Relay-Version: version B 2.10 5/3/83; site utzoo.UUCP Path: utzoo!linus!philabs!prls!pyramid!hplabs!hpda!hpsmtc1!hpisof0!campbelr From: campbelr@hpisof0.UUCP Newsgroups: sci.space.shuttle Subject: Re: Throttling the Challenger Message-ID: <5270002@hpisof0.HP.COM> Date: Wed, 28-Oct-87 19:09:46 EST Article-I.D.: hpisof0.5270002 Posted: Wed Oct 28 19:09:46 1987 Date-Received: Sat, 31-Oct-87 16:47:25 EST References: <187@scdpyr.UUCP> Organization: Hewlett Packard, Cupertino Lines: 36 >>Flowrates: >> Total 1,130 lb/s 22,557 gpm >> Hydrogen 160 lb/s 16,436 gpm >> Oxygen 970 lb/s 6,121 gpm > >Does the above flowrates indicate tha actual combustion mixture present at the >combustion chamber? If so then why is there a greater ratio than 2 parts H to >one part O? I would think that the extra hydrogen would be unconsumed making >the engine less efficient than it could be... What am I missing? > >Phil Biehl While the temperature of the products will be lower because of the energy used to heat the excess hydrogen, the SSME is not the most efficient at a 2 to 1 mixture ratio. Not getting involved in discussions on units, the performance of a rocket is measured by its specific impulse. F Vexit I = --- ~ ------- s . g w . Where F is thrust, Is is specific impulse, w is the mass flow rate, and Vexit is the nozzle exit velocity of the gases. Trusting me that exit velocity is proportional to the square root of combustion temperature over the molecualr weight of the exhaust gas, by lowering combustion temperature you are also lowering the molecular weight (Water = 18, Hydrogen = 2, Both mixed < 18) and at some point is the ideal mixture ratio. If you really want the equation for Vexit, let me know. It is rather larger than the one above :-) Bob Campbell Some times I wish that I could stop you from Hewlett Packard talking, when I hear the silly things you say. hplabs!hpda!campbelr - Elvis Costello