Homework Answers
So the first diffuser
with a single normal shock, the pressure loss is 67.17% but for the
wedge
shaped diffuser it is only 41.97%.
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A supersonic two-dimensional inlet is to be designed to operate at Mach 3.0. Two possibilities wi...
GAS DYNAMICS 4.14 A supersonic inlet is to be designed to operate at Mach 3.0. Two...
GAS DYNAMICS
4.14 A supersonic inlet is to be designed to operate at Mach 3.0. Two possibilities are con- sidered, as shown in Figure 4.48. In one, the compression and deceleration of the flow takes place through a single normal shock (Figure 4.48a); in the other, a wedge-shaped Figure 4.47 A supersonic inlet. M =24 514 Oblique Shock and Expansion Waves 215 M M м. M (b) Figure 4.48 (a) Normal shock diffuser, (b) wedge-shaped diffuser. diffuser (Figure 4.48b) is...
Can you please do this question correctly. Thanks!! 08 Question 2.7 Two possibilities are considered for the design of a two-dimensional jet engine inlet as shown in the figures (a-b) below. The inle...
Can you please do this question correctly. Thanks!!
08 Question 2.7 Two possibilities are considered for the design of a two-dimensional jet engine inlet as shown in the figures (a-b) below. The inlet is to operate at the Mach number Mi, shown in the table below. In the first design configuration, shown in figure (a), the deceleration of the flow takes place through a normal shock. For the second case, shown in figure (b), a wedge-shaped diffuser is used to...
Supersonic aircraft develop shock waves at the engine inlet when it flies supersonically. Consider the two...
Supersonic aircraft develop shock waves at the engine inlet when it flies supersonically. Consider the two types of engine inlets described as follows and calculate the total pressure recovery ratio for each engine inlet design when the aircraft flies at Mach 2.5. Take the specific heat ratio y to be 1.4. (a) A three-shock system (two oblique + one normal, external compression inlet) as shown in Fig. 1 Please note that the two blue arrows are not part of the...
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....
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 2.8 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...
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...
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...
GAS DYNAMICS
4.14 A supersonic inlet is to be designed to operate at Mach 3.0. Two possibilities are con- sidered, as shown in Figure 4.48. In one, the compression and deceleration of the flow takes place through a single normal shock (Figure 4.48a); in the other, a wedge-shaped Figure 4.47 A supersonic inlet. M =24 514 Oblique Shock and Expansion Waves 215 M M м. M (b) Figure 4.48 (a) Normal shock diffuser, (b) wedge-shaped diffuser. diffuser (Figure 4.48b) is...
Can you please do this question correctly. Thanks!!
08 Question 2.7 Two possibilities are considered for the design of a two-dimensional jet engine inlet as shown in the figures (a-b) below. The inlet is to operate at the Mach number Mi, shown in the table below. In the first design configuration, shown in figure (a), the deceleration of the flow takes place through a normal shock. For the second case, shown in figure (b), a wedge-shaped diffuser is used to...
Supersonic aircraft develop shock waves at the engine inlet when it flies supersonically. Consider the two types of engine inlets described as follows and calculate the total pressure recovery ratio for each engine inlet design when the aircraft flies at Mach 2.5. Take the specific heat ratio y to be 1.4. (a) A three-shock system (two oblique + one normal, external compression inlet) as shown in Fig. 1 Please note that the two blue arrows are not part of the...
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....
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 2.8 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...
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...
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...
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