Question

The equation below describes how nozzle exit velocity is affected by other parameters for chemical rockets. Derive the equation starting from one dimensional isentropic flow; total enthalpy conservation from a chamber (1) to a nozzle exit (2). v_(2)=\sqrt((2k)/(k-1)(R_(u))/(MW)T_(1)[1-((p_(2))/(p_(1)))^((k-1)/(k))]) $v_2 = \sqrt{\frac{2k}{k-1} \frac{R_u}{MW} T_1 [1 - (\frac{p_2}{p_1})^{(k-1)/k}]}$

Name: the equation below describes how nozzle exit velocity is affected by other parameters for chemical rockets derive the equation starting from one dimensional isentropic flow total enthalpy co 67894
Uploaded: 2022-01-16T15:56:48-08:00
Duration: 1 min 19 s
Channel: Manik Pulyani
Description: the equation below describes how nozzle exit velocity is affected by other parameters for chemical rockets derive the equation starting from one dimensional isentropic flow total enthalpy co 67894

          The equation below describes how nozzle exit velocity is affected by other parameters for
chemical rockets. Derive the equation starting from one dimensional isentropic flow; total
enthalpy conservation from a chamber (1) to a nozzle exit (2).
v_(2)=\sqrt((2k)/(k-1)(R_(u))/(MW)T_(1)[1-((p_(2))/(p_(1)))^((k-1)/(k))])
$v_2 = \sqrt{\frac{2k}{k-1} \frac{R_u}{MW} T_1 [1 - (\frac{p_2}{p_1})^{(k-1)/k}]}$

the equation below describes how nozzle exit velocity is affected by other parameters for chemical rockets derive the equation starting from one dimensional isentropic flow total enthalpy co 67894

Added by Esperanza V.

University Physics with Modern Physics

Hugh D. Young 14th Edition

Instant Answer

Solved by Expert Manik Pulyani

01/16/2022

Step 1

Step 1: We start with the conservation of energy equation for a steady, adiabatic flow: $h_1 + \frac{v_1^2}{2} = h_2 + \frac{v_2^2}{2}$ where $h$ is the enthalpy and $v$ is the velocity. Show more…

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The equation below describes how nozzle exit velocity is affected by other parameters for chemical rockets. Derive the equation starting from one dimensional isentropic flow; total enthalpy conservation from a chamber (1) to a nozzle exit (2). v_(2)=\sqrt((2k)/(k-1)(R_(u))/(MW)T_(1)[1-((p_(2))/(p_(1)))^((k-1)/(k))]) $v_2 = \sqrt{\frac{2k}{k-1} \frac{R_u}{MW} T_1 [1 - (\frac{p_2}{p_1})^{(k-1)/k}]}$