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The pressure-chamber would be held at 250°F . This would keep the methane liquid, but the metal strong .
Normally that would be the case , but at 1 Million + psi the CH4 will turn to hot ice , below ~250F°.
You would then need to shovel it like coal !
Good points , manly-man !If I let it go from liquid to ice , it would clog up & go boom ! Also , it damned sure better be real heavy ; the reinforcement necessary for that much pressure is huge . Only someone standing behind the engine exhaust would experience it's rediculous power , it is meant for a large , SSTO spaceplane . Let us measure ; One 100MW SMR - 40 ft. X 20 ft. by 20 ft. . One Nuclear Compression Drive - 20ft.X20ft.X 20ft. . One 4,000gal. LNG tank - 10 ft. X 10ft. X 20ft. .Craft size - Venture Star class .Gross Take-Off Weight - 500k lbs.Launch locations - Remote .OK , spread the good mews ! P.M.
Cliff Notes SSME pressure : 4,000 psi.Exhaust Velocity : 10,000 mphHeavy gas cylinder : 10,000 psi.Rupture Ex. Velocity : 30,000 mph*relatively wide throat allows more layered exhaust & higher velocities. extrapolating for lightweight CH4 yields 1M.mph at 1M.psi .Okay , done for day !..................P.M.
Graph , and extrapolate for ballpark
Who is us ? You & Gunter Zoloff ?
If you must have a formula , try Navier-Stokes: `m`=pA♤T/z .My process is extrapolation from known values . I will show it here step-by-step .Step 1 : Sample a multitude of rocket systems . Note chamber pressures , throat diameters , gas densities , and flow velocities .Step 2: Sample hi-pressure vessel ruptures . Note pressure , hole size, gas density , and escape velocities. Step 3 : Establish P/V pattern .Step 4 : Extrapolate from 10k.psi to 1 Million psi .Step 5 : Compensate for lighter weight methane reaction mass .Step 6 : Calculate for different pressure chamber orifice sizes .Conclusion : Large orifice sizes should yield ~1Mmph. @ 1M.psi. , ISP ~45k.sec. , thrust ~25M.lbs. .Smaller orifice sizes would greatly reduce these values , but electrothermal " afterburners " would greatly increase them .Alright,it's an aerospacepropulsion breakthrough ! I will take your congrats. now . P.M.
Yaah mahn , Ya needs an aerospace engineer mahn ! I'm a system designer , not a rocket scientist.I never had the patience ta crunch formulas like dat ! I tell you whut , why don't you put on dem sneaks , ahnd chase down da nearest pencil-on-da-ear nerd walkin' down da street , cuz I not be wone , cuz ! 10 gits ya one my numbas be ballpark dough !Adios , #s jockey !...............P.M.
I be sure , buut , you not be sure ! Just track down a graduate student and give him/her this thread . Have them run realistic #s through the relevant equations . Then You'll be sure . Adios , P.M.
What is needed is a nuclear-mechanical drive . This would be a nuclear-powered high pressure system , fielding 1 million psi.+ , & yielding exhaust velocities approaching 1M mph ! The pressure-chamber would be held at 250°F .