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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.
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How does angle of attack affect lift and drag?
A higher angle of attack has an increase of both lift and drag.
What doesnt affect the amount of lift on an airplanes wing?
The best way to answer this question would be to say what does effect the lift of a wing. Pretty much the only things that effect the lift of a wing are the density of the air over the wing, the surface area of the wing, the speed of air over the wing and the angle of attack. Everything else has no effect on the amount of lift on 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 is a loss of lift that can cause an airplane to crash?
A STALL, where the wing exceeds it's maximum angle of attack for the conditions (speed, g-force, etc>) under which the airplane is flying. Air separation over the top of the wing increases as angle of attack (angle of the wing compared to the airflow) increases, until the separation causes a decrease in lift. When under these conditions the amount of lift is less than the weight of the aircraft, the wing is stalled, and the aircraft descends. Since most aircraft don't seem to have an angle of attack meter, the airspeed indicator is usually marked with stall speeds experienced under various specific circumstances.
What two conditions normally cause an increase in lift?
increased angle of attack and increased speed
Why do some helicopters have more than 4 blades?
The number of blades required is proportional to the amount of lift required. There are several factors that affect the amount of lift produced by rotor blades. They are the shape of the air foil, the rotational speed, the angle of attack, the length of the rotor blades, and the strength of the blades. All of these have practical limits. Adding an additional blade helps keep all these parameters within practical limits.
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
