What is the lift coefficient of a wing?
The lift coefficient is defined as: CL = L/qS , where L is the lift force, S the area of the wing and q = (rU2/2) is the dynamic pressure with r the air density and U the airspeed. Similarly, the drag coefficient is written as: CD = D/qS , where D is the drag force and the other symbols have the same meaning.
What is a normal lift coefficient?
Lift Coefficient: Incidence A typical value for the type of airfoil section mentioned is about 1.5. The corresponding value of is around 18 degrees.
How do you find the coefficient of lift?
The lift coefficient Cl is equal to the lift L divided by the quantity: density r times half the velocity V squared times the wing area A. The lift coefficient then expresses the ratio of the lift force to the force produced by the dynamic pressure times the area.
Does the wing or horizontal stabilizer create more lift?
While the wings push the fuselage up, the horizontal stabilizer pushes the tail down. Yes, this does increase load on the wings. Look closely at the airfoil on a horizontal stabilizer, you can see it is inverted.
What is my lift coefficient?
What is the most effective wing shape?
Elliptical Wing The elliptical wing is aerodynamically most efficient because elliptical spanwise lift distribution induces the lowest possible drag.
What is the lift coefficient of NACA 16-123?
For example, the NACA 16-123 airfoil has minimum pressure 60% of the chord back with a lift coefficient of 0.1 and maximum thickness of 23% of the chord. An improvement over 1-series airfoils with emphasis on maximizing laminar flow.
What are modifications of NACA 1234 airfoils?
Modifications. For example, the NACA 1234-05 is a NACA 1234 airfoil with a sharp leading edge and maximum thickness 50% of the chord (0.5 chords) from the leading edge. In addition, for a more precise description of the airfoil all numbers can be presented as decimals.
What are the NACA 4-digit wing sections?
The NACA four-digit wing sections define the profile by: First digit describing maximum camber as percentage of the chord. Second digit describing the distance of maximum camber from the airfoil leading edge in tens of percents of the chord.
What is the maximum camber of NACA 2412 airfoil?
For example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord.