Please show all work!! A thin wing with a parabolic chord distribution is flying at speed U∞ and zero angle of attack, asshown below. The fluid has density p and viscosity μ. Determine the drag force, D, and the dragcoefficient, Cp = D(US), where S is the planform area of the wing. Assume laminar flow andexpress your drag coefficient answer in terms of the Reynolds number based on a, Re₁ = U∞a/v.U∞TOP VIEWS = areab|c(y) = quadraticy

Given1. Flight Speed: U∞2. Fluid Properties:Density ρViscosity μ3. Wing Dimensions:Wing has a…

Answered: A thin wing with a parabolic chord…

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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A thin wing with a parabolic chord distribution is flying at speed U∞ and zero angle of attack, asshown below. The fluid has density ρ and viscosity μ. Assume that the flow starts laminar at theleading edge but then transitions to tubulent at xcrit = 0.25a. a) Sketch the regions of laminar and turbulent flow over the wing. Calculate and label relevantdistances.b) Determine the drag force, D, and the drag coefficient, CD ≡ D/((1/2) ρU2∞S), where S is theplanform area of the wing. Express your drag coefficient answer in terms of the Reynoldsnumber based on a, Rea ≡ (U∞a)/nu.
The drag equation for the Gofaster 172 is: D = 0.0003v2A. D is drag in pounds; v is airspeed in feet/second; and A is aircraft frontal area in square feet. At maximum airspeed, D = 140 lbs. How much does max airspeed INCREASE if the fuselage is narrowed such that frontal area A is reduced from 16 ft2 to 14 ft2? Give the answer in ft/sec AND mph. drag is 140 lbs. at maximum airspeed, regardless of frontal area. the question is: what is the INCREASE in max airspeed, not what is the max airspeed.
Solve asap using plot(attach it)
The large block shown is x = 72 cm wide, y = 54 cm long, and z = 9.0 cm high. This block is passing through air (density of air p = 1.43 kg/m³) at a speed of v = 8.61 m/s. Find the drag force F41 acting on the block when it has the velocity vj and a drag coefficient I = 0.812. V2 Fa.1 N %3D Find the drag force F42 acting on the block when it has the velocity vz with a drag coefficient I = 0.893. F42 N Find the drag force Fa.3 acting on the block when it has the velocity vz with a drag coefficient I = 1.06. F4.3 = N EN
Draw the diagram of the dimensionless velocity profile and 11 for the boundary layer on the surface under the pressure gradient and discuss the diagrams by fully mentioning the parameters
1. The Stokes-Oseen formula for drag force Fon a sphere of diameter D in a fluid stream of low velocity V, density p, and viscosity u is: 9T F = 3TuDV + 16PD? Is this formula dimensionally homogenous? 2. The efficiency n of a pump is defined as the (dimensionless) ratio of the power required to drive a pump: QAp input power Where Q is the volume rate of flow and Ap is the pressure rise produced by the pump. Suppose that a certain pump develops a pressure of Ibf/in? (1ft = 12 in) when its flow rate is 40 L/s (1L =0.001 m). If the input power is 16hp (1hp = 760 W), what is the efficiency?
A solid cone of angle 2Ɵ, base r 0 , and density ρ c is rotating with initialangular velocity ω 0 inside a conical seat,as shown below. The clearance h is filled with oilof viscosity μ. Neglecting air drag, derive an analytical expression for thecone’s angular velocity ω(t) if there is noapplied torque.
Two infinite plates a distance h apart are parallel to the xzplane with the upper plate moving at speed V, as inFig. There is a fluid of viscosity μ and constant pressurebetween the plates. Neglecting gravity and assumingincompressible turbulent flow u(y) between the plates, usethe logarithmic law and appropriate boundary conditions toderive a formula for dimensionless wall shear stress versusdimensionless plate velocity. Sketch a typical shape of theprofile u(y).
If a missile takes off vertically from sea level and leavesthe atmosphere, it has zero drag when it starts and zerodrag when it finishes. It follows that the drag must be amaximum somewhere in between. To simplify the analysis,assume a constant drag coefficient, CD, and constant verticalacceleration, a. Let the density variation be modeled by thetroposphere relation. Find an expression for thealtitude z* where the drag is a maximum. Comment onyour result.
QUESTION 6 Above a flat plate, a steady and two-dimensional laminar boundary layer grows without pressure gradient. At x₁ = 0.3 m from the flat plate leading edge, the boundary layer has tickness ō. Assuming a cubic self-similar velocity profile, determine the distance x2 at which the boundary layer thickness is 1.7 times that at x₁. State your answer in metres to three decimal places and enter the numerical value only.
A light aircraft is flying at an altitude of 1000 m. If the wing chord is 1.5 m, and the freestream velocity is determined using the equivalent airspeed of 80 m/s, determine the overall Reynold's Number. Also, determine the coefficient of skin friction drag. (*Tip, determine what time of flow it is based on the calculated RN, then choose the correct Cf formula - laminar or turbulent)
(a) Use the y-momentum equation to show that the pressure gradient across the boundary layer is approximately zero i.e. = 0 . Assume the boundary layer to be a two-dimensional ду steady and incompressible flow. Neglect gravitational forces. State clearly all assumptions made. Use the Bernoulli's equation to prove that the pressure difference is given by (b) P2-P1 = -4pU? for a fluid with constant density p flowing from point 1 to point 2 where pi, U1, A1 are the pressure, velocity and flow cross-section area at point 1 and p2, U2, A2 are the pressure, velocity and flow cross-section area at point 2 respectively. The ratio of the cross-section area A1 = 3.

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