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Air at static conditions of 100kPa and 400K and a Mach number of 3.0 is diverted...
1. A uniform supersonic flow at Mach 2.0, with static pressure of 75 kPa and a...
1. A uniform supersonic flow at Mach 2.0, with static pressure of 75 kPa and a temperature oi 250 К, ехрands aгound a 10 degrees pressure p2, temperature T,, and the fan angle. convex corner. Determine the downstream Mach number M,, Fan angle Мi Mа 10°
1. A uniform supersonic flow at Mach 2.0, with static pressure of 75 kPa and a temperature oi 250 К, ехрands aгound a 10 degrees pressure p2, temperature T,, and the fan angle. convex...
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...
Question 2.8 Refering to the figure below, a supersonic flow with upstream Mach number, M, static...
Question 2.8 Refering to the figure below, a supersonic flow with upstream Mach number, M, static pressure, pi, and static temperature, Ti, as specified in the table below, encounters a corner with a turning angle ore Determine the angle of the oblique shock, ?, the angle of the reflected wave, q, the Mach numbers M2 and M, and the downstream static pressure Ps and static temperature Ty Mi P1 M3 P3 T3 Design Data Value Unit Mach number (M) Static...
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...
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...
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...
Question 1.4 A convergent-divergent nozzle is designed to operate with isentropic flow with an exit Mach number, Me. The flowin the nozzle is supplied from a reservoir of air with a static pressure o...
Question 1.4 A convergent-divergent nozzle is designed to operate with isentropic flow with an exit Mach number, Me. The flowin the nozzle is supplied from a reservoir of air with a static pressure ofPr and a static temperature of Tr and the nozzle has a throat area, AT, as specified in the table below Value Unit Design Data Exit Mach number (ME) 0.55 Area of throat (AT) 600 kPa Reservoir static pressure (PR) 380 WAT Reservoir static temperature (TR) kPa...
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?
please solve this Consider the flow of air in a long frictional pipe under isothermal conditions....
please solve this
Consider the flow of air in a long frictional pipe under isothermal conditions. At the pipe inlet 10 N/m2. respectively, and the velocity the static temperature and pressure are 318 K and 1 is 100 m/s. The pipe diameter is 0.25 m and the friction coefficient is 0.05. For air, take 7 1.4. Analyze the problem as the isothermal Fanno flow and calculate iThe length of pipe to choke the flow. The limiting velocity. The limiting pressure....
Part A The Mach number of the air flow out the nozzle at B is M-04....
Part A The Mach number of the air flow out the nozzle at B is M-04. The air has a temperature of 8°C and absolute pressure of 18 kPa. (Figure 1) Determine the absolute pressure of the air within the large reservoir at A Express your answer to three significant figures and include the appropriate units. 四? AValue Units Submit Request Answer Figure < 1of1 > Part B Determine the temperature of the air within the large reservoir at A...
1. A uniform supersonic flow at Mach 2.0, with static pressure of 75 kPa and a temperature oi 250 К, ехрands aгound a 10 degrees pressure p2, temperature T,, and the fan angle. convex corner. Determine the downstream Mach number M,, Fan angle Мi Mа 10°
1. A uniform supersonic flow at Mach 2.0, with static pressure of 75 kPa and a temperature oi 250 К, ехрands aгound a 10 degrees pressure p2, temperature T,, and the fan angle. convex...
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...
Question 2.8 Refering to the figure below, a supersonic flow with upstream Mach number, M, static pressure, pi, and static temperature, Ti, as specified in the table below, encounters a corner with a turning angle ore Determine the angle of the oblique shock, ?, the angle of the reflected wave, q, the Mach numbers M2 and M, and the downstream static pressure Ps and static temperature Ty Mi P1 M3 P3 T3 Design Data Value Unit Mach number (M) Static...
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...
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...
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...
Question 1.4 A convergent-divergent nozzle is designed to operate with isentropic flow with an exit Mach number, Me. The flowin the nozzle is supplied from a reservoir of air with a static pressure ofPr and a static temperature of Tr and the nozzle has a throat area, AT, as specified in the table below Value Unit Design Data Exit Mach number (ME) 0.55 Area of throat (AT) 600 kPa Reservoir static pressure (PR) 380 WAT Reservoir static temperature (TR) kPa...
please solve this
Consider the flow of air in a long frictional pipe under isothermal conditions. At the pipe inlet 10 N/m2. respectively, and the velocity the static temperature and pressure are 318 K and 1 is 100 m/s. The pipe diameter is 0.25 m and the friction coefficient is 0.05. For air, take 7 1.4. Analyze the problem as the isothermal Fanno flow and calculate iThe length of pipe to choke the flow. The limiting velocity. The limiting pressure....
Part A The Mach number of the air flow out the nozzle at B is M-04. The air has a temperature of 8°C and absolute pressure of 18 kPa. (Figure 1) Determine the absolute pressure of the air within the large reservoir at A Express your answer to three significant figures and include the appropriate units. 四? AValue Units Submit Request Answer Figure < 1of1 > Part B Determine the temperature of the air within the large reservoir at A...
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