The formula for calculating the lift force of an aircraft, the formula for the lift of an aircraft

Lift = (airflow density velocity squared wing area lift coefficient) 2 = dynamic pressure wing area lift coefficient.

l=1/2•ρ•v²•s•cl=q•s•cl

Resistance = (airflow density velocity squared wing area drag coefficient) 2 = dynamic pressure wing area drag coefficient.

d=1/2•ρ•v²•s•cd=q•s•cd

The dynamic pressure of the air flow q=1 2 V

Lift-to-drag ratio l d= cl cd

Both the lift coefficient Cl and the drag coefficient cd of the same airfoil vary with the angle of attack.

The ratio of lift to drag of the wing at a certain speed is called the lift-to-drag ratio, the higher the lift-drag ratio, the higher the aerodynamic efficiency of the airfoil, and the smaller the drag while generating greater lift.

1. The formula for calculating the lift of the aircraft is: L (lift) = V (gas density, flow velocity, ring value).

3. Kuta condition for aircraft to generate lift: In a real and lift-generating wing, the airflow always meets at the trailing edge, otherwise a point with an infinite airflow velocity will be generated at the trailing edge of the wing. This condition is known as the Kuta condition, and only when this condition is met can the wing generate lift.

The formula for calculating the lift of the machine is: l (lift) = v (gas density, flow velocity, ring value).

Flight pressure 1 2 Air density Equal-squared time theory of flight speed: when the air flow passes through the upper and lower surfaces of the wing, because the upper surface is longer than the lower surface, the air flow must pass through the upper and lower surfaces in the same time, according to S=VT, the flow velocity of the upper surface is greater than that of the lower surface, and then according to Bernoulli's theorem: when the non-compressible, ideal fluid flows steadily along the flow tube, the static pressure of the fluid decreases as the flow velocity increases; Conversely, as the flow velocity decreases, the static pressure of the fluid increases.

But the sum of the static and dynamic pressures of the fluid, known as the total pressure, remains the same all the time. This creates a pressure difference that creates lift.

The formula for calculating the lift of an aircraft is pure: l (lift) = v (gas density, flow velocity, ring value).

Flight pressure 1 2 Air density Equal-squared time theory of flight speed: when the air flow passes through the upper and lower surfaces of the wing, because the upper surface is longer than the lower surface, the air flow must pass through the upper and lower surfaces in the same time, according to S=VT, the flow velocity of the upper surface is greater than that of the lower surface, and then according to Bernoulli's theorem: when the non-compressible, ideal fluid flows steadily along the flow tube, the static pressure of the fluid will decrease as the velocity increases before the flow is done; Conversely, as the flow velocity decreases, the static pressure of the fluid increases.

But the sum of the static and dynamic pressures of the fluid, known as the total pressure, remains the same all the time. This creates a pressure difference that creates lift.

l = 1 2pv 2cs (l is lift).

C— Lift coefficient, the lift coefficient increases with the increase of the aircraft's angle of attack, when the aircraft reaches the critical angle of attack (the angle of attack is the angle between the wingchord of the aircraft and the relative direction of the airflow), the lift coefficient is also at the maximum value cmax, when the critical angle of attack is exceeded, the lift coefficient of the aircraft will drop sharply, and the lift of the aircraft will also decrease sharply, which is known as the stall state.

v — the airspeed of the aircraft, the speed at which the aircraft moves relative to the air. As the barmates say, airspeed is not the same as ground speed.

s—the plane projection area of the wing, the larger the projection area of the wing's vertical fingers, the greater the lift.

Expansion: The air velocity on the upper surface of the wing is greater than that on the lower surface, and there is a pressure difference between the upper and lower surfaces, so there is a pressure difference, which is what causes the lift.

The formula for calculating the lift of the machine is: l (lift) = v (gas density, flow velocity, ring value).

Flight pressure 1 2 Air density Equal-squared time theory of flight speed: when the air flow passes through the upper and lower surfaces of the wing, because the upper surface is longer than the lower surface, the air flow must pass through the upper and lower surfaces in the same time, according to S=VT, the flow velocity of the upper surface is greater than that of the lower surface, and then according to Bernoulli's theorem: when the non-compressible, ideal fluid flows steadily along the flow tube, the static pressure of the fluid decreases as the flow velocity increases; Conversely, as the flow velocity decreases, the static pressure of the fluid increases.

But the sum of the static and dynamic pressures of the fluid, known as the total pressure, remains the same all the time. This creates a pressure difference that creates lift.

The lift coefficient of the aircraft c =l (

Where, l represents the lift of the aircraft and q represents the dynamic pressure in aerodynamics, and it is calculated by the formula q = v 2 2

Represents the square) that is, q = v v 2, represents the flight state of the aircraft, the air density of this draft, (related to the altitude, the higher the altitude, the smaller its value, generally by checking the corresponding table can be found by God peeling), v represents the flight speed of the aircraft.

s represents the reference area, and in general, only the wing area of the aircraft can be taken.

In addition, in aerodynamics, according to this formula, as well as the principle of equilibrium of forces, a formula calculated by the integral method is derived, which is much more complicated than this formula because it requires a clear understanding of the pressure and friction distribution of the surface parts of the aircraft, and uses integrals. It's also cumbersome to show it out.

The formula for calculating the lift of an aircraft is pure: l (lift) = v (gas density, flow velocity, ring value).

Flight pressure 1 2 Air density Equal-squared time theory of flight speed: when the air flow passes through the upper and lower surfaces of the wing, because the upper surface is longer than the lower surface, the air flow must pass through the upper and lower surfaces in the same time, according to S=VT, the flow velocity of the upper surface is greater than that of the lower surface, and then according to Bernoulli's theorem: when the non-compressible, ideal fluid flows steadily along the flow tube, the static pressure of the fluid will decrease as the velocity increases before the flow is done; Conversely, as the flow velocity decreases, the static pressure of the fluid increases.

But the sum of the static and dynamic pressures of the fluid, known as the total pressure, remains the same all the time. This creates a pressure difference that creates lift.

The formula for calculating the lift of the machine is: l (lift) = v (gas density, flow velocity, ring value).

Flight pressure 1 2 Air density Equal-squared time theory of flight speed: when the air flow passes through the upper and lower surfaces of the wing, because the upper surface is longer than the lower surface, the air flow must pass through the upper and lower surfaces in the same time, according to S=VT, the flow velocity of the upper surface is greater than that of the lower surface, and then according to Bernoulli's theorem: when the non-compressible, ideal fluid flows steadily along the flow tube, the static pressure of the fluid decreases as the flow velocity increases; Conversely, as the flow velocity decreases, the static pressure of the fluid increases.

But the sum of the static and dynamic pressures of the fluid, known as the total pressure, remains the same all the time. This creates a pressure difference that creates lift.

The formula for calculating the lift of the machine is: l (lift) = v (gas density, flow velocity, ring value).

Flight pressure 1 2 Air density Equal-squared time theory of flight speed: when the air flow passes through the upper and lower surfaces of the wing, because the upper surface is longer than the lower surface, the air flow must pass through the upper and lower surfaces in the same time, according to S=VT, the flow velocity of the upper surface is greater than that of the lower surface, and then according to Bernoulli's theorem: when the non-compressible, ideal fluid flows steadily along the flow tube, the static pressure of the fluid decreases as the flow velocity increases; Conversely, as the flow velocity decreases, the static pressure of the fluid increases.

But the sum of the static and dynamic pressures of the fluid, known as the total pressure, remains the same all the time. This creates a pressure difference that creates lift.