Statement 1 : If P is the pressure of gas inside the exhaust chamber of a rocket and `P_(0)` is the pressure of the gas outside the chamber. The forward thrust on the rocket is `2a (P- P_(0))` insteady of a `(P-P_(0))` where a is the area of orifice.
Statement -2: The formula thrust `= a(P - P_(0))` holds good for fluids at rest. In the case of rocket the flurids are in motion and we have to use Bernoulli's principle for calculating the thrust.

Options

A. Statement I is true, statement II is true and statement II is correct explanation for statement I
B. Statement I is true, statement II is true and statement II is not the correct explanation for statement I
C. Statement I is true, statement II is false.
D. Statement I is false, statement II is true.

Answer

A

Explanation

`P=P_(0)+(1)/(2)rhoV^(2)impliesrhoaV^(2)=2a(P-P_(0))`