3 Matching Annotations
- Mar 2022
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www.grc.nasa.gov www.grc.nasa.gov
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The amount of thrust produced by the rocket depends on the mass flow rate through the engine, the exit velocity of the exhaust, and the pressure at the nozzle exit. All of these variables depend on the design of the nozzle.
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which means that the Mach number is equal to 1.0 in the throat
If the hot exhaust flow weren't choked at the throat, will the Mach number still be 1? But, why would the Mach number be 1 in the first in a choked flow?
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rocket thrust equation
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