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Consider the flow over a circular cylinder; the incompressible flow over such a cylinder is discussed in Section 3.13. Consider also the flow over a sphere; the incompressible flow over a sphere is described in Section 6.4. The subsonic compressible flow over both the cylinder and the sphere is qualitatively similar but quantitatively different from their incompressible counterparts. Indeed, because of the “bluntness” of these bodies, their critical Mach numbers are relatively low. In particular:
For a cylinder:
For a sphere:
Explain on a physical basis why the sphere has a higher
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Chapter 11 Solutions
Fundamentals of Aerodynamics
- Please answer fastarrow_forwardIn your own words, write a summary of the differences between incompressible flow, subsonic flow, and supersonic flow.arrow_forwardAssume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23 kg/m3 (0.002377 slug/ft3) and 1.01 × 105 N/m2(2116 lb/ft2), respectively. Prove that the flow field specified is not incompressible;i.e., it is a compressible flow as stated without proof .arrow_forward
- 1. Consider a flat plate at an angle of attack α to a M∞ = 4.2 airflow at p∞ = 1 atm[abs].• What is the maximum static pressure that can occur on the plate surface andwhile the shock wave is still attached at the leading edge?• At what value of α does this occur? gamma = 1.4 and R = 287 J/kgK. THERE IS NO PICTURE FOR THIS QUESTIONarrow_forwardit is aerodynamicarrow_forwardI need help on 4aarrow_forward
- Assume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23 kg/m3 (0.002377 slug/ft3) and 1.01 × 105 N/m2 (2116 lb/ft2), respectively. Consider a low-speed open-circuit subsonic wind tunnel with aninlet-to-throat area ratio of 12. The tunnel is turned on, and the pressuredifference between the inlet (the settling chamber) and the test section isread as a height difference of 10 cm on a U-tube mercury manometer.(The density of liquid mercury is 1.36 × 104 kg/m3.) Calculate thevelocity of the air in the test section.arrow_forwardQ.5. With careful design, one can orient the bend on the lower wall so that the reflected wave is exactly canceled by the return bend, as shown. This is a method of reducing the Mach number in a channel (a supersonic diffuser). If the bend angle is 10°, find (a) the downstream width h and (b) the downstream Mach number. Assume a weak wave. M= 3.5 Shock 1 m Shockarrow_forward2arrow_forward
- Part bcd if u dont know all parts please skip it otherwise downvotearrow_forwardA flow with Mach number M1 = 2 and pressure p1 = 1 atm is turned away from itself twice,first through an angle of 10 deg and then through a second angle of 20 deg. Compute the Machnumber and the static pressure downstream of the second turn. Then, suppose that the original flow(M1 = 2 and p1 = 1 atm) is turned away from itself through a single turn of 30 deg. Compute theMach number and static pressure downstream of this turn, and show that the values are the sameas for the first flow with two turns totaling 30 deg.3arrow_forwardA tiny scratch in the side of a supersonic wind tunnelcreates a very weak wave of angle 17°, as shown in Fig., after which a normal shock occurs. The air temperaturein region (1) is 250 K. Estimate the temperaturein region (2).arrow_forward
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