4. Write down the lift curve equation (lift coefficient versus angle of attack) according to the thin airfoil theory. What is the amount of the lift curve slope for a thin airfoil ? NACA 2412 airfoil LEq.(4.57) ut soefficient 0.4 -0.4 Eg. (4,64)- -0.1 Moment coefficient -0.8 - -0.2 -0. • Re-3.1 X 10 O Re -8.9 X 10 -0.4 -8 8 16 24 a, degrees dc = ? da

4. Write down the lift curve equation (lift coefficient versus angle of attack) according to the thin airfoil theory. What is the amount of the lift curve slope for a thin airfoil ? NACA 2412 airfoil LEq.(4.57) ut soefficient 0.4 -0.4 Eg. (4,64)- -0.1 Moment coefficient -0.8 - -0.2 -0. • Re-3.1 X 10 O Re -8.9 X 10 -0.4 -8 8 16 24 a, degrees dc = ? da

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

Consider a rectangular wing with NACA 0009 airfoil section spanning the test section of a wind tunnel, the test section airflow conditions are standard sea level w/a velocity of 116 mi/hr. The wing is at an angle attack of 4° and the wind tunnel force balance measures a lift of 28.43 lbf. What is the area of the wing? R.N = 3.0 X106; C̟ at angle attack of 4° = 0.4 %3D
D
Parvin bhai
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.
7. A 2700-lb car is traveling @ sea level at a constant speed. Its engine is running at 4500 rev/min. and is producing 175 ft-lb of torque. It has a drivetrain efficiency of 90%, a drive axle slippage of 2%, 15-inch-radius wheels, and an overall gear reduction ratio of 3 to 1. If the car's frontal area is 21.5 ft, what is its drag coefficient?
The NACA 4412 airfoil has a mean chamber line given by 0.25 for 0ss0.4 l0.111 02+ 08: - ()'| 0.111 0.2 + 0.8 – (4)*| for 0.4 ss1 Using thin airfoil theory, calculate Cme/4 and Xcp/C when a =3° %3D NIU