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 (Pdynamic), Area (A) and lift coefficient (CL) 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=Pdynamic*A*CL 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 (Pdynamic), Area (A) and lift coefficient (CL). 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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