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GAS DYNAMICS 4.14 A supersonic inlet is to be designed to operate at Mach 3.0. Two...
A supersonic two-dimensional inlet is to be designed to operate at Mach 3.0. Two possibilities will be considered, as shown in figure . In one, the compression and slowing down of the flow take place through a single normal shock; in the other, a diffuser that has a double- wedge, the deceleration occurs through two weak oblique shocks, followed by a normal shock. The wedge turning angles are each 8°. Compare the loss in stagnation pressure for the two cases....
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...
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...
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....
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...
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...