What is the lift formula and what is the lift formula?

l (lift) = v (gas density flow rate.

Ring value) where the ring is the path integral of the velocity of the fluid along a closed curve.

If V is the velocity of the fluid, Ds is the unit vector along the closed curve C.

So: <>

The dimension of the ring quantity.

is the square of the length divided by the time.

This equation can also be used to calculate the Magnus effect.

of aerodynamic force. However, the above theory only applies to subsonic speed (more precisely, MA is less than, in supersonic flight due to the fact that air is compressible, Bernoulli's theorem.

No, there is no circulation movement at this time, and the lift mainly depends on the shock waves on the upper and lower surfaces of the wing.

resulting in a pressure difference.

Y (lift) = 1 2p (density) * v2 (square of velocity) s (wing area) cy (lift coefficient) satisfied.

The formula for lift is l (lift) = v (gas density, flow velocity, ring magnitude value).

The lift force is the upward force, that is, the upward force is greater than the downward force, and its resultant force can make the object rise, and the lift force maintains the aircraft in the air.

The causes of lift are complex, as many conditions such as viscosity and compressibility of the actual fluid need to be considered. At present, most of the use is Kutajukovsky's theorem, which is the most accurate method for engineers to calculate the lift of an aircraft.

Specifically, the lift is caused by the circulation around the wing, resulting in an up-and-down pressure difference, which is the lift (y), and the lift and backward induced drag (d) are combined into aerodynamic force (r). The sum of the lift forces flowing through the individual profiles is the lift of the wing. Lift sustains the aircraft in the air.

** of lift.

The difference in air pressure caused by the difference in lift ** in the velocity of the airflow on the upper and lower surfaces of the wing. However, the explanation of the cause of the velocity difference between the upper and lower surfaces of the wing is complicated, and the isochronous theory and fluid continuity theory used in popular science cannot fully explain the cause of the velocity difference.

Two-dimensional wing theory is commonly used in the aviation community, which mainly relies on the Kuta condition, the ring around the wing, Kuta Zhukovsky's theorem and Bernoulli's theorem.

The formula for the lift force is: cl=l (qs), where l is the eigenscale, and in the cylindrical and airfoil problems, respectively, the cylinder diameter and chord length. At the fixed Mach number, the lift coefficient Cl varies with the angle of attack of the aircraft, and when it is not large, the change of Cl with is linear.

Lift refers to a dimensionless quantity that is the ratio of the lift experienced by an object to the product of the air pressure and the reference area. When calculating the lift of an aircraft, the feature length is generally expressed in terms of area.

Lift application: The vast majority of the lift of the aircraft is generated by the wing, the tail usually produces negative lift, and the lift generated by other parts of the aircraft is very small, which is generally not considered. The principle of lift is that the presence of the ring around the wing (attachment vortex) causes the flow velocity of the upper and lower surfaces of the wing to be different, the pressure is different, and the direction is perpendicular to the relative air flow.

The generation of wing lift mainly depends on the action of the upper surface suction, rather than the effect of the positive pressure on the lower surface, the suction formed on the upper surface of the wing accounts for about 60-80% of the total lift, and the lift formed by the positive pressure on the lower surface only accounts for about 20-40% of the total lift. So it cannot be assumed that the aircraft is supported in the air, mainly as a result of the impact of air from under the wing.

There will be various drags in the air when an airplane flies, and the drag force is the aerodynamic force that is opposite to the direction of the airplane's movement, which hinders the progress of the aircraft, and here we also need to understand it. According to the causes of resistance, it can be divided into friction resistance, differential pressure resistance, induced resistance and interference resistance.

The four types of resistance are for low-speed aircraft, and for high-speed aircraft, in addition to these resistances, other drags such as wave resistance are also generated.

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.

l (lift) = v (gas density, flow velocity, ring value), where the ring quantity is the path integral of the fluid's velocity along a closed curve. If v is the velocity of the fluid and ds is the unit vector along the closed curve c, then:

The dimension of the ring quantity is the square of the length divided by the time.

This equation can also be used to calculate the aerodynamic force of the Magnus effect.

However, the above theory only applies to subsonic speed (more precisely, MA is less than, in supersonic flight, because the air is compressible, Bernoulli's theorem does not hold, when there is no circulation movement, the lift is mainly caused by the pressure difference caused by the shock waves on the upper and lower surfaces of the wings).

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.

Hello, the relationship between gravity and lift can be expressed by the following formula: F=MG-L, where F represents the total force, M represents the mass of the object, G represents gravity, and L represents lift.

Gravity is a force experienced by an object, it is produced by the combination of the mass of the object and the gravitational force, it will make the object fall downward, the magnitude of the gravitational force depends on the mass of the object and also depends on the magnitude of the gravitational force.

Lift is a reaction force whose magnitude depends on the shape of the object, the velocity of the object, the density of the object, and the environment in which the object is located. The lift force can either make the object rise in this direction or keep the object in the air rolling.

The relationship between gravity and lift can be expressed by the formula F=MG-L, where F is the total force, M is the mass of the object, G is the gravitational force, and L is the lift force. When f is greater than 0, the object will rise upward; When f is less than 0, the object will fall rapidly towards the car.

The relationship between gravity and lift can be expressed as:

f=mg-l, as known in years.

where F is the total force of the aircraft, M is the mass of the aircraft, G is the acceleration due to gravity, and L is the lift.

If the airplane can be in a finch state to keep flying steadily, f must be equal to zero, so the formula for calculating the lift can be expressed as:

l = mg。

There is no direct relationship between the two splits, but it can be expressed by the second law of the bull's rolling and slipping: f=ma, where f is the external force on the object, m is the mass of the object, and a is the acceleration of the object when the external force is applied. It can be seen that the greater the external force (e.g., lift), the greater the acceleration and the greater the influence of gravity.

Newton's second law tells us that the gravitational force of an object is generated by the force reacted by the force of the ascending force, and its relation is: f=ma=m(g+a), where f is the force, m is the mass, a is the acceleration, and g is the acceleration of gravity.

The formula for the relationship between lift and gravity: g mg

The formula for the relationship between lift and gravity is l=wgcosɑ