Liftoff velocity for given weight Solution

STEP 0: Pre-Calculation Summary
Formula Used
Liftoff velocity = 1.2*(sqrt((2*Weight Newton)/(Freestream density*Reference Area*Maximum Lift Coefficient)))
VLO = 1.2*(sqrt((2*W)/(ρ*S*CL,max)))
This formula uses 1 Functions, 5 Variables
Functions Used
sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)
Variables Used
Liftoff velocity - (Measured in Meter per Second) - Liftoff velocity is defined as the velocity of the aircraft at which it first becomes airborne.
Weight Newton - (Measured in Newton) - Weight Newton is a vector quantity and defined as the product of mass and acceleration acting on that mass.
Freestream density - (Measured in Kilogram per Cubic Meter) - Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
Maximum Lift Coefficient - Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack.
STEP 1: Convert Input(s) to Base Unit
Weight Newton: 60.34 Newton --> 60.34 Newton No Conversion Required
Freestream density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Maximum Lift Coefficient: 1.65 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
VLO = 1.2*(sqrt((2*W)/(ρ*S*CL,max))) --> 1.2*(sqrt((2*60.34)/(1.225*5.08*1.65)))
Evaluating ... ...
VLO = 4.11393119786997
STEP 3: Convert Result to Output's Unit
4.11393119786997 Meter per Second --> No Conversion Required
FINAL ANSWER
4.11393119786997 4.113931 Meter per Second <-- Liftoff velocity
(Calculation completed in 00.004 seconds)

Credits

Created by Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
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15 Take-Off Calculators

Take Off Ground Run
Go Takeoff Ground Run = Weight Of Aircraft/(2*[g])*int((2*Velocity of Aircraft)/(Thrust Force-Drag Force-Reference Of Rolling Resistance Coefficient*(Weight Of Aircraft-Lift Force)),x,0,Aircraft Lift Off Speed)
Drag during ground effect
Go Drag Force = (Parasite Drag coefficient+(((Lift Coefficient^2)*Ground effect factor)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)))*(0.5*Freestream density*(Flight Velocity^2)*Reference Area)
Thrust for given liftoff distance
Go Thrust of an aircraft = 1.44*(Weight Newton^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Liftoff Distance)
Liftoff distance
Go Liftoff Distance = 1.44*(Weight Newton^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Thrust of an aircraft)
Liftoff velocity for given weight
Go Liftoff velocity = 1.2*(sqrt((2*Weight Newton)/(Freestream density*Reference Area*Maximum Lift Coefficient)))
Stall velocity for given weight
Go Stall Velocity = sqrt((2*Weight Newton)/(Freestream density*Reference Area*Maximum Lift Coefficient))
Maximum Lift coefficient for given liftoff velocity
Go Maximum Lift Coefficient = 2.88*Weight Newton/(Freestream density*Reference Area*(Liftoff velocity^2))
Ground effect factor
Go Ground effect factor = ((16*Height from Ground/Wingspan)^2)/(1+((16*Height from Ground/Wingspan)^2))
Maximum Lift coefficient for given stall velocity
Go Maximum Lift Coefficient = 2*Weight Newton/(Freestream density*Reference Area*(Stall Velocity^2))
Coefficient of rolling friction during ground roll
Go Coefficient of Rolling Friction = Rolling Resistance/(Weight Newton-Lift Force)
Lift acting on aircraft during ground roll
Go Lift Force = Weight Newton-(Rolling Resistance/Coefficient of Rolling Friction)
Weight of aircraft during ground roll
Go Weight Newton = (Rolling Resistance/Coefficient of Rolling Friction)+Lift Force
Resistance force during ground roll
Go Rolling Resistance = Coefficient of Rolling Friction*(Weight Newton-Lift Force)
Liftoff velocity for given stall velocity
Go Liftoff velocity = 1.2*Stall Velocity
Stall velocity for given liftoff velocity
Go Stall Velocity = Liftoff velocity/1.2

Liftoff velocity for given weight Formula

Liftoff velocity = 1.2*(sqrt((2*Weight Newton)/(Freestream density*Reference Area*Maximum Lift Coefficient)))
VLO = 1.2*(sqrt((2*W)/(ρ*S*CL,max)))

What is an assisted takeoff?

Assisted takeoff is any system for helping aircraft into the air (as opposed to strictly under its own power).

How to Calculate Liftoff velocity for given weight?

Liftoff velocity for given weight calculator uses Liftoff velocity = 1.2*(sqrt((2*Weight Newton)/(Freestream density*Reference Area*Maximum Lift Coefficient))) to calculate the Liftoff velocity, The Liftoff velocity for given weight is a function of the maximum lift coefficient which in turn depends on the stall angle of attack. Liftoff velocity is denoted by VLO symbol.

How to calculate Liftoff velocity for given weight using this online calculator? To use this online calculator for Liftoff velocity for given weight, enter Weight Newton (W), Freestream density ), Reference Area (S) & Maximum Lift Coefficient (CL,max) and hit the calculate button. Here is how the Liftoff velocity for given weight calculation can be explained with given input values -> 1.497957 = 1.2*(sqrt((2*60.34)/(1.225*5.08*1.65))).

FAQ

What is Liftoff velocity for given weight?
The Liftoff velocity for given weight is a function of the maximum lift coefficient which in turn depends on the stall angle of attack and is represented as VLO = 1.2*(sqrt((2*W)/(ρ*S*CL,max))) or Liftoff velocity = 1.2*(sqrt((2*Weight Newton)/(Freestream density*Reference Area*Maximum Lift Coefficient))). Weight Newton is a vector quantity and defined as the product of mass and acceleration acting on that mass, Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area & Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack.
How to calculate Liftoff velocity for given weight?
The Liftoff velocity for given weight is a function of the maximum lift coefficient which in turn depends on the stall angle of attack is calculated using Liftoff velocity = 1.2*(sqrt((2*Weight Newton)/(Freestream density*Reference Area*Maximum Lift Coefficient))). To calculate Liftoff velocity for given weight, you need Weight Newton (W), Freestream density ), Reference Area (S) & Maximum Lift Coefficient (CL,max). With our tool, you need to enter the respective value for Weight Newton, Freestream density, Reference Area & Maximum 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 Liftoff velocity?
In this formula, Liftoff velocity uses Weight Newton, Freestream density, Reference Area & Maximum Lift Coefficient. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Liftoff velocity = 1.2*Stall Velocity
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