What trend did you notice in the yaw angle-induced error?
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- Air at 20C flows at 1 m/s between two parallel flat plates spaced 5 cm apart. Estimate the distance from the entrance to the point at which the hydrodynamic boundary layers meet.Discuss the significance of Reynolds number in pressurized flow analysis ?Answer completely. The Fanning equation is essentially the same as the Darcy-Weisbach equation but differs by their friction factors. What is the relationship between the friction factor, f, of the Darcy-Weisbach equation and the friction factor, f’, of the Fanning equation?
- 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 QUESTIONThe instrument fairing on an aircraft is shown below, consisting of a forward ramp at30◦, a horizontal section, and a rear ramp at 25◦. During a flight in air at Mach 5.5,the static pressure is 42.6 kPa and the static temperature is 250 K. An oblique shockforms at the turn of the forward ramp, two expansion fans form at the front and rear ofthe horizontal section, and a second oblique shock forms at the turn of the rear ramp. (a) Calculate the Mach numbers and pressures at regions 2, 3, 4, and 5. (b) Determine stagnation pressure ratio p05/p01. (c) Tabulate the angles of all oblique shocks waves leading/trailing expansion waves relative to horizontal (not relative to flow angle). Gamma = 1.4, R=287 J/kgK PLEASE SHOW ALL WORKOn March 16, 1990, an Air Force SR-71 set a new continental speedrecord, averaging a velocity of 2112 mi/h at an altitude of 80,000 ft.Calculate the temperature (in degrees Fahrenheit) at a stagnation point onthe vehicle.
- A dry gas well equipped 30 MMcfd with 85psig tubing pressure must be compressed to 300 psig for sales by centrifugal compressor design What is the amount of actual power required to perform this job, estimate the minimum number of compression stages required for optimum compression efficiency? Additional data nsty = 0.069 cuft , suction temperature 85 K = 1.2 . theoretical speed N - 12200 rpm average deviation factor -0.85atmospheric pressure (assumed xd)=14.71 psia1. A flat plate airfoil with a chord length of 1 m and a width of 6 m is required to generate a lift of 40, 000 N when flying in air at a Mach number of 2.0, a temperature of −20°C and a pressure of 105 P a. What is the required angle of attack? What is the wave drag at this angle of attack? 2. A symmetrical diamond-shaped airfoil is placed at an angle of attack of 2° in a flow at Mach 2 and static pressure of 2×103 P a. The half-angle at the leading and trailing edges is 3° . If its total surface area (top and bottom) is 4 m2 , find the forces due to lift and wave drag acting on the airfoil.Write the practical application of the Aerodynamics. How to Calibration of Air Velocity from Pressure Using Sub-Sonic Wind Tunnel? Write the components of Sub-Sonic Wind Tunnel?
- Consider an oblique shock wave with a wave angle of 36.87◦. Theupstream flow is given by M1 = 3 and p1 = 1 atm. Calculate the totalpressure behind the shock usinga. p0,2/p0,1 b. p0,2/p1 Compare the results.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.10 Consider a diamond-shaped airfoil. The maximum thickness is 0.04 and occurs at mid-chord. The freestream Mach number is 2.0, and the airfoil is operating at a 5 degree angle of attack. a)Find the expressions for the lift coefficient, drag coefficient, and lift to drag ratio using shock-expansion theory Cl= 0.2286, Cd= 0.0302, and L/D= 7.57 Please show work