Comments by "User 2C47" (@user2C47) on "Primal Space" channel.

  1. Maybe fragments of engine parts.
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  2. SN8 test was successful. Low fuel header tank pressure caused loss of thrust during landing burn and subsequent RUD caused by high lithobraking velocity.
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  3. Putting RVac on a Falcon 2nd stage would require a complete reconfiguration of the fuel tanks, and the thrust would likely be too much. Also, Falcon's stage 0 does not support cryogenic fuel. (Only the oxidizer is cryogenic) Simply put, the cost would be far greater than the benefit.
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  4. Can you think of a better nozzle design for chemical engines?
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  5. SN8 test completed. All was successful except fuel header tank pressure.
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