Consider an initially uniform supersonic air flow passing over a solid surface (
ID: 2088847 • Letter: C
Question
Consider an initially uniform supersonic air flow passing over a solid surface (see the bottom of the figure) and then through a set of Prandtl-Meyer waves shown below. After the last wave, the flow at the point marked 2 is moving upward at an angle of 15?. Determine the (static) temperature and pressure in the region marked 3, which is near the wall but downstream of the last of the PM waves shown in the figure. HINT: There may be other flow features that you need to include in your analysis that are not shown in the figure.
Wave Reflections Consider an initially uniform supersonic air flow passing over a solid surface (see the bottom of the figure) and then through a set of Prandtl-Meyer waves shown below. After the last wave, the flow at the point marked 2 is moving upward at an angle of 15°. Determine the (static) temperature and pressure in the region marked 3, which is near the wall but downstream of the last of the PM waves shown in the figure. HINT: There may be other flow features that you need to include in your analysis that are not shown in the figure. 2 15° M-2.6 ??-30 atm ??? 1400 RExplanation / Answer
Wave Reflections Consider an initially uniform supersonic air flow passing over a solid surface (see the bottom of the figure) and then through a set of Prandtl-Meyer waves shown below. After the last wave, the flow at the point marked 2 is moving upward at an angle of 15°. Determine the (static) temperature and pressure in the region marked 3, which is near the wall but downstream of the last of the PM waves shown in the figure. HINT: There may be other flow features that you need to include in your analysis that are not shown in the figure. 2 15° M-2.6 ??-30 atm ??? 1400 R