The propulsive power of the rocket is (where v1 = Jet velocity and v2 = Aircraft velocity)
A. $$\frac{{{\text{v}}_1^2 - {\text{v}}_2^2}}{{2{\text{g}}}}$$
B. $$\frac{{{{\left( {{{\text{v}}_1} - {{\text{v}}_2}} \right)}^2}}}{{2{\text{g}}}}$$
C. $$\frac{{{\text{v}}_1^2 - {\text{v}}_2^2}}{{\text{g}}}$$
D. $$\frac{{{{\left( {{{\text{v}}_1} - {{\text{v}}_2}} \right)}^2}}}{{\text{g}}}$$
Answer: Option A
Solution (By Examveda Team)
The propulsive power of the rocket is $$\frac{{{\text{v}}_1^2 - {\text{v}}_2^2}}{{2{\text{g}}}}$$Where ,
v1 = Jet velocity
v2 = Aircraft velocity
This Question Belongs to Mechanical Engineering >> Compressors, Gas Turbines And Jet Engines
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