tavarish palkovnik

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Great sentence…”at what pressure” Pressure is the one and main only one making significant differences. In my language, pressure is the one fu..ing chickens in the yard

That’s true, impulse giving real thrust (расчетный импульс) should be calculated from specific impulse (удельный импульс) taking in consideration pressure values. Specific is like said usually given in ratio 40:1 and for example motor burning at 10km in buster phase is let’s say in ratio 100:0,265 (bars) To correct myself, coefficient K in upper formula is more related to the looses in burning process, some of fuel mass will not contribute making thrust force and with K it is included. To return on pressure, which value will be used for “pa” … it depends of how nozzle is executed and on expansion of gases. If gases will expand all to the atmospheric pressure (pressure at exit of nozzle is equal to atmospheric pressure) maximal thrust will be at disposal. That’s why motors of space rockets in upper stages have nozzles as big as bells on churches so that gas can expand to the level of low pressure as it is up there. Unfortunately for constructors of A-A missiles, they must make compromise with nozzles because those can be used at low level and high level flights. Conclusion…thrust is variable and that is a fact. Just as second fact and that is, drag coefficient in turbulent air flow, what is mostly case, for sure will be increasing with altitude (viscosity, Reynold’s number etc) Motor gives, drag takes!

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Just from the curiosity and my wish to see it, who will be kind to show me thrust diagram of R-27ER momentarily used in DSC. For example at 10km altitude.

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отражают математику, физику, механику, аэродинамику, термодинамику ...

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We have saying “Selo veselo” … it could be “Happy village” although it sounds much better in original What v f(t) saying… 700=Isp * ln (m0/m1) -> 700=Isp * ln (350/230) -> Isp=1665 … garbage fuel However, no it isn’t garbage fuel but vertical launch. That is why velocity reduction is such a massive, rocket would be under extremely high kinematic overload to get directed toward target. First what should be forgotten immediately is to have warm start of such rocket from the container. It would knock down that container together with the truck in black mother ground underneath. Furthermore, this rocket is with only aerodynamic controlling surfaces and for that initial velocity is expected and needed. No, they will not implement gas dynamics surfaces, if this system ever “see light of living” in what I doubt. The principal is to have strong cold start, either by gas generator, either by some kind of “mortar catapult” and that flight time should be incorporated in velocity envelope presented in this graph. And I think it is

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Всегда можно воспользоваться возможностью не смотреть, тогда в голове не будет вопросов. Просто так

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