Maximum Lift coefficient for given liftoff velocity Solution

STEP 0: Pre-Calculation Summary
Formula Used
Maximum Lift Coefficient = 2.88*Weight Newton/(Freestream density*Reference Area*(Liftoff velocity^2))
CL,max = 2.88*W/(ρ*S*(VLO^2))
This formula uses 5 Variables
Variables Used
Maximum Lift Coefficient - Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack.
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.
Liftoff velocity - (Measured in Meter per Second) - Liftoff velocity is defined as the velocity of the aircraft at which it first becomes airborne.
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
Liftoff velocity: 93 Meter per Second --> 93 Meter per Second No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
CL,max = 2.88*W/(ρ*S*(VLO^2)) --> 2.88*60.34/(1.225*5.08*(93^2))
Evaluating ... ...
CL,max = 0.00322873272474656
STEP 3: Convert Result to Output's Unit
0.00322873272474656 --> No Conversion Required
FINAL ANSWER
0.00322873272474656 0.003229 <-- Maximum Lift Coefficient
(Calculation completed in 00.004 seconds)

Credits

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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

Maximum Lift coefficient for given liftoff velocity Formula

Maximum Lift Coefficient = 2.88*Weight Newton/(Freestream density*Reference Area*(Liftoff velocity^2))
CL,max = 2.88*W/(ρ*S*(VLO^2))

What is a high density altitude?

A “high” density altitude means that air density is reduced, which has an adverse impact on aircraft performance.

How to Calculate Maximum Lift coefficient for given liftoff velocity?

Maximum Lift coefficient for given liftoff velocity calculator uses Maximum Lift Coefficient = 2.88*Weight Newton/(Freestream density*Reference Area*(Liftoff velocity^2)) to calculate the Maximum Lift Coefficient, The Maximum Lift coefficient for given liftoff velocity of an aircraft depends upon the instantaneous weight and altitude of the aircraft. Maximum Lift Coefficient is denoted by CL,max symbol.

How to calculate Maximum Lift coefficient for given liftoff velocity using this online calculator? To use this online calculator for Maximum Lift coefficient for given liftoff velocity, enter Weight Newton (W), Freestream density ), Reference Area (S) & Liftoff velocity (VLO) and hit the calculate button. Here is how the Maximum Lift coefficient for given liftoff velocity calculation can be explained with given input values -> 0.000428 = 2.88*60.34/(1.225*5.08*(93^2)).

FAQ

What is Maximum Lift coefficient for given liftoff velocity?
The Maximum Lift coefficient for given liftoff velocity of an aircraft depends upon the instantaneous weight and altitude of the aircraft and is represented as CL,max = 2.88*W/(ρ*S*(VLO^2)) or Maximum Lift Coefficient = 2.88*Weight Newton/(Freestream density*Reference Area*(Liftoff velocity^2)). 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 & Liftoff velocity is defined as the velocity of the aircraft at which it first becomes airborne.
How to calculate Maximum Lift coefficient for given liftoff velocity?
The Maximum Lift coefficient for given liftoff velocity of an aircraft depends upon the instantaneous weight and altitude of the aircraft is calculated using Maximum Lift Coefficient = 2.88*Weight Newton/(Freestream density*Reference Area*(Liftoff velocity^2)). To calculate Maximum Lift coefficient for given liftoff velocity, you need Weight Newton (W), Freestream density ), Reference Area (S) & Liftoff velocity (VLO). With our tool, you need to enter the respective value for Weight Newton, Freestream density, Reference Area & Liftoff velocity 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 Maximum Lift Coefficient?
In this formula, Maximum Lift Coefficient uses Weight Newton, Freestream density, Reference Area & Liftoff velocity. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Maximum Lift Coefficient = 2*Weight Newton/(Freestream density*Reference Area*(Stall Velocity^2))
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