Lift for Level and Unaccelerated Flight at Negligible Thrust Angle Calculator

✖Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion.ⓘ Dynamic Pressure [P_dynamic]			+10% -10%
✖The Area is the amount of two-dimensional space taken up by an object.ⓘ Area [A]			+10% -10%
✖The Lift Coefficient 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.ⓘ Lift Coefficient [C_L]			+10% -10%

✖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 for Level and Unaccelerated Flight at Negligible Thrust Angle [F_L]

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Formula

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Lift for Level and Unaccelerated Flight at Negligible Thrust Angle

Formula

`"F"_{"L"} = "P"_{"dynamic"}*"A"*"C"_{"L"}`

Example

`"220N"="10Pa"*"20m²"*"1.1"`

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Lift for Level and Unaccelerated Flight at Negligible Thrust Angle Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift Force = Dynamic Pressure*Area*Lift Coefficient
F_L = P_dynamic*A*C_L
This formula uses 4 Variables

Variables Used

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.
Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion.
Area - (Measured in Square Meter) - The Area is the amount of two-dimensional space taken up by an object.
Lift Coefficient - The Lift Coefficient 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.

STEP 1: Convert Input(s) to Base Unit

Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Area: 20 Square Meter --> 20 Square Meter No Conversion Required
Lift Coefficient: 1.1 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

F_L = P_dynamic*A*C_L --> 10*20*1.1

Evaluating ... ...

F_L = 220

STEP 3: Convert Result to Output's Unit

220 Newton --> No Conversion Required

FINAL ANSWER

220 Newton <-- Lift Force

(Calculation completed in 00.020 seconds)

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Created by Vinay Mishra

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

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

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< 19 Lift and Drag Requirements Calculators

Lift Coefficient 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 at Minimum Thrust = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)

Lift-Induced Drag Coefficient given required Thrust

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

Zero-Lift Drag Coefficient 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 given required Thrust of Aircraft

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

Freestream Velocity given Total Drag Force

Go Freestream Velocity = Power/Drag Force

Total Drag Force given required Power

Go Drag Force = Power/Freestream Velocity

Freestream Velocity 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

Lift for Level and Unaccelerated Flight at Negligible Thrust Angle Formula

Lift Force = Dynamic Pressure*Area*Lift Coefficient
F_L = P_dynamic*A*C_L

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 Level and Unaccelerated Flight at Negligible Thrust Angle?

Lift for Level and Unaccelerated Flight at Negligible Thrust Angle calculator uses Lift Force = Dynamic Pressure*Area*Lift Coefficient to calculate the Lift Force, The Lift for Level and Unaccelerated Flight at Negligible Thrust Angle refers to the amount of aerodynamic lift generated by an aircraft's wings when the aircraft is flying straight and level with minimal or no thrust being produced by the engines and negligible changes in altitude or speed, in this state, the lift generated by the wings balances the weight of the aircraft, allowing it to maintain a constant altitude and speed without any acceleration. Lift Force is denoted by F_L symbol.

How to calculate Lift for Level and Unaccelerated Flight at Negligible Thrust Angle using this online calculator? To use this online calculator for Lift for Level and Unaccelerated Flight at Negligible Thrust Angle, enter Dynamic Pressure (P_dynamic), Area (A) & Lift Coefficient (C_L) and hit the calculate button. Here is how the Lift for Level and Unaccelerated Flight at Negligible Thrust Angle calculation can be explained with given input values -> 88 = 10*20*1.1.

FAQ

What is Lift for Level and Unaccelerated Flight at Negligible Thrust Angle?

The Lift for Level and Unaccelerated Flight at Negligible Thrust Angle refers to the amount of aerodynamic lift generated by an aircraft's wings when the aircraft is flying straight and level with minimal or no thrust being produced by the engines and negligible changes in altitude or speed, in this state, the lift generated by the wings balances the weight of the aircraft, allowing it to maintain a constant altitude and speed without any acceleration and is represented as F_L = P_dynamic*A*C_L or Lift Force = Dynamic Pressure*Area*Lift Coefficient. Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion, The Area is the amount of two-dimensional space taken up by an object & The Lift Coefficient 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 Level and Unaccelerated Flight at Negligible Thrust Angle?

The Lift for Level and Unaccelerated Flight at Negligible Thrust Angle refers to the amount of aerodynamic lift generated by an aircraft's wings when the aircraft is flying straight and level with minimal or no thrust being produced by the engines and negligible changes in altitude or speed, in this state, the lift generated by the wings balances the weight of the aircraft, allowing it to maintain a constant altitude and speed without any acceleration is calculated using Lift Force = Dynamic Pressure*Area*Lift Coefficient. To calculate Lift for Level and Unaccelerated Flight at Negligible Thrust Angle, you need Dynamic Pressure (P_dynamic), Area (A) & Lift Coefficient (C_L). With our tool, you need to enter the respective value for Dynamic Pressure, Area & 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 & Lift Coefficient. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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