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What is the Mach number of a military jet traveling at 1250 km/h. If the atmospheric temperature is -32 degree Celsius.

Which of the following statement is NOT correct about the Mach number?     If the Mach number value is between 0.8 and 1.2, then the flow is supersonic.     The internal duct flow analysis mainly depends only two types of flow, supersonic and subsonic flow.     If the Mach number value is between 0.3 and 0.8, then the flow is subsonic.     Density effects are negligible for Mach number less than 0.3.

Moving to another question will save this res Question 10 The static temperature of a moving fluid is greater than stagnation pressure equals to stagnation temperature greater than stagnation temperature smaller thag stagnation temperature AMoving to another question will save this respon

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Question 3: a) In a '72.77' mm diameter pipeline conveying air, the inlet Mach number is measured to be $0.5198'. Find the length of the pipeline at which the flow conditions become sonic. Assume standard air properties and the average friction factor obtained from independent tests is 0.02. Also obtain Mach number at 1 m from the inlet of the pipe.

SAE 10W-30 oil with viscosity 1 x 10-4 lbf s/ft2 is used as a lubricant between two parts of a machine that slide past one another with a velocity difference of 4 ft/s. What spacing, in inches, is required if you don't want a shear stress of more than 2 lbf/ft²?

At a section in a nozzle (air flow), following properties are known. Po = 1000 KPa; To=500k ; V = 200 m/see é) The temperature (T) at this section is (in K), a. 480; b. 500; c. 520; d. 540; e.560 (ti) The Mach number (M) i's, a. 0.26 ; b. 0:36 ; C. 0.46;d.0.56;e.a66 3.

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Question B2 a) At a given instant of time, two pressure waves, each moving at the speed of sound, emitted by a point source moving with a constant velocity in a fluid in at rest are shown in figure QB2. Determine the Mach number involved and indicate with a sketch the instantaneous location of the point source. R=5 cm 12 cm Figure QB2 R=24 cm [8 Marks] b) The gas velocity across a normal shock wave decreases from 480 m/s to 160 m/s. If the pressure and density upstream of the shock are 62 kPa and 1.5 kg/m ³, find the pressure and density downstream of the shock and the specific heat ratio of the gas. c) An aircraft is in supersonic flight at 11 km altitude on a standard day. The true air speed of the plane is 695 m/s. Calculate the flight Mach number of the aircraft. A total head tube is attached to the plane is used to sense stagnation pressure which is converted to flight Mach number by an on-board computer. However, the computer programme has ignored the normal shock wave that…

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Please anybody answer this ASAP,i need the answer in 40 min Air flows through a normal shock wave, upstream conditions are V₁= 650 m To1= 550 k and po₁= 750 kPa. Calculate the downstream determine conditions: *)Ma2, *)T2, *)p2 and *)02.

DONT ANSWER PART A, B and C. Just answer the extra question for which I have attached the picture.    THanks!