0
Want this question answered?
Be notified when an answer is posted
Add your answer:
Earn +20 pts
How to convert Normal Force lbf to Lift lbf?
Lift lbf = (Normal force lbf) x (cosine of angle of attack)
What is the difference between the Angle of Attack and th Angle of Incidence?
Hi!The angle of incidence is built into the aircraft, and cannot be changed. This angle is the angle that the wing makes with a level surface (such as if the ground if the aircraft were parked).The angle of attack (commonly abbreviated AoA), is the angle that the chordline of the airfoil makes with the relative wind. So if you were in straight and level flight, maintaining altitude, the angle of attack would be zero degrees.When an aircraft exceeds a critical angle of attack (which is determined by the design of the airplane), the airflow will peel off of the wing, causing the wing to stop producing lift. The aircraft is, in this scenario, stalled.Hope this helps.Source(s):PPL ASEL 6/17/08
What is angle of an airplane with Horizon in takeoff time?
The angle of the airplane, (or more importantly the wing) at the time of take-off depends on a few factors. While flat on the ground, there is a built in angle to the wing (called the chord) in relation to the level centerline of the aircraft ( called the datum). This is called the angle of incidence. As the pilot accelerates the aircraft down the runway, aerodynamic force on the elevators will cause the nose to rise up. The difference between the angle the wind is hitting the aircraft and the chord line is called the Angle of Attack. At a steady speed, the bigger the angle of attack, the more lift a wing will produce up to a certain point (usually about 25 degrees). At that angle, the wing stalls and lift is lost on the wing until the AOA is reduced, granted the speed is constant. Also if the wing is held at a perticular AOA, and wind speed over the wing is increased, lift will increase also. So it really depends on the speed of the aircraft and how much lift it need to get off the ground. But the rotation angle is different on every plane. Usually they try to keep the angle the same and adjust the speed of the take-off to make more lift.
What is the difference between the angle of attack and angle of incidence?
Zero degrees.
What angle does a plane lift off?
15 degrees
How does angle of attack affect lift and drag?
A higher angle of attack has an increase of both lift and drag.
How does the angle of attack affect the amount of lift?
Inclination Effects on Lift. As a wing moves through the air, the wing is inclined to the flight direction at some angle. The angle between the chord line and the flight direction is called the angle of attack and has a large effect on the lift generated by a wing.
What is the point at which lift starts to drop off?
This is termed the Critical Angle of Attack and represents a maximum in the Lift Coefficient vs. Angle of Attack curve. If the angle of attack is increased beyond this point, the wing will stall. For most airfoils, the critical angle of attack is around 15 deg. For swept back wings it is typically higher.
What is the difference between angle of attack and positive angle of attack?
Angle of attack may be negative or positive - it's simply the angle between the wing chord line and the oncoming airflow. If it's positive then the aircraft will benefit from the lift that is provided, if it's negative then there is no lift (but there's still drag). This is a potentially dangerous situation, unless you wish your aircraft to descend.
What three things are needed for flight?
Differences in air pressure, an angle of attack, and lift
How to convert Normal Force lbf to Lift lbf?
Lift lbf = (Normal force lbf) x (cosine of angle of attack)
What two conditions normally cause an increase in lift?
increased angle of attack and increased speed
What control stall margin?
Stall margin is the difference in the critical angle of attack and the angle of attack in which you are operating.Example:Suppose, critical angle of attack= 15°AOA operating in a flight= 5°then, Lift by the wing balances the weight of the airplane with a STALL MARGIN= 10°Stall Margin is being controlled by an angle of attack and the position of flap control..CHEERS!
Why do flow separates over an airfoil?
Because of a change in the angle of attack. When you exceed the critical angle of attack there is not enough wind passing over the airfoil and therefore disrupting lift, the airfoil stalls.
What is the coefficient of lift for a NACA 1412 airfoil at angle of attack of 4 and Mach .8?
min lift coeff of 1412 =.60 thefore Cl will be 1.10 at angle of attatck 4 and mach .8
Why does an unsymmetrical wing have more lift than an symmetrical wing at zero angle of attack?
Bernoulli's theorem
What is the angle of attack of a helicopter blade?
It varies for all blades collectively as you pull up or push down on the collective. and alternates from side-to-side and front-to back as you move the cyclic. If you move the cyclicto the right it decreases the angle of attack on the right side and increases the angle of attack on the left side. Since the right side loses lift and the left side gains lift the helicopter will bank and turn to the right.The angle of attack of all the blades at hover will be about zero.
