A rocket motor has a combustion chamber temperature of 2600 K and the products have molecular weight of 25g/mol and ratio of specific heats 1.2.The universal gas constant is 8314 J/kg-mol-K. What is the value of theoretical c^{*} in (m/s)?
A rocket motor has a combustion chamber temperature of 2600 K and the products have molecular weight of 25g/mol and ratio of specific heats 1.2.The universal gas constant is 8314 J/kg-mol-K. What is the value of theoretical c^{*} in (m/s)?
Characteristic velocity of a rocket motor is given as
c^{*}=\frac{\sqrt{\gamma RT_{c}}}{\gamma \sqrt{\left ( \frac{2}{\gamma +1} \right )^{\frac{\gamma +1}{\gamma -1}}}}
On putting the values we get
=\frac{\sqrt{1.2\times 8314\times 2600}}{1.2\sqrt{\left ( \frac{2}{1.2+1} \right )^{\frac{1.2+1}{1.2-1}}}} \\=\frac{1018.6}{0.71} \\=1433.8\;m/s
