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X Incorrect Air is drawn into a wind tunnel used for testing automobiles as shown in...
9) For the air wind tunnel shown above in Q8: (6 points) Assuming a circular cross...
9) For the air wind tunnel shown above in Q8: (6 points) Assuming a circular cross section, the atmospheric pressure is 101.325 kPa, density of air is 1.2 kg/m², and absolute viscosity of air is 1.825*10-Ns/m² (assume there are no losses in the wind tunnel) Contraction ratio: 7 Diffuser length: 3 m Test section diameter = test section length = 70 cm a) When a static-pitot tube placed in the test section with a manometer (manometer fluid is water with...
For the air wind tunnel shown Honeycomb Flow Straightener Anti-Turbulence Screens Silencer Fan Diffuser Test Section...
For the air wind tunnel shown Honeycomb Flow Straightener Anti-Turbulence Screens Silencer Fan Diffuser Test Section Inlet Assuming a circular cross section, the atmospheric pressure is 101.325 kPa, density of air is 1.2 kg/m?, and absolute viscosity of air is 1.825*10-S Ns/m? (assume there are no losses in the wind tunnel) Contraction ratio: 7 Diffuser length: 3 m Test section diameter = test section length = 70 cm a) When a static-pitot tube placed in the test section with a...
1. [20 pts] An indraft wind tunnel pulls air into an inlet, through a contraction, the...
1. [20 pts] An indraft wind tunnel pulls air into an inlet, through a contraction, the test section, and the diffuser, as shown below. The test section has a circular cross section and it has a diameter of 0.5 m. Assume the wind tunnel is at sea level and the temperature and pressure of the atmosphere are given by standard atmospheric conditions. (a) If the test section is designed to have a velocity of 200 m/s, determine the Mach number,...
1. Consider a design of a low-speed open-circuit subsonic wind tunnel. The goal is to achieve...
1. Consider a design of a low-speed open-circuit subsonic wind tunnel. The goal is to achieve a free stream velocity of 150 m/s at the test section of this tunnel. This wind tunnel is equipped with a U-tube mercury manometer that measures the pressure difference between the inlet (the settling chamber) and the test section. If the fan of the wind tunnel is able to generate the maximum pressure difference corresponding to a height difference of 10 cm on the...
Honeycomb Flow Straightener Anti-Turbulence Screens Silencer Fan Diffuser Test Section Inlet 9) For the air wind...
Honeycomb Flow Straightener Anti-Turbulence Screens Silencer Fan Diffuser Test Section Inlet 9) For the air wind tunnel shown above in Q8: (6 points) Assuming a circular cross section, the atmospheric pressure is 101.325 kPa, density of air is 1.2 kg/m², and absolute viscosity of air is 1.825*10-Ns/m² (assume there are no losses in the wind tunnel) Contraction ratio: 7| Diffuser length: 3 m Test section diameter = test section length = 70 cm a) When a static-pitot tube placed in...
8) (1 point) Honeycomb Flow Straightener -Anti-Turbulence Screens Silencer Diffuser Fan Test Section Inlet The wind...
8) (1 point) Honeycomb Flow Straightener -Anti-Turbulence Screens Silencer Diffuser Fan Test Section Inlet The wind tunnel shown above is; a) open circuit/suction/low speed wind tunnel b) open circuit/blow-down low speed wind tunnel c) closed circuit/suction/supersonic wind tunnel d) closed circuit/blow-down/supersonic wind tunnel 9) For the air wind tunnel shown above in Q8: (6 points) Assuming a circular cross section, the atmospheric pressure is 101.325 kPa, density of air is 1.2 kg/m², and absolute viscosity of air is 1.825*10-Ns/m² (assume...
8) (1 point) Honeycomb Flow Straightener -Anti-Turbulence Screens Silencer Fan Test Section Diffuser Inlet The wind...
8) (1 point) Honeycomb Flow Straightener -Anti-Turbulence Screens Silencer Fan Test Section Diffuser Inlet The wind tunnel shown above is; a) open circuit/suction/low speed wind tunnel b) open circuit/blow-down/low speed wind tunnel c) closed circuit/suction/supersonic wind tunnel d) closed circuit/blow-down/supersonic wind tunnel 9) For the air wind tunnel shown above in Q8: (6 points) Assuming a circular cross section, the atmospheric pressure is 101.325 kPa, density of air is 1.2 kg/m°, and absolute viscosity of air is 1.825*10-5 Ns/m² (assume...
4-For the manometer shown in the Fig. below contains oil and water.For the column heights indicat...
4-For the manometer shown in the Fig. below contains oil and water.For the column heights indicated what is the pressur differential between pipes A and B. CDI water water 650) 20 10 Glycerin S.G-1.26 oil o-o.as S.G 0.85 Dimensions in cm S-The inverted U-tube manometer contains oil S.G.-0.9and water. The pressure differential between A and B, pA-PB is-5kPa Determine the differential reading,h Oil 0.2 m 0.3 m Water 9-Air flows through a pipe at a rate of 200L/s.The pipe consists...
please use bernoulis equation. thanks -/1 Question 4 View Policies Current Attempt in Progress port Water...
please use bernoulis equation. thanks
-/1 Question 4 View Policies Current Attempt in Progress port Water flows through the pipe contraction shown in the figure below. For the given 0.21-m difference h in the manometer level, determine the flowrate Q. Q- Save for Later Attempts: 0 of 5 used Submit Answer
6 The venture meter shown in Figure below carries oil (sg 0.90). The specific gravity of...
6 The venture meter shown in Figure below carries oil (sg 0.90). The specific gravity of the gage fluid in the manometer is 1.40. a. Find the pressure difference between points A and B h. Find the velocity at pointA c. Calculate the volume flow rate of oil. 8 Marks [8 Marks 17 Marks] 75-mm How A. 200- nside 0.50 m
9) For the air wind tunnel shown above in Q8: (6 points) Assuming a circular cross section, the atmospheric pressure is 101.325 kPa, density of air is 1.2 kg/m², and absolute viscosity of air is 1.825*10-Ns/m² (assume there are no losses in the wind tunnel) Contraction ratio: 7 Diffuser length: 3 m Test section diameter = test section length = 70 cm a) When a static-pitot tube placed in the test section with a manometer (manometer fluid is water with...
For the air wind tunnel shown Honeycomb Flow Straightener Anti-Turbulence Screens Silencer Fan Diffuser Test Section Inlet Assuming a circular cross section, the atmospheric pressure is 101.325 kPa, density of air is 1.2 kg/m?, and absolute viscosity of air is 1.825*10-S Ns/m? (assume there are no losses in the wind tunnel) Contraction ratio: 7 Diffuser length: 3 m Test section diameter = test section length = 70 cm a) When a static-pitot tube placed in the test section with a...
1. [20 pts] An indraft wind tunnel pulls air into an inlet, through a contraction, the test section, and the diffuser, as shown below. The test section has a circular cross section and it has a diameter of 0.5 m. Assume the wind tunnel is at sea level and the temperature and pressure of the atmosphere are given by standard atmospheric conditions. (a) If the test section is designed to have a velocity of 200 m/s, determine the Mach number,...
1. Consider a design of a low-speed open-circuit subsonic wind tunnel. The goal is to achieve a free stream velocity of 150 m/s at the test section of this tunnel. This wind tunnel is equipped with a U-tube mercury manometer that measures the pressure difference between the inlet (the settling chamber) and the test section. If the fan of the wind tunnel is able to generate the maximum pressure difference corresponding to a height difference of 10 cm on the...
Honeycomb Flow Straightener Anti-Turbulence Screens Silencer Fan Diffuser Test Section Inlet 9) For the air wind tunnel shown above in Q8: (6 points) Assuming a circular cross section, the atmospheric pressure is 101.325 kPa, density of air is 1.2 kg/m², and absolute viscosity of air is 1.825*10-Ns/m² (assume there are no losses in the wind tunnel) Contraction ratio: 7| Diffuser length: 3 m Test section diameter = test section length = 70 cm a) When a static-pitot tube placed in...
8) (1 point) Honeycomb Flow Straightener -Anti-Turbulence Screens Silencer Diffuser Fan Test Section Inlet The wind tunnel shown above is; a) open circuit/suction/low speed wind tunnel b) open circuit/blow-down low speed wind tunnel c) closed circuit/suction/supersonic wind tunnel d) closed circuit/blow-down/supersonic wind tunnel 9) For the air wind tunnel shown above in Q8: (6 points) Assuming a circular cross section, the atmospheric pressure is 101.325 kPa, density of air is 1.2 kg/m², and absolute viscosity of air is 1.825*10-Ns/m² (assume...
8) (1 point) Honeycomb Flow Straightener -Anti-Turbulence Screens Silencer Fan Test Section Diffuser Inlet The wind tunnel shown above is; a) open circuit/suction/low speed wind tunnel b) open circuit/blow-down/low speed wind tunnel c) closed circuit/suction/supersonic wind tunnel d) closed circuit/blow-down/supersonic wind tunnel 9) For the air wind tunnel shown above in Q8: (6 points) Assuming a circular cross section, the atmospheric pressure is 101.325 kPa, density of air is 1.2 kg/m°, and absolute viscosity of air is 1.825*10-5 Ns/m² (assume...
4-For the manometer shown in the Fig. below contains oil and water.For the column heights indicated what is the pressur differential between pipes A and B. CDI water water 650) 20 10 Glycerin S.G-1.26 oil o-o.as S.G 0.85 Dimensions in cm S-The inverted U-tube manometer contains oil S.G.-0.9and water. The pressure differential between A and B, pA-PB is-5kPa Determine the differential reading,h Oil 0.2 m 0.3 m Water 9-Air flows through a pipe at a rate of 200L/s.The pipe consists...
please use bernoulis equation. thanks
-/1 Question 4 View Policies Current Attempt in Progress port Water flows through the pipe contraction shown in the figure below. For the given 0.21-m difference h in the manometer level, determine the flowrate Q. Q- Save for Later Attempts: 0 of 5 used Submit Answer
6 The venture meter shown in Figure below carries oil (sg 0.90). The specific gravity of the gage fluid in the manometer is 1.40. a. Find the pressure difference between points A and B h. Find the velocity at pointA c. Calculate the volume flow rate of oil. 8 Marks [8 Marks 17 Marks] 75-mm How A. 200- nside 0.50 m
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