If a rocket has an exhaust velocity of 2.5 km/s and a thrust of 500 kg What is the fuel flow rate in mass/second

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Anonymous Fri Sep 24 19:27:15 2010 No.1798724 [Reply] [Original]

If a rocket has an exhaust velocity of 2.5 km/s and a thrust of 500 kg

What is the fuel flow rate in mass/second

>>	Anonymous Fri Sep 24 19:37:15 2010 No.1798755 File: 219 KB, 1024x783, 1285213967814.jpg [View same] [iqdb] [saucenao] [google]

>>	Anonymous Fri Sep 24 19:41:15 2010 No.1798776 File: 26 KB, 470x360, moonrise1.jpg [View same] [iqdb] [saucenao] [google] bumping for help

>>	Anonymous Fri Sep 24 19:47:15 2010 No.1798794 Assuming 500kg of thrust means 500 x 9.81 N. Consider for exerted on body of fuel: F = d(mv)/dt = v dm/dt => dm/dt = F/v = 500 x 9.81 / 2500 = 1.962 kg/s Therefore, for rocket, dm/dt=-1.962 kg/s

>>	Anonymous Fri Sep 24 20:01:15 2010 No.1798844 File: 58 KB, 600x750, 1283577767910.jpg [View same] [iqdb] [saucenao] [google] >>1798794 Thanks for the help, in return I give you back your chis farly

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