impulse curves are presented for O-N mixtures of 90, 85, 80, 75, 70, and 60% by weight O being burned with H. The chamber pressures were 1000 psia and 500 psia and various exhaust pressures from 7.35 psia to 0.005 psia were used. Expansion ratio vs impulses for the several conditions is plotted. The specific impulse is a function of expansion ratio and is independent of the chamber pressure in the range of 500 to 1000 psia chamber pressure. It is desirable to burn a H rich mixture as the specific impulse is highest with slightly more H than storchiometric. This is theorized to be due to the average molecular weight being lowered faster than the temperature drop.
Provenance: Lockheed Martin Missiles & Fire Control