Conditions before a shock are T1 = 40°C, p1 = 1.2 bar, and M1 = 3.0....
Conditions before a shock are T1 = 40°C, p1 = 1.2 bar, and M1 = 3.0. An oblique shock is observed at 45° to the approaching air flow.
(a) Determine the Mach number and flow direction after the shock.
(b) What are the temperature and pressure after the shock?’
(c) Is this a weak or a strong shock?
Homework Answers
I have attached the graph which i have used to calculate delta angle and to define weak shock....
if it is not clear please see the forth page
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Conditions before a shock are T1 = 40°C, p1 = 1.2 bar, and M1 =
3.0....
fluid dynamics: 4. (a) List the conditions that cause an oblique shock to form (b) A Mach 2.4 air flow at 450 K and...
fluid dynamics:
4. (a) List the conditions that cause an oblique shock to form (b) A Mach 2.4 air flow at 450 K and 1.9 bar is deflected (6) 15 by a standing oblique shock. Obtain the two possible shock angles (0) and identify the angles associated with the weak shock and the strong shock. 5 (c) Determine the conditions after the weak shock (i.e. calculate T,, p, and M2)
4. (a) List the conditions that cause an oblique shock...
Air at P1=3 bar, T1=288k, M1=1.5 is brought to sonic velocity in a frictionless constant area...
Air at P1=3 bar, T1=288k, M1=1.5 is brought to sonic velocity in a frictionless constant area duct thought which heat transfer can occur: 1. Determine the final pressure and temperature and the heat add during the process 2. What will be the Mach number, pressure and temperature of air if this heat is extracted from the air?
A supersonic airfoil moves through air at 80kPa and -10°C with a Mach number of 2.0. The leading edge of the airfoil deflects the air at an angle of e the weak oblique shock angle, post shock Mach nu...
A supersonic airfoil moves through air at 80kPa and -10°C with a Mach number of 2.0. The leading edge of the airfoil deflects the air at an angle of e the weak oblique shock angle, post shock Mach number, and post shock pressure for this flow
A supersonic airfoil moves through air at 80kPa and -10°C with a Mach number of 2.0. The leading edge of the airfoil deflects the air at an angle of e the weak oblique shock...
A supersonic flow of air with Mach number of M1=2.8 is deflected towards itself by 16o. What is the Mach number M2 behind the a weak oblique shock?
A supersonic flow of air with Mach number of M1=2.8 is deflected towards itself by 16o. What is the Mach number M2 behind the a weak oblique shock?
uo u (b shock u U2 shock Consider a blunt reentry vehicle in the atmosphere moving...
uo u (b shock u U2 shock Consider a blunt reentry vehicle in the atmosphere moving with a velocity uo 3.4 km/s in the upper atmosphere with the effective temperature t-10°C, effective average molecular weight M 24, and effective ration of specific heats y 1.34. The supersonic air flow with respect to the reentry vehicle forms a shock in front. Consider two regions, as shown in the figure, (1) where the air flow velocity is normal to the shock and...
Air flowing with a Mach number of 2 with a pressure of 80 kPa and a...
Air flowing with a Mach number of 2 with a pressure of 80 kPa and a temperature of 30°C passes over a component of an aircraft that can be modeled as a wedge with an included angle of 8° that is aligned with the flow. The flow is turned through an angle of 4°, leading to the generation of an oblique shock wave. Find after the oblique shock: a) the pressure b) the temperature. c) the Mach number after the...
Both qualitatively and quantitatively understand how the properties of a flow change through a normal shock....
Both qualitatively and quantitatively understand how the properties of a flow change through a normal shock. Know why a normal shock is called a normal shock. Know what object shapes cause normal shocks to form, and what object shapes cause attached oblique shocks to form. Know where to find a normal shock or normal shocks on an airplane or rocket for any Mach number ldentify shocks in photographs, and characterize important parts of the flow (supersonic vs subsonic, etc) Qualitatively...
Air at static conditions of 100kPa and 400K and a Mach number of 3.0 is diverted...
Air at static conditions of 100kPa and 400K and a Mach number of 3.0 is diverted by a plate at an angle of 10° with respect to the oncoming flow. An expansion fan is established at the edge of the plate, determine the pressure, temperature and Mach number behind the expansion fan.
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
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 =
fluid dynamics:
4. (a) List the conditions that cause an oblique shock to form (b) A Mach 2.4 air flow at 450 K and 1.9 bar is deflected (6) 15 by a standing oblique shock. Obtain the two possible shock angles (0) and identify the angles associated with the weak shock and the strong shock. 5 (c) Determine the conditions after the weak shock (i.e. calculate T,, p, and M2)
4. (a) List the conditions that cause an oblique shock...
A supersonic airfoil moves through air at 80kPa and -10°C with a Mach number of 2.0. The leading edge of the airfoil deflects the air at an angle of e the weak oblique shock angle, post shock Mach number, and post shock pressure for this flow
A supersonic airfoil moves through air at 80kPa and -10°C with a Mach number of 2.0. The leading edge of the airfoil deflects the air at an angle of e the weak oblique shock...
uo u (b shock u U2 shock Consider a blunt reentry vehicle in the atmosphere moving with a velocity uo 3.4 km/s in the upper atmosphere with the effective temperature t-10°C, effective average molecular weight M 24, and effective ration of specific heats y 1.34. The supersonic air flow with respect to the reentry vehicle forms a shock in front. Consider two regions, as shown in the figure, (1) where the air flow velocity is normal to the shock and...
Air flowing with a Mach number of 2 with a pressure of 80 kPa and a temperature of 30°C passes over a component of an aircraft that can be modeled as a wedge with an included angle of 8° that is aligned with the flow. The flow is turned through an angle of 4°, leading to the generation of an oblique shock wave. Find after the oblique shock: a) the pressure b) the temperature. c) the Mach number after the...
Both qualitatively and quantitatively understand how the properties of a flow change through a normal shock. Know why a normal shock is called a normal shock. Know what object shapes cause normal shocks to form, and what object shapes cause attached oblique shocks to form. Know where to find a normal shock or normal shocks on an airplane or rocket for any Mach number ldentify shocks in photographs, and characterize important parts of the flow (supersonic vs subsonic, etc) Qualitatively...
Air at static conditions of 100kPa and 400K and a Mach number of 3.0 is diverted by a plate at an angle of 10° with respect to the oncoming flow. An expansion fan is established at the edge of the plate, determine the pressure, temperature and Mach number behind the expansion fan.
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
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 =
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