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MIT Rocketlab's How to Design Build and Operate Liquid Fueled Rocket Engines
Anyone here used the information from this book? I'm trying to do some
design based on it, although I've found in a couple of places the formula's make great leaps with no explanation. The main one I'm having problems with is Step 9. start quote The chamber length is found from Eq. (21) Vc = (1.1) (Ac Lc) However, we must first determine the chamber area or Ac. We do this by assuming that the chamber diameter is five times the nozzle throat diameter or Dc = 5Dt, therefore Dc = 1.2 in. and Ac = 1.13 in2 Therefore, Lc = Vc/(1.1)(1.13) = 2.67/1.245 = 2.15 in end quote Having a chamber volume of 2.67 in^3 and calculating the the chamber diameter by Dc = 5Dt, the cross-sectional area of the chamber should be Ac = 2 pi r = pi * Dc as far as I can tell. But they introduce a figure 1.13 in^2 for Ac, with no explanation. On the formula page they provide a formula for Ac: Ac = Dc^2 / 4 This produces a value of 0.35 in^2. Any ideas on what is going on here? What is the correct value? I've been trying to follow their example so I can build and validate a spreadsheet for such calculations, but I'm stuck here. I've also been trying to convert the formulae to metric. Has anyone already converted it? Secondly, is there a better publication out there to superseed this book? This book is aimed at static test articles, do other publications apply more to flight articles? Lastly, how well will these values apply to an aerospike type of engine, specifically an annular version? Would I be able to use the same areas and volumes effectively? Thanks, David P.S. Sorry for the cross post, but being a historical book now I think it's relavent to both. |
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The classic text on liquids is George Sutton's "Rocket Propulsion Elements".
Sutton spent years working at Rocketdyne. The book was written over 40 years ago, has been continually revised, and now is in its 7th edition. Also Huzel and Huang's "Modern Engineering for Design of Liquid-Propellant Rocket Engines (Progress in Astronautics and Aeronautics, Vol 147)" is good. It's more recent (1992). H & H usually fill in the gaps between equations. Both are available at Amazon.com but are pricy. Any university science library will have copies. Later Ray Schmitt "David Findlay" wrote in message ... Anyone here used the information from this book? I'm trying to do some design based on it, although I've found in a couple of places the formula's make great leaps with no explanation. The main one I'm having problems with is Step 9. start quote The chamber length is found from Eq. (21) Vc = (1.1) (Ac Lc) However, we must first determine the chamber area or Ac. We do this by assuming that the chamber diameter is five times the nozzle throat diameter or Dc = 5Dt, therefore Dc = 1.2 in. and Ac = 1.13 in2 Therefore, Lc = Vc/(1.1)(1.13) = 2.67/1.245 = 2.15 in end quote Having a chamber volume of 2.67 in^3 and calculating the the chamber diameter by Dc = 5Dt, the cross-sectional area of the chamber should be Ac = 2 pi r = pi * Dc as far as I can tell. But they introduce a figure 1.13 in^2 for Ac, with no explanation. On the formula page they provide a formula for Ac: Ac = Dc^2 / 4 This produces a value of 0.35 in^2. Any ideas on what is going on here? What is the correct value? I've been trying to follow their example so I can build and validate a spreadsheet for such calculations, but I'm stuck here. I've also been trying to convert the formulae to metric. Has anyone already converted it? Secondly, is there a better publication out there to superseed this book? This book is aimed at static test articles, do other publications apply more to flight articles? Lastly, how well will these values apply to an aerospike type of engine, specifically an annular version? Would I be able to use the same areas and volumes effectively? Thanks, David P.S. Sorry for the cross post, but being a historical book now I think it's relavent to both. |
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