Answer number 1 with full detail, fluid mechanics Velocity MeasurementsData & Calculations• The tube is not without its errors while simple.• The most important likelihood for error arises from its dependenceon alignment with the fluid flow direction for the correctness of themeasured velocity."Yaw Angle Dependence"• For an established flow in the open channel flume the fluid velocity(Ah on the manometer) will change at different directions of thepitot tube (0°, 30°, 45°). Velocity MeasurementsQuestions and Conclusions• What trend did you notice in the yaw angle-induced error?• What trend did you notice in the velocity at differentdepths?Describe and explain the reaction of the static and stagnantpressure manometer. Why should this reaction have beenpredicted?

introduction; yaw angle error is misalignment of the rotor from the wind direction.

Answered: What trend did you notice in the yaw…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

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tenjeratures: Evuporator islet water ta, °C FO 15 10 15 CondenseI inici watei ibs C Continue iterations untii all variabies change by an absolute value less than 0.1 percent during an iteration. Ans.: For fa= 10°C and th= 25°C, te= 2.84°C, tc = 34.05°C, qe = 134.39 kW and P = 28.34 kW. %3D
The Mach no. of a fixed geometry inlet at overspeeded for starting mode (Ai= 0.13 m2, ,At= 0.095 m2) 0.41 O 2.77 O 1.72 O 0.49 O
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
A pitotstatic tube to be used in 2n airplane for on-flight measurement was calibrated on ground by using air of density 1.20 kg/m? . A measurement taken at an altitude of 3000 m where the ambient pressure and density were 70 kPa (abs) and 0.91 ke/m? respectively, indicated a velocity of 200 m/s by using the above ground level calibration. Estimate the true speed of the airplane [Take k = 1.4 and R = 287 (kg K)l.
Z\0 @ P 0:10 ZAIN IQ II. Quiz 2 Thermo.pdf Gas flowing through a diverging nozzle has at inlet section a temperature of 20 °C, pressure 120 kN/m² and velocity 300 m/s. At the outlet of the nozzle the velocity has fallen to 100 m/s. Assuming an adiabatic flow, what is the values of outlet pressure, temperature, internal energy and specific enthalpy at outlet section. Take y= 1.333 and Cv= 0.86 kJ/kg K.
For Air: y = 1.4 PART B Question B1 a) With the aid of sketches give a clear account of the operation of convergent nozzles as a function of back pressure. In your answer clearly indicate the critical points (pressure ratios) along the pressure ratio axis. b) Determine the required area ratio A part of the expansion of new teaching and research facilities at QMUL, a new two dimensional blow- down supersonic jet facility is going to be designed, manufactured and installed at our Whitehead Aeronautical Laboratory, Figure QB1. The design Mach number for this facility is M₁ = 2.0. A = A₁ A R=287J/kg K A₁ location at which the area ratio ( A₁ c) What should be the supply pressure to the nozzle (P) in order to have a normal shock wave at a Ax =) is 1.5? A Settling Chamber Po To for this design Mach number. d) For part c, what would be the discharge mass flow rate per unit throat area? You may assume P =105 N/m² and To = 300K. atm Convergent-Divergent Nozzle A AX Schematic of a Supersonic Jet…
Pressure measurement will be carried out with Pitot tube in air flow with average speed 400 m/s, static pressure 0.8 bar and static temperature 15ºC. How many kPa is the total pressure measured by the Pitot tube, since R=287 J/kgK and k=1.4? a. 163.67 b. 182.57 c. 159.75 d. 187.05 e. 178.42
please solve it i need urgent A naturally-aspirated (NA) oil engine (i.e., a slow-speed CI Engine) which produces one power pulse in two revolutions of its crankshaft is to be designed to operate with the following characteristic at sea level where the mean atmospheric conditions are Pa = 101325 N/m2 and ta = 17°C. The value of gas constant of air is Ra = 0.287 kJ/(kg·K). Gross brake power, Wb, gross = 300 kW Volumetric efficiency, hvol = 80% Brake specific fuel consumption, sfcb = 255 g/(kW·h) Actual air-to-fuel ratio, (A/F)act = (m a / m f )act = 17:1 Angular speed of the shaft, w = 125 rad/s Calculate: (i) The required engine capacity Vs, total in cc (cm3), as well as in litres (L); Vs is the swept volume, and (ii) the brake mean effective pressure ( Pbm ). The engine is fitted with a supercharger (SC) so that it may be operated at an al- titude, z, of 3000 m (above sea level) where the atmospheric pressure (Pa) in N/m2 is determined from the following relation: Pa =…
For steady isentropic fl ow, if the absolute temperature increases50 percent, by what ratio does the static pressureincrease?(a) 1.12, (b) 1.22, (c) 2.25, (d ) 2.76, (e) 4.13
Example 2. A high-speed AC 130 gunship is flying at a pressure altitude of 10 km. A Pitot tube on the wingtip measures a pressure of 4.24 x 10ª N/m2. Calculate the Mach number at which the aircraft is flying. Solution: Solving for P1 at an altitude of 10000 m, we get 2.65 x 104 N/m2 k-1 1.4-1 Po k 4.24 x 104) 1.4 M? k – 1 - 1 - 1 1.4 – 1 2.65 x 104 M? = 0.719 M1 = 0.848
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.
The nozzle of a supersonic wind tunnel has an exit-to-throat area ratioof 6.79. When the tunnel is running, a Pitot tube mounted in the testsection measures 1.448 atm. What is the reservoir pressure for thetunnel?

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