Drag for Level and Unaccelerated Flight Calculator

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Lift and Drag Requirements

Thrust and Power Requirements

✖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%

✖Drag Force is the resisting force experienced by an object moving through a fluid.ⓘ Drag for Level and Unaccelerated Flight [F_D]

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Formula

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Drag for Level and Unaccelerated Flight

Formula

`"F"_{"D"} = "T"*(cos("σ"_{"T"}))`

Example

`"99.995N"="100N"*(cos("0.01rad"))`

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Drag for Level and Unaccelerated Flight Solution

STEP 0: Pre-Calculation Summary

Formula Used

Drag Force = Thrust*(cos(Thrust angle))
F_D = T*(cos(σ_T))
This formula uses 1 Functions, 3 Variables

Functions Used

cos - Cosine of an angle is the ratio of the side adjacent to the angle to the hypotenuse of the triangle., cos(Angle)

Variables Used

Drag Force - (Measured in Newton) - Drag Force is the resisting force experienced by an object moving through a fluid.
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

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

F_D = T*(cos(σ_T)) --> 100*(cos(0.01))

Evaluating ... ...

F_D = 99.9950000416665

STEP 3: Convert Result to Output's Unit

99.9950000416665 Newton --> No Conversion Required

FINAL ANSWER

99.9950000416665 ≈ 99.995 Newton <-- Drag Force

(Calculation completed in 00.004 seconds)

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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

Sai Venkata Phanindra Chary Arendra has verified this Calculator and 300+ more calculators!

< 19 Lift and Drag Requirements Calculators

Lift coefficient for given minimum required thrust

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

Zero-lift drag coefficient for given lift coefficient

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

Zero-lift drag coefficient at minimum required thrust

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

Lift-induced drag coefficient for given required thrust

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

Zero-lift drag coefficient for given required thrust

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

Lift for Unaccelerated Flight

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

Coefficient of Drag for given thrust and weight

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

Coefficient of Lift for given thrust and weight

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

Drag for Level and Unaccelerated Flight at Negligible Thrust Angle

Go Drag Force = Dynamic Pressure*Area*Drag Coefficient

Lift for Level and Unaccelerated Flight at Negligible Thrust Angle

Go Lift Force = Dynamic Pressure*Area*Lift Coefficient

Drag for Level and Unaccelerated Flight

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

Coefficient of Drag for given thrust-to-weight ratio

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

Coefficient of Lift for given thrust-to-weight ratio

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

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

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

Freestream Velocity for given total drag force

Go Freestream Velocity = Power/Drag Force

Total drag force for given required power

Go Drag Force = Power/Freestream Velocity

Freestream velocity for given required power

Go Freestream Velocity = Power/Thrust

Coefficient of Drag due to lift for minimum power required

Go Coefficient Of Drag Due to Lift = 3*Zero Lift Drag Coefficient

Zero-lift drag coefficient for minimum power required

Go Zero Lift Drag Coefficient = Coefficient Of Drag Due to Lift/3

Drag for Level and Unaccelerated Flight Formula

Drag Force = Thrust*(cos(Thrust angle))
F_D = T*(cos(σ_T))

How does drag affect airplane flight?

Drag is defined as the force that delays or slows the forward movement of an airplane through the air.

How to Calculate Drag for Level and Unaccelerated Flight?

Drag for Level and Unaccelerated Flight calculator uses Drag Force = Thrust*(cos(Thrust angle)) to calculate the Drag Force, The Drag for Level and Unaccelerated Flight is the drag force acting on an aeroplane for zero acceleration and zero flight path angle. Drag Force is denoted by F_D symbol.

How to calculate Drag for Level and Unaccelerated Flight using this online calculator? To use this online calculator for Drag for Level and Unaccelerated Flight, enter Thrust (T) & Thrust angle (σ_T) and hit the calculate button. Here is how the Drag for Level and Unaccelerated Flight calculation can be explained with given input values -> 99.995 = 100*(cos(0.01)).

FAQ

What is Drag for Level and Unaccelerated Flight?

The Drag for Level and Unaccelerated Flight is the drag force acting on an aeroplane for zero acceleration and zero flight path angle and is represented as F_D = T*(cos(σ_T)) or Drag Force = Thrust*(cos(Thrust angle)). 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 Drag for Level and Unaccelerated Flight?

The Drag for Level and Unaccelerated Flight is the drag force acting on an aeroplane for zero acceleration and zero flight path angle is calculated using Drag Force = Thrust*(cos(Thrust angle)). To calculate Drag for Level and Unaccelerated Flight, you need Thrust (T) & Thrust angle (σ_T). With our tool, you need to enter the respective value for 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 Drag Force?

In this formula, Drag Force uses Thrust & Thrust angle. We can use 2 other way(s) to calculate the same, which is/are as follows -

Drag Force = Dynamic Pressure*Area*Drag Coefficient
Drag Force = Power/Freestream Velocity

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