Assume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23 kg/m3 (0.002377 slug/ft3) and 1.01 × 105 N/m2 (2116 lb/ft2), respectively. Consider a low-speed open-circuit subsonic wind tunnel with aninlet-to-throat area ratio of 12. The tunnel is turned on, and the pressuredifference between the inlet (the settling chamber) and the test section isread as a height difference of 10 cm on a U-tube mercury manometer.(The density of liquid mercury is 1.36 × 104 kg/m3.) Calculate thevelocity of the air in the test section.
Assume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23 kg/m3 (0.002377 slug/ft3) and 1.01 × 105 N/m2 (2116 lb/ft2), respectively. Consider a low-speed open-circuit subsonic wind tunnel with aninlet-to-throat area ratio of 12. The tunnel is turned on, and the pressuredifference between the inlet (the settling chamber) and the test section isread as a height difference of 10 cm on a U-tube mercury manometer.(The density of liquid mercury is 1.36 × 104 kg/m3.) Calculate thevelocity of the air in the test section.
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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Assume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23 kg/m3 (0.002377 slug/ft3) and 1.01 × 105 N/m2 (2116 lb/ft2), respectively.
Consider a low-speed open-circuit subsonic wind tunnel with an
inlet-to-throat area ratio of 12. The tunnel is turned on, and the pressure
difference between the inlet (the settling chamber) and the test section is
read as a height difference of 10 cm on a U-tube mercury manometer.
(The density of liquid mercury is 1.36 × 104 kg/m3.) Calculate the
velocity of the air in the test section.
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