Weight of aircraft in level, unaccelerated flight Calculator

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Thrust and Power Requirements

Lift and Drag Requirements

✖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 Force [F_L]			+10% -10%
✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Thrust [T]			+10% -10%
✖Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction.ⓘ Thrust angle [σ_T]			+10% -10%

✖Weight of Body is the force acting on the object due to gravity.ⓘ Weight of aircraft in level, unaccelerated flight [W_body]

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Formula

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Weight of aircraft in level, unaccelerated flight

Formula

`"W"_{"body"} = "F"_{"L"}+("T"*sin("σ"_{"T"}))`

Example

`"221N"="220N"+("100N"*sin("0.01rad"))`

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Weight of aircraft in level, unaccelerated flight Solution

STEP 0: Pre-Calculation Summary

Formula Used

Weight of Body = Lift Force+(Thrust*sin(Thrust angle))
W_body = F_L+(T*sin(σ_T))
This formula uses 1 Functions, 4 Variables

Functions Used

sin - Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse., sin(Angle)

Variables Used

Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
Lift Force - (Measured in Newton) - 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.
Thrust - (Measured in Newton) - The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.
Thrust angle - (Measured in Radian) - Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction.

STEP 1: Convert Input(s) to Base Unit

Lift Force: 220 Newton --> 220 Newton No Conversion Required
Thrust: 100 Newton --> 100 Newton No Conversion Required
Thrust angle: 0.01 Radian --> 0.01 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

W_body = F_L+(T*sin(σ_T)) --> 220+(100*sin(0.01))

Evaluating ... ...

W_body = 220.999983333417

STEP 3: Convert Result to Output's Unit

220.999983333417 Newton --> No Conversion Required

FINAL ANSWER

220.999983333417 ≈ 221 Newton <-- Weight of Body

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Aircraft Performance » Level Flight » Thrust and Power Requirements » Weight of aircraft in level, unaccelerated flight

Credits

Created by Vinay Mishra

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

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Sai Venkata Phanindra Chary Arendra

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

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< 19 Thrust and Power Requirements Calculators

Minimum Thrust required for given weight

Go Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a wing))

Minimum Thrust required for given lift coefficient

Go Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)))

Minimum Thrust of aircraft required

Go Thrust = Dynamic Pressure*Reference Area*(Zero Lift Drag Coefficient+Coefficient Of Drag Due to Lift)

Weight of aircraft for given required power

Go Weight of Body = Power*Lift Coefficient/(Freestream Velocity*Drag Coefficient)

Power required for given aerodynamic coefficients

Go Power = Weight of Body*Freestream Velocity*Drag Coefficient/Lift Coefficient

Thrust Angle for Unaccelerated Level Flight for given Lift

Go Thrust angle = asin((Weight of Body-Lift Force)/Thrust)

Weight of aircraft in level, unaccelerated flight

Go Weight of Body = Lift Force+(Thrust*sin(Thrust angle))

Weight of aircraft for given coefficients of lift and drag

Go Weight of Body = Lift Coefficient*Thrust/Drag Coefficient

Thrust for given coefficients of lift and drag

Go Thrust = Drag Coefficient*Weight of Body/Lift Coefficient

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

Go Weight of Body = Dynamic Pressure*Area*Lift Coefficient

Thrust of aircraft required for level, unaccelerated flight

Go Thrust = Dynamic Pressure*Area*Drag Coefficient

Thrust for Level and Unaccelerated Flight

Go Thrust = Drag Force/(cos(Thrust angle))

Thrust Angle for Unaccelerated Level Flight for given Drag

Go Thrust angle = acos(Drag Force/Thrust)

Thrust-to-weight ratio

Go Thrust-to-Weight Ratio = Drag Coefficient/Lift Coefficient

Thrust of aircraft required for given Lift-to-drag ratio

Go Thrust = Weight of Body/Lift-to-drag Ratio

Weight of aircraft for given Lift-to-drag ratio

Go Weight of Body = Thrust*Lift-to-drag Ratio

Power required for given total drag force

Go Power = Drag Force*Freestream Velocity

Power required for given required thrust of aircraft

Go Power = Freestream Velocity*Thrust

Thrust of aircraft required for given required power

Go Thrust = Power/Freestream Velocity

Weight of aircraft in level, unaccelerated flight Formula

Weight of Body = Lift Force+(Thrust*sin(Thrust angle))
W_body = F_L+(T*sin(σ_T))

What is the dry operating weight?

Dry Operating Weight (DOW) is the total weight of the aircraft with no fuel, passengers, baggage, and cargo.

How to Calculate Weight of aircraft in level, unaccelerated flight?

Weight of aircraft in level, unaccelerated flight calculator uses Weight of Body = Lift Force+(Thrust*sin(Thrust angle)) to calculate the Weight of Body, The Weight of aircraft in level, unaccelerated flight is the sum of lift and sine component of thrust acting on aircraft. Weight of Body is denoted by W_body symbol.

How to calculate Weight of aircraft in level, unaccelerated flight using this online calculator? To use this online calculator for Weight of aircraft in level, unaccelerated flight, enter Lift Force (F_L), Thrust (T) & Thrust angle (σ_T) and hit the calculate button. Here is how the Weight of aircraft in level, unaccelerated flight calculation can be explained with given input values -> 244.1586 = 220+(100*sin(0.01)).

FAQ

What is Weight of aircraft in level, unaccelerated flight?

The Weight of aircraft in level, unaccelerated flight is the sum of lift and sine component of thrust acting on aircraft and is represented as W_body = F_L+(T*sin(σ_T)) or Weight of Body = Lift Force+(Thrust*sin(Thrust angle)). 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, The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air & Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction.

How to calculate Weight of aircraft in level, unaccelerated flight?

The Weight of aircraft in level, unaccelerated flight is the sum of lift and sine component of thrust acting on aircraft is calculated using Weight of Body = Lift Force+(Thrust*sin(Thrust angle)). To calculate Weight of aircraft in level, unaccelerated flight, you need Lift Force (F_L), Thrust (T) & Thrust angle (σ_T). With our tool, you need to enter the respective value for Lift Force, Thrust & Thrust angle 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 Weight of Body?

In this formula, Weight of Body uses Lift Force, Thrust & Thrust angle. We can use 4 other way(s) to calculate the same, which is/are as follows -

Weight of Body = Dynamic Pressure*Area*Lift Coefficient
Weight of Body = Lift Coefficient*Thrust/Drag Coefficient
Weight of Body = Thrust*Lift-to-drag Ratio
Weight of Body = Power*Lift Coefficient/(Freestream Velocity*Drag Coefficient)

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