Question

Problem 1: A wing with an elliptical planform and an elliptical lift distribution has an aspect...

Problem 1: A wing with an elliptical planform and an elliptical lift distribution has an aspect ratio of 6 and a span of 12 m. The wing loading is 900 N/m2 when flying at a speed of 40 m/s at sea level. Compute the induced drag for this wing. Also compute the downwash and the induced angle of attack (Note: at sea level, ?? = 1.23 kg/m3 ).

Engineering   Mechanical-Engineering   
0 0
Add a commentTranscribed image text
Next >

Homework Answers

Answer #1

0 0
Know the answer?
Your Answer:

Post as a guest

Your Name:

What's your source?

Earn Coins

Coins can be redeemed for fabulous gifts.

Log In

Sign Up

Not the answer you're looking for?
Ask your own homework help question
Similar Questions
Problem 1: A wing with an elliptical planform and an elliptical lift distribution has an aspect...
Problem 1: A wing with an elliptical planform and an elliptical lift distribution has an aspect ratio of 6 and a span of 12 m. The wing loading is 900 N/m2 when flying at a speed of 40 m/s at sea level. Compute the induced drag for this wing. Also compute the downwash and the induced angle of attack (Note: at sea level, ?? = 1.23 kg/m3 ).
A finite wing with a NACA 23012 airfoil has an area of 20 m2 , an...
A finite wing with a NACA 23012 airfoil has an area of 20 m2 , an aspect ratio 5.85, and a span efficiency factor of 0.85. If the wing has a profile drag coefficient of 0.004 at 6° angle of attack, calculate CL and CD.
An airplane has a mass of 48,000 kg, a wing area of 300 m2, a maximum...
An airplane has a mass of 48,000 kg, a wing area of 300 m2, a maximum lift coefficient of 3.2, and a cruising drag coefficient of 0.03 at an altitude of 12,000 m. Determine(a) the takeoff speed at sea level, assuming it is 20 percent over the stall speed, and (b) the thrust that the engines must deliver for a cruising speed of 900 km/h.
A finite wing with an area of 2.0 ft2, an aspect ratio of 7.0 and a...
A finite wing with an area of 2.0 ft2, an aspect ratio of 7.0 and a span efficiency factor of 0.96 is mounted in a wind tunnel where the test section flow velocity is 110 ft/s at standard sea-level conditions. When the wing is pitched to a = -20, no lift is measured. When the wing is pitched to a = 10.00, a lift of 20 lbs is measured. Determine the lift curve slope for the airfoil (i.e., the infinite...
Consider an infinite wing with a NACA 1412 airfoil section and a chord length of 1.5...
Consider an infinite wing with a NACA 1412 airfoil section and a chord length of 1.5 ft. The wing is at an angle of attack of 5° in an airflow velocity of 170 ft/s at standard sea-level conditions. Calculate the lift, drag, and moment about the quarter-chord per unit span. Refer to the Appendix graphs given below for the standard values. (Round the final answers to two decimal places.) 1)The lift per unit span is _______lb. 2)The drag per unit...
The RV-4, a single engine 2-seat light aircraft, has a span of 7.1 meters, an aspect...
The RV-4, a single engine 2-seat light aircraft, has a span of 7.1 meters, an aspect ratio of 5.5, and a span efficiency factor of .65. If the aircraft is flying at a velocity of 260 km/hour at an altitude of 2,000 meters (a) What is the induced drag when the total weight is 5,700N?         (b) What is the induced drag with a velocity of 90 km/hour (the approximate stalling speed)?
Let’s say this airfoil was used in a specific airplane. This airplane is flying at 135...
Let’s say this airfoil was used in a specific airplane. This airplane is flying at 135 mph (60.4 m/s), has a wing area of 150 ft2 (13.94 m2), and flying at an angle of attack of 1º. How much lift will the wings generate? Use the lift equation that was discussed in Lecture 11, and give your answer in Newtons. Also, use an air density of 1.22 kg/m3 ** 1 degree of attack is 0.65.
A cargo plane has two wings and each wing has an area of 34.15 m2. The...
A cargo plane has two wings and each wing has an area of 34.15 m2. The mass of the cargo plane is 9310 kg. When the plane is taking off, the speed of the air over the top of the wing v2 is 1.8 times air speed under the wing v1 (i.e. v2 = 1.8 v1). If v1 is the same as the speed of the plane, what is the minimum speed of the plane v1 to obtain enough lift...
A wing-body model is tested in a wind tunnel with a flow of 100 m/s at...
A wing-body model is tested in a wind tunnel with a flow of 100 m/s at standard sea-level conditions. The wing area is 1.5 m2 and the mean aerodynamic chord length is 0.45 m. Measurements of lift force, L, and moment about the center of gravity, M CG are made using the wind tunnel force balance. B1(a) When the lift is zero, the moment about the center of gravity is measured to be, MCG = −12.4 Nm . At another...
A: An airplane has an effective wing surface area of 18 m2 that is generating the...
A: An airplane has an effective wing surface area of 18 m2 that is generating the lift force. In level flight the air speed over the top of the wings is 61.5 m/s, while the air speed beneath the wings is 58.5m/s. What is the weight of the plane? B: An antifreeze solution is made by mixing ethylene glycol (ρ = 1112 kg/m3) with water. Suppose that the specific gravity of such a solution is 1.1100. Assuming that the total...
ADVERTISEMENT
Need Online Homework Help?

Get Answers For Free
Most questions answered within 1 hours.

Ask a Question
ADVERTISEMENT