![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 pressure (pi) Static temperature (Ti Corner angle C 2.2 52kPa 280 OK Calculate: Your answers a) Angle of the oblique shock (p) b) Mach number M c) Angle of the reflected wave (p) d) Mach number M e) Static pressure P ß Static temperature T deg I mark 12 marks] deg 2 marks) 12 marks kPa112 marks) KD 12 marks](http://img.homeworklib.com/questions/49f53900-cb1d-11eb-a654-3b44002576a2.png?x-oss-process=image/resize,w_560)
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Question 2.8 Refering to the figure below, a supersonic flow with upstream Mach number, M, static...
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. 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...
4. A supersonic engine inlet is shown below-with a spike centerbody. Suppose the flight Mach number...
4. A supersonic engine inlet is shown below-with a spike centerbody. Suppose the flight Mach number M1 = 2.5, and the pressure is pı = 50,000 N/m². The half-angle of the spike centerbody is 10°, as shown. For a particular mass flow through the engine, it happens that there is an oblique shock at a, and a normal shock wave standing at b. Before entering the second shock wave, the fluid expands through a Prandtl-Meyer turn, as the skech indicates....
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...
M 3. Consider a scenario in which supersonic flow is expanded and turned by 150 through...
M 3. Consider a scenario in which supersonic flow is expanded and turned by 150 through a Prandtl-Meyer expansion wave/fan. Consider the gas to be calorically perfect Air with upstream properties as follows: M1 = 4, P = 20 kPa, T = 250 K. Find: 0-150 M2 (a) freestream Prandtl-Meyer function, Vi. (b) downstream Mach number, M2. (c) downstream static pressure, P2. (d) downstream static temperature, T2.
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...
GAS DYNAMICS 3 M = 2.2 M, = 22 124 12 (a) (b) Figure 4.55 (a)...
GAS DYNAMICS
3 M = 2.2 M, = 22 124 12 (a) (b) Figure 4.55 (a) One-shock spike, (b) two-shock spike diffuser. Figure 4.56 Supersonic flow past a sharp corner. M OM P12 м. 10° Figure 4.57 Flow through incident and reflected oblique shocks. M = 2.4 P1 = 101 kPa 10° Oblique Shock and Expansion Waves 219 Figure 4.58 Oblique shock reflection from a solid wall. M,=2.2 Po= 100 kPa M2 M 30° Air X Jet boundary Figure 4.59...
Question 2.10 A two-dimensional wedge-shaped airfoil, with chord, c, consists of straight-line segments with wedge angl...
Question 2.10 A two-dimensional wedge-shaped airfoil, with chord, c, consists of straight-line segments with wedge angles, θ¡et and θaf, at the leading and trailing edges, as defined in the figure and given in the table below. The airfoil operates at an angle of attack, α, and it is moving through air at a supersonic speed, M. The atmospheric temperature and pressure far upstream of the airfoil are T and p as specified in the table The various flow regions are...
7.8. Air at 800°R and 15 psia is flowing at a Mach number of M =...
7.8. Air at 800°R and 15 psia is flowing at a Mach number of M = 1.8 and is deflected through a 15° angle. The directional change is accompanied by an oblique shock. (a) What are the possible shock angles? (b) For each shock angle, compute the temperature and pressure after the shock.
scouS in a pipe are expre in terms of a Jriction Jactor, J. It is important to frictional forces in pipe flow because t...
scouS in a pipe are expre in terms of a Jriction Jactor, J. It is important to frictional forces in pipe flow because they result in pressure loss which must be accounted for in the piping system. For turbulent flow in pipes, the friction factor is calculated using the Colebrook equation: e/D 2.51 VT where e is the roughness height, D is the pipe diameter and Re is the pipe Reynolds number (dimensionless). For e/D = 0.008 and Re =...
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. 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...
4. A supersonic engine inlet is shown below-with a spike centerbody. Suppose the flight Mach number M1 = 2.5, and the pressure is pı = 50,000 N/m². The half-angle of the spike centerbody is 10°, as shown. For a particular mass flow through the engine, it happens that there is an oblique shock at a, and a normal shock wave standing at b. Before entering the second shock wave, the fluid expands through a Prandtl-Meyer turn, as the skech indicates....
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...
M 3. Consider a scenario in which supersonic flow is expanded and turned by 150 through a Prandtl-Meyer expansion wave/fan. Consider the gas to be calorically perfect Air with upstream properties as follows: M1 = 4, P = 20 kPa, T = 250 K. Find: 0-150 M2 (a) freestream Prandtl-Meyer function, Vi. (b) downstream Mach number, M2. (c) downstream static pressure, P2. (d) downstream static temperature, T2.
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...
GAS DYNAMICS
3 M = 2.2 M, = 22 124 12 (a) (b) Figure 4.55 (a) One-shock spike, (b) two-shock spike diffuser. Figure 4.56 Supersonic flow past a sharp corner. M OM P12 м. 10° Figure 4.57 Flow through incident and reflected oblique shocks. M = 2.4 P1 = 101 kPa 10° Oblique Shock and Expansion Waves 219 Figure 4.58 Oblique shock reflection from a solid wall. M,=2.2 Po= 100 kPa M2 M 30° Air X Jet boundary Figure 4.59...
Question 2.10 A two-dimensional wedge-shaped airfoil, with chord, c, consists of straight-line segments with wedge angles, θ¡et and θaf, at the leading and trailing edges, as defined in the figure and given in the table below. The airfoil operates at an angle of attack, α, and it is moving through air at a supersonic speed, M. The atmospheric temperature and pressure far upstream of the airfoil are T and p as specified in the table The various flow regions are...
7.8. Air at 800°R and 15 psia is flowing at a Mach number of M = 1.8 and is deflected through a 15° angle. The directional change is accompanied by an oblique shock. (a) What are the possible shock angles? (b) For each shock angle, compute the temperature and pressure after the shock.
scouS in a pipe are expre in terms of a Jriction Jactor, J. It is important to frictional forces in pipe flow because they result in pressure loss which must be accounted for in the piping system. For turbulent flow in pipes, the friction factor is calculated using the Colebrook equation: e/D 2.51 VT where e is the roughness height, D is the pipe diameter and Re is the pipe Reynolds number (dimensionless). For e/D = 0.008 and Re =...
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