KNOWN: Speed and temperature of atmospheric air flowing over a flat plate of prescribedlength and temperature.FIND: Rate of heat transfer corresponding to Rex,c = 10°, 5 × 10³ and 106.SCHEMATIC:AirU∞=25m/sToo=25°Cp=1atm个个个19-TS=125°CASSUMPTIONS: (1) Flow over top and bottom surfaces.L=1mPROPERTIES: Table 4-4, Air (T+= 348K, 1 atm): p = 1.00 kg/m³, v = 20.72 x 10= 0.0299 W/m-K, Pr = 0.700.m/s, k

Answered: Image /qna-images/answer/661ac4a8-43fe-426e-acbe-49ded92bb998.jpg

Answered: KNOWN: Speed and temperature of…

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

See similar textbooks

Similar questions

Q2: A) Assuming linear variation of velocity in the boundary layer i.e. (u/u) =(y/6), up to y= 8 and then u = u, determine using the integral momentum equation, the boundary layer thickness. B) The temperature ratio: [T,-T)/(T, -T)] = sin (zy/0.015) in flow over a flat plate. If k = 0.03 W/m.K, determine the value of convective heat transfer coefficient.
Q.3 Air (density 1.2 kg/m3 and kinematic viscosity 15 centistokes) flows over a flat plate, at zero angle of incidence, at a velocity of 20 m/s. If Reynolds number at transition is taken as 2.5 × 105, maximum distance, from leading edge up to which the boundary layer remains laminar is
answer quickly
Q1: Find the boundary layer thickness (6) equation, the shear stress (to) and the coefficient of drag (C₁) if the velocity distribution in the laminar boundary layer over the face of a spillway was observed to be: u 7- (C)-()*+C)*. U Then calculate the boundary layer thickness and drag force if the air flows over a sharp edged flat plate 0.25m long and 0.5m wide at a velocity 1 m/s, take the air density 1.23 kg/m³ and the kinematic viscosity is 1.46*10-5 m/s².
Problem-2 For the turbulent incompressible boundary layer, the velocity profile is given as u/Ue, y = y/8, Ue and d are boundary-layer edge velocity where, u = and boundary layer thickness, respectively. Using momentum integral equation, prove that: 8/x = 0.383/Re,/5 8% /x = 0.0479/Re/5 and 0/x = 0.0372/Re/5
Air at 20⁰c and 1 ATM flows over a flat plate, v= 35 m/s. The plate is 75 cm long and guarded at 60⁰c. Suppose the depth of one Units on Z, count the transfer of Calor from that plate.
A block, as shown below, is sliding on a thin horizontal layer of water (u = 1.68 x 103 kg/m.s) between ice and the block with a speed of 13 m/s. The thickness of the water layer is 3.32 x 10-5 m. Given the following dimensions of the block, what is the force (F) required to maintain this movement? A = 9 cm B = 9 cm C= 8 cm B 2.96 N 5.33 N 4.14 N 4.74 N
Information Momentum Balance
2. The table below shows experimental data for the shape and pressure distribution on the upper and lower surface of an airfoil at zero angle of attack. X 0 0.25 0.5 0.75 1 Yu 0 0.0952 0.0922 0.0588 0 Fx = dYu dx 5 Y₁ 0 -0.0254 -0.0144 -0.0052 0 PL Pd) d: dx Y = Yu (x) Calculate the drag and lift force on the airfoil by numerically evaluating the integrals = S₁² ( P₂₁ = ['(P₁ - F (P₁ - Pu)dx 0 y = Y₂ (x) Pu 1.000 -1.640 -0.786 -0.212 0 Fy x Pi 1.000 0.589 0.426 0.322 0 Use finite difference approximations of the derivatives and the composite Simpson's rule to evaluate the integrals. Hint: Use central differences to estimate the derivatives wherever possible since they are more accurate than forward or backward differences.
I want the detailed solution to understand a question
You are designing an airfoil for a new hobby RC plane. Because of your limited knowledge, you have mistakenly approximated your airfoil as an ellipse with a = 75mm and b = 12mm. Here, “a” is the depth of your wing and “b” is the thickness. Your plane travels through the air at approximately 20mph (8.9m/s). As it does so, skin friction produces a drag-induced heat of 800W on your wind, of length 1m. Properties of Air: k = 0.025 W/mK, Pr = 0.72, v = 1.847 x 10−5, u = 16.84 x 10−6, p = 1.2 kg/m3, B = 1/Tf (ideal gas), TInfinity = 25oC a) What is the Reynold’s number? Hint: “D” is taken to be the thickness for an elliptical crosssection. b) What is the Nusselt number? c) What is the convection coefficient? d) What is the average temperature of your wing? Assume an ellipse perimeter of approximately 200mm.

Recommended textbooks for you

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Control Systems Engineering

Mechanical Engineering

ISBN:

9781118170519

Author:

Norman S. Nise

Publisher:

WILEY

Mechanics of Materials (MindTap Course List)

Mechanical Engineering

ISBN:

9781337093347

Author:

Barry J. Goodno, James M. Gere

Publisher:

Cengage Learning

Engineering Mechanics: Statics

Mechanical Engineering

ISBN:

9781118807330

Author:

James L. Meriam, L. G. Kraige, J. N. Bolton

Publisher:

WILEY

SEE MORE TEXTBOOKS