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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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 00.004 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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< Lift and Drag Requirements Calculators

Lift for Unaccelerated Flight

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

Drag for Level and Unaccelerated Flight at Negligible Thrust Angle

LaTeX Go Drag Force = Dynamic Pressure*Area*Drag Coefficient

Lift for Level and Unaccelerated Flight at Negligible Thrust Angle

LaTeX Go Lift Force = Dynamic Pressure*Area*Lift Coefficient

Drag for Level and Unaccelerated Flight

LaTeX Go Drag Force = Thrust*cos(Thrust Angle)

Lift for Level and Unaccelerated Flight at Negligible Thrust Angle Formula

LaTeX Go

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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