This thread -- I've conceded failure.
No. You conceded the hoax hypothesis, but you redefined victory to mean having come up with a physically valid explanation ostensibly on your own, without anyone's help here—and indeed allegedly despite their interference.
I gave you credit for 5-minutes-worth of help.
It would have gone like this:
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Static Pressure can be approximated with Fluid Dynamics simplified model of Pressure, Restriction and Flow.... which are correlated by: P = F * R.
The pressure inside the Combustion chamber is rated for 120 psia, with a throat aperture of 16.4 sqIn. The Nozzle Exit is constricted by the platform beneath it with a starting angle of 1.5 degrees, and a 34 inch diameter nozzle exit. You can calculate the approximated pressure drop from Combustion Chamber to Nozzle to Vacuum, similar to how a simple electric circuit works in SERIAL, for Volts(pressure), Amps (Flow) and Resistance (Restriction)... the Concepts work out the same. It won't be exact, but will be approximated.
As the rocket ascends, this constriction becomes less quickly, however, Fluid Dynamics still can produce an approximate pressure for you.
The resulting Static Pressure Thrust can be approximated as the "PSI of the Nozzle chamber" x "Area of the Nozzle Exit in SqIn".
You might want to factor this into your model, this may add significant thrust/impact to the first 30 cm of takeoff.
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I derived MOST of this from you simply pointing me at the "aperture of exiting the Nozzle". That's about ALL YOU DID.
Are you a Bad Teacher? Or purposefully slowing down the process? You spent weeks to help me accomplish what could have been said in 5 minutes (shown above).