Shockwave is created toward aft end of object

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Heavy Duty Truck Systems
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Chapter 21 / Exercise 22
Heavy Duty Truck Systems
Bennett
Expert Verified
Shockwave is created toward aft end of object
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Heavy Duty Truck Systems
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Chapter 21 / Exercise 22
Heavy Duty Truck Systems
Bennett
Expert Verified
Transonic FlightLocal velocities greater than the free -stream airspeed. Effects of compressibility begin to occur.Notice that the up wash and flow direction change well ahead of the leading edge.Assume that a speed change from 0.50M to 0.72 occurs and .72 is the critical M number for this airfoil.
HIGH SPEED FLIGHTSubsonic - Mach Numbers below 0.75(all local speeds are less than Mach 1)Transonic - Mach 0.75 to 1.20(local speeds are greater and less than Mach 1)Supersonic - Mach 1.20 to 5.00(all local speeds are greater than Mach 1)> Hypersonic- 5.0 or greater
Transonic FlightOccurs when some local flows over an airfoil are supersonic while others are subsonic.The transonic region is from mach 0.75 to 1.20The Critical Mach Number is the mach number at which sonic flow first appears on an airfoil/wing.It is important to remember that transonic flow can occur on helicopter rotor blades, aeronautic propellers, and on internal parts such as nozzle flows, and inlets.The Critical Mach Number is the mach number at which sonic flow first appears on an airfoil/wing.It is important to remember that transonic flow can occur on helicopter rotor blades, aeronautic propellers, and on internal parts such as nozzle flows, and inlets.
Types of High-Speed Flight- Since an aircraft will have some aerodynamic shape and will be developing LIFT, there will be LOCAL FLOWS on the surfaces that are greater than the speed of flight. It is possible to have both subsonic and supersonic flows on an aircraft at the same time. Thus, an aircraft can experience compressibility effects well BELOW the speed of sound.
As the critical Mach number .72 is exceeded an area of supersonic airflow is created and a normal shock wave forms a boundary between supersonic and subsonic flow.Principal effect- large increase in the static pressure of the airstream behind the wave.If the shock wave is strong, boundary layer behind may lack energy and airflow separation occurs.It takes greater speeds for this to occur. See diagrams.
Study review questionsThe critical Reynolds number is used to predicta. the amount of lift produced by an airfoil b. the amount of drag produced by an airfoilc. the point where the airflow turns turbulent d. the point where the boundary layer begins
a._____ angle of attack b. _____ lift c. _____ drag d.___ center of pressure e. ___ resultant2Verbal Quiz option
3. Throughout most of the flight range of a typical airfoil, at the usual angles of attack, the CP moves forward as the angle of attack increases, and backward as the angle of attack decreases.a. trueb. falseVerbal quiz option
4. The speed of sound is a. the speed when the first airflow on the aircraft goes supersonic.b. the ratio of the aircraft speed to the temperature.

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