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
\(=\frac{\sqrt{1.2\times 8314\times 2600}}{1.2\sqrt{\left ( \frac{2}{1.2+1} \right )^{\frac{1.2+1}{1.2-1}}}}
\\=\frac{1018.6}{0.71}
\\=1433.8\;m/s\)
