7) Explain the principle of measuring flow velocity using a pitot tube in a low-speed wind...
Velocity data analysis: Air flow speed is tested using a Pitot tube. Table 1 summarizes the Power supply of the wind tunnel and the dynamic pressure DP. The dynamic pressure P, is the difference between the total pressure P, and the static pressure P, measured by the Pitot tube. Please determine: 1) the air flow speed at each power supply (consider room 2) Plot the flow speed vs power supply using a computer 3) If the relation of the flow...
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...
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...
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...
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...
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...
Problem: The altimeter of a low-speed Piper Aztec reads 8000ft. A Pitot tube mounted on the wingtip measures a pressure of 1650 lb/ft2 . If the outside air temperature is 500 deg R, What is the true velocity of the airplane?, What is the equivalent airspeed? How did they get the pressure of 2.34e-3 for airspeed in step 4? (4 Bookmarks) Show all steps: ON Chapter 4, Problem 21P = 1.83x10 E Comment Step 3 of 4 A Calculate the...
1.) In Chapter 4 we will learn how a low-speed wind tunnel generates airflow to study aerodynamic shapes. Consider a tunnel that uses a U-tube mercury manometer attached between the bell inlet (station 1) and the test section (station 2) to measure the static pressure differential (por setting the airspeed of the flow. The pressure differential 1527 N/m2 for a test section airspeed of 50 m/s. What is the height of the unbalanced column of mercury?
b. A very thin wing section is being tested in a low speed wind-tunnel. Assuming that the flow on the surface of the wing produce a laminar boundary layer and the velocity profile is given as follows; Determine the theoretical value of; 8" where Rex is the Reynold number at a distance x from the leading edge of the wing, Rei is the Reynolds number at the trailing edge of the wing and Cr (or Cp) is the average skin...