Lift for a level, unaccelerated flight at negligible thrust angle Calculator

Category	Physics ↺
Physics	Flight Stability and Control ↺
Flight-Stability-And-Control	Airplane Performance ↺
Airplane-Performance	Thrust Required for Level Unaccelerated Flight ↺

✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluidⓘ Dynamic Pressure [P_dynamic]			+10% -10%
✖The area is the amount of two-dimensional space taken up by an object.ⓘ Area [A]			+10% -10%
✖The lift coefficient (CL) is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. ⓘ lift coefficient [C_L]			+10% -10%

✖The lift force, lifting force or simply lift is the sum of all the forces on a body that force it to move perpendicular to the direction of flowⓘ Lift for a level, unaccelerated flight at negligible thrust angle [L]

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Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has created this Calculator and 200+ more calculators!

Sai Venkata Phanindra Chary Arendra

Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad

Sai Venkata Phanindra Chary Arendra has verified this Calculator and 100+ more calculators!

< 11 Other formulas that you can solve using the same Inputs

Diagonal of a Rectangle when breadth and area are given

Diagonal=sqrt(((Area)^2/(Breadth)^2)+(Breadth)^2) GO

Diagonal of a Rectangle when length and area are given

Diagonal=sqrt(((Area)^2/(Length)^2)+(Length)^2) GO

Side of a Kite when other side and area are given

Side A=(Area*cosec(Angle Between Sides))/Side B GO

Perimeter of rectangle when area and rectangle length are given

Perimeter=(2*Area+2*(Length)^2)/Length GO

Buoyant Force

Buoyant Force=Pressure*Area GO

Perimeter of a square when area is given

Perimeter=4*sqrt(Area) GO

Diagonal of a Square when area is given

Diagonal=sqrt(2*Area) GO

Length of rectangle when area and breadth are given

Length=Area/Breadth GO

Breadth of rectangle when area and length are given

Breadth=Area/Length GO

Pressure when force and area are given

Pressure=Force/Area GO

Stress

Stress=Force/Area GO

< 11 Other formulas that calculate the same Output

Lift in an accelerated flight

Lift force=(Mass*[g]*cos(Flight path angle))+(Mass*(Velocity^2)/Radius of Curvature)-(Thrust force*sin(Thrust angle)) GO

Forces acting Perpendicular to the body on the flight path

Lift force=Weight*cos(Angle of Inclination)-Mass*((Velocity^2)/Radius) GO

Lift acting on aircraft during ground roll

Lift force=Weight-(Rolling Resistance/Coefficient of Rolling Friction) GO

Lift force for a body moving in a fluid of certain density

Lift force=lift coefficient*Reference Area*Density*(Velocity^2)/2 GO

Lift for an unaccelerated flight

Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle)) GO

Lift Force

Lift force=lift coefficient*Dynamic Pressure*Area GO

Total Lift of wing-tail combination

Lift force=Lift due to wing+Lift due to tail GO

Lift force with angle of attack

Lift force=Drag Force*cot(Angle of attack) GO

Lift for given glide angle

Lift force=Drag Force/tan(Glide angle) GO

Lift during level turn

Lift force=Weight/cos(Bank angle) GO

Lift for a given load factor

Lift force=Load factor*Weight GO

Lift for a level, unaccelerated flight at negligible thrust angle Formula

Lift force=Dynamic Pressure*Area*lift coefficient
L=P<sub>dynamic*A*C<sub>L</sub>

More formulas

Thrust required for level, unaccelerated flight GO

Weight of aircraft for a level, unaccelerated flight at negligible thrust angle GO

Thrust-to-weight ratio GO

Thrust for given coefficients of lift and drag GO

Weight of aircraft for given coefficients of lift and drag GO

Coefficient of Lift for given thrust-to-weight ratio GO

Coefficient of Lift for given thrust and weight GO

Minimum Thrust required GO

Minimum Thrust required for given lift coefficient GO

Lift coefficient for given minimum required thrust GO

Minimum Thrust required for given weight GO

What happens if the lift is less than weight?

If lift becomes less than weight, the aircraft loses altitude. When the lift is greater than the weight, the aircraft gains altitude.

How to Calculate Lift for a level, unaccelerated flight at negligible thrust angle?

Lift for a level, unaccelerated flight at negligible thrust angle calculator uses Lift force=Dynamic Pressure*Area*lift coefficient to calculate the Lift force, The Lift for a level, unaccelerated flight at negligible thrust angle is the product of dynamic pressure, reference area, and coefficient of lift. Lift force and is denoted by L symbol.

How to calculate Lift for a level, unaccelerated flight at negligible thrust angle using this online calculator? To use this online calculator for Lift for a level, unaccelerated flight at negligible thrust angle, enter Dynamic Pressure (P_dynamic), Area (A) and lift coefficient (C_L) and hit the calculate button. Here is how the Lift for a level, unaccelerated flight at negligible thrust angle calculation can be explained with given input values -> 5000 = 10*50*10.

FAQ

What is Lift for a level, unaccelerated flight at negligible thrust angle?

The Lift for a level, unaccelerated flight at negligible thrust angle is the product of dynamic pressure, reference area, and coefficient of lift and is represented as L=P_{dynamic*A*C_L} or Lift force=Dynamic Pressure*Area*lift coefficient. Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid, The area is the amount of two-dimensional space taken up by an object and The lift coefficient (CL) is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. .

How to calculate Lift for a level, unaccelerated flight at negligible thrust angle?

The Lift for a level, unaccelerated flight at negligible thrust angle is the product of dynamic pressure, reference area, and coefficient of lift is calculated using Lift force=Dynamic Pressure*Area*lift coefficient. To calculate Lift for a level, unaccelerated flight at negligible thrust angle, you need Dynamic Pressure (P_dynamic), Area (A) and lift coefficient (C_L). With our tool, you need to enter the respective value for Dynamic Pressure, Area and lift coefficient and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Lift force?

In this formula, Lift force uses Dynamic Pressure, Area and lift coefficient. We can use 11 other way(s) to calculate the same, which is/are as follows -

Lift force=lift coefficient*Dynamic Pressure*Area
Lift force=Weight*cos(Angle of Inclination)-Mass*((Velocity^2)/Radius)
Lift force=(Mass*[g]*cos(Flight path angle))+(Mass*(Velocity^2)/Radius of Curvature)-(Thrust force*sin(Thrust angle))
Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle))
Lift force=Drag Force*cot(Angle of attack)
Lift force=Drag Force/tan(Glide angle)
Lift force=Weight-(Rolling Resistance/Coefficient of Rolling Friction)
Lift force=Weight/cos(Bank angle)
Lift force=Load factor*Weight
Lift force=Lift due to wing+Lift due to tail
Lift force=lift coefficient*Reference Area*Density*(Velocity^2)/2

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