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Mtakeoff takeoff mass MFinal = final vehicle mass after fuel is consumed a) Set Voo flight velocity = dx/dt b) Set mfuel = fuel mass flow rate = - dM dt this is conservation of mass Isp = specific impulse defined to be: = I/ (ṁfuel * g) g = 9.8 m/s² Derive the Breguet range formula which is; Range = S = Isp V∞ (±) In (Mtakeoff) MFinal Assume that we cruise, with no acceleration, with a constant V∞, (L/D) and Isp J = thrust D= drag L = lift, W = weight

Mtakeoff takeoff mass MFinal = final vehicle mass after fuel is consumed a) Set Voo flight velocity = dx/dt b) Set mfuel = fuel mass flow rate = - dM dt this is conservation of mass Isp = specific impulse defined to be: = I/ (ṁfuel * g) g = 9.8 m/s² Derive the Breguet range formula which is; Range = S = Isp V∞ (±) In (Mtakeoff) MFinal Assume that we cruise, with no acceleration, with a constant V∞, (L/D) and Isp J = thrust D= drag L = lift, W = weight

Introductory Circuit Analysis (13th Edition)
Introductory Circuit Analysis (13th Edition)
13th Edition
ISBN:9780133923605
Author:Robert L. Boylestad
Publisher:Robert L. Boylestad
Chapter1: Introduction
Section: Chapter Questions
Problem 1P: Visit your local library (at school or home) and describe the extent to which it provides literature...
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Mtakeoff takeoff mass MFinal = final vehicle mass after fuel is consumed a) Set Voo flight velocity = dx/dt b) Set mfuel = fuel mass flow rate = - dM dt this is conservation of mass Isp = specific impulse defined to be: = I/ (ṁfuel * g) g = 9.8 m/s²
Transcribed Image Text:Mtakeoff takeoff mass MFinal = final vehicle mass after fuel is consumed a) Set Voo flight velocity = dx/dt b) Set mfuel = fuel mass flow rate = - dM dt this is conservation of mass Isp = specific impulse defined to be: = I/ (ṁfuel * g) g = 9.8 m/s²
Derive the Breguet range formula which is; Range = S = Isp V∞ (±) In (Mtakeoff) MFinal Assume that we cruise, with no acceleration, with a constant V∞, (L/D) and Isp J = thrust D= drag L = lift, W = weight
Transcribed Image Text:Derive the Breguet range formula which is; Range = S = Isp V∞ (±) In (Mtakeoff) MFinal Assume that we cruise, with no acceleration, with a constant V∞, (L/D) and Isp J = thrust D= drag L = lift, W = weight
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