modern compressible flows, solve show all steps and solutions Consider a Pitot static tube mounted on the nose of an experimental airplane.A Pitot tube measures the total pressure at the tip of the probe (hencesometimes called the Pitot pressure), and a Pitot static tube combines thiswith a simultaneous measurement of the free-stream static pressure. The Pitotand free-stream static measurements are given below for three different flightconditions. Calculate the free-stream Mach number at which the airplane isflying for each of the three different conditions:a. Pitot pressure = 1.22 × 105 N/m², static pressure = 1.01 × 105 N/m²b. Pitot pressure = 7222 lb/ft², static pressure = 2116 lb/ft²c. Pitot pressure = 13107 lb/ft², static pressure = 1020 lb/ft²

Answered: Consider a Pitot static tube mounted on…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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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.
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For supersonic and hypersonic wind tunnels, a diffuser efficiency, ηD,can be defined as the ratio of the total pressures at the diffuser exit andnozzle reservoir, divided by the total pressure ratio across a normal shockat the test-section Mach number. This is a measure of the efficiency ofthe diffuser relative to normal shock pressure recovery. Consider asupersonic wind tunnel designed for a test-section Mach number of 3.0which exhausts directly to the atmosphere. The diffuser efficiency is 1.2.Calculate the minimum reservoir pressure necessary for running thetunnel.
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1.AB
On October 3, 1967, pilot William J. "Pete" Knight set a world record that still stands to this day for the fastest flight by a crewed, powered aircraft by flying the North American Aviation X-15 as fast as Mach 6.7 at an altitude of 102,000 ft above sea level. Mach number is the ratio of an object’s velocity to the local speed of sound. Using the table for atmospheric properties with respect to altitude, calculate the speed of sound at an altitude of 100,000 ft. What must have been the velocity of the X-15?
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Please solve it correctly I will rate
Please show all work of a,b,&c. A supersonic converging-diverging nozzle is near the exit of a turbojet engine. Its cross-section is circular. The gas has the properties of air, and the flow is isentropic. At the throat location (the minimum area) the air flow is choked (is Mach one) and the throat has diameter of 20 cm.
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Q2.B
An aircraft cruising at 1000-m elevation, z, above you moves past in a flyby. It is moving with a Mach number equal to 1.5 and the ambient temperature is 20 °C. How many seconds after the plane passes overhead do you expect to wait before you hear the aircraft? k = 1.4, R = 287 J/kg.K Mach cone Aircraft moving with velocity V and Mach number Ma

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