Question

Q3. Answer true or false. If false, state the true answer. 1) For a single compression or expansion wave, non-uniform conditions prevail upstream and downstream of the wave. 2) For expansion flow, $V_2 > V_1$, then $V_{2n} > V_{1n}$, so $p_2 = p_1$. 3) A Prandtl-Meyer function, $v$, represents the angle through which a stream, initially at $M = 0$, must be expanded to reach a supersonic Mach number. 4) For an under-expanded nozzle, the exit velocity is affected by backpressure. 5) For an over-expanded nozzle, the exit velocity is affected by backpressure. 6) The expansion along the plug nozzle is controlled by the backpressure nozzle wall. 7) For attached or detached shockwave, the low pressure after the shockwave produce excessive drag forces on the airfoil.

          Q3. Answer true or false. If false, state the true answer.
1) For a single compression or expansion wave, non-uniform conditions prevail upstream and downstream of
the wave.
2) For expansion flow, $V_2 > V_1$, then $V_{2n} > V_{1n}$, so $p_2 = p_1$.
3) A Prandtl-Meyer function, $v$, represents the angle through which a stream, initially at $M = 0$, must be
expanded to reach a supersonic Mach number.
4) For an under-expanded nozzle, the exit velocity is affected by backpressure.
5) For an over-expanded nozzle, the exit velocity is affected by backpressure.
6) The expansion along the plug nozzle is controlled by the backpressure nozzle wall.
7) For attached or detached shockwave, the low pressure after the shockwave produce excessive drag forces
on the airfoil.

Q3. Answer true or false. If false, state the true answer.
1) For a single compression or expansion wave, non-uniform conditions prevail upstream and downstream of
the wave.
2) For expansion flow, V2 > V1, then V2n > V1n, so p2 = p1.
3) A Prandtl-Meyer function, v, represents the angle through which a stream, initially at M = 0, must be
expanded to reach a supersonic Mach number.
4) For an under-expanded nozzle, the exit velocity is affected by backpressure.
5) For an over-expanded nozzle, the exit velocity is affected by backpressure.
6) The expansion along the plug nozzle is controlled by the backpressure nozzle wall.
7) For attached or detached shockwave, the low pressure after the shockwave produce excessive drag forces
on the airfoil.

Added by Robert R.

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