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Problem 4 (15%) A supersonic wind tunnel operates with air at the total pressure Pt temperature...
A blow down supersonic wind tunnel has a test section area of 0.2 m2 and a design Mach number of 2.5. The pressure and temperature in the high pressure air tank is 50 MPa and 400 K. Ignore all losses...
A blow down supersonic wind tunnel has a test section area of 0.2 m2 and a design Mach number of 2.5. The pressure and temperature in the high pressure air tank is 50 MPa and 400 K. Ignore all losses between the high pressure tank and the test section. a) Estimate the throat area of the nozzle. b) Estimate the static pressure and static temperature in the test section. c) Estimate the required gas temperature in the high pressure tank...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. Ti = °C P1 = kPa m V = b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. P2 = kPa
minimum of 3 significant figures please Dry air flows from a reservoir in which the temperature...
minimum of 3 significant figures please
Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. T1 = °C P. = kPa 777 Vi = S b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. P2 = kPa m...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. T, = °C P1 = kPa V1 = b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. p2 = kPa m V2 =
Can you please do this question correctly,thanks!! 183 184Question 2.6 Air is flowing at supersonic speed over a two-dimensional wedge with an upstream static pressure, P, and static temperature, T,...
Can you please do this question correctly,thanks!!
183 184Question 2.6 Air is flowing at supersonic speed over a two-dimensional wedge with an upstream static pressure, P, and static temperature, T, which are defined in the table below 185 186 Value Design Data Unit 187 188 Upstream static pressure (P) 96 kPa 189 Upstream static temperature (T) 265 CK 190 Upstream mach number (M) 2.55 WATCH 191 Wedge half-angle (e) 18 UNITS 192 193 Your answers 194 a) Find the wedge...
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,...
A compressor is used to charge the supersonic wind tunnel air tanks at the Aerodynamics Research...
A compressor is used to charge the supersonic wind tunnel air tanks at the Aerodynamics Research Center. The tanks have a total volume of 40 m3. Air is inspired at ambient pressure (101 kPa) and temperature (293 K) in a conduit with a diameter of 40 cm at an average velocity of 10 m/s. Assuming that the losses in the system are negligible, determine: (a) the rate of change of the mass of air inside the tanks; (b) the rate...
a wind tunnel nozzle is designed to operate at mach number of 5. to check the...
a wind tunnel nozzle is designed to operate at mach number of
5. to check the flow velocity, a pitot probe is placed at the
nozzle exit. since the probe tip is blunt, a normal shock stans off
the tip of the probe
KARNIVA ifolio- Ma X &Microsoft & 447745 &Senarai Ru 84) Whats x 427301 X ny course/68145/content/447745 1/1 KKKM3223 Fluid Dynamics Question on Compressible Flow (for students not attending the PBL session on 10 and 13 May 2019)...
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...
2. Find the Mach number and air speed corresponding of 500 kPa(abs) in an air flow with a (static) pressure of 100 kPa...
2. Find the Mach number and air speed corresponding of 500 kPa(abs) in an air flow with a (static) pressure of 100 kPa and measured (stagnation) temperature of 500 K. DISCUSSION: Suppose that, instead of assuming that a normal shock occurs upstream of the Pitot tube, it is assumed that the flow upstream is ISENTROPIC... what would the estimated flow speed be in that case? (NOTE: A normal shock is always observed to form upstream of bluff bodies such as...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. Ti = °C P1 = kPa m V = b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. P2 = kPa
minimum of 3 significant figures please
Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. T1 = °C P. = kPa 777 Vi = S b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. P2 = kPa m...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. T, = °C P1 = kPa V1 = b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. p2 = kPa m V2 =
Can you please do this question correctly,thanks!!
183 184Question 2.6 Air is flowing at supersonic speed over a two-dimensional wedge with an upstream static pressure, P, and static temperature, T, which are defined in the table below 185 186 Value Design Data Unit 187 188 Upstream static pressure (P) 96 kPa 189 Upstream static temperature (T) 265 CK 190 Upstream mach number (M) 2.55 WATCH 191 Wedge half-angle (e) 18 UNITS 192 193 Your answers 194 a) Find the wedge...
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,...
A compressor is used to charge the supersonic wind tunnel air tanks at the Aerodynamics Research Center. The tanks have a total volume of 40 m3. Air is inspired at ambient pressure (101 kPa) and temperature (293 K) in a conduit with a diameter of 40 cm at an average velocity of 10 m/s. Assuming that the losses in the system are negligible, determine: (a) the rate of change of the mass of air inside the tanks; (b) the rate...
a wind tunnel nozzle is designed to operate at mach number of
5. to check the flow velocity, a pitot probe is placed at the
nozzle exit. since the probe tip is blunt, a normal shock stans off
the tip of the probe
KARNIVA ifolio- Ma X &Microsoft & 447745 &Senarai Ru 84) Whats x 427301 X ny course/68145/content/447745 1/1 KKKM3223 Fluid Dynamics Question on Compressible Flow (for students not attending the PBL session on 10 and 13 May 2019)...
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...
2. Find the Mach number and air speed corresponding of 500 kPa(abs) in an air flow with a (static) pressure of 100 kPa and measured (stagnation) temperature of 500 K. DISCUSSION: Suppose that, instead of assuming that a normal shock occurs upstream of the Pitot tube, it is assumed that the flow upstream is ISENTROPIC... what would the estimated flow speed be in that case? (NOTE: A normal shock is always observed to form upstream of bluff bodies such as...
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