Weight of Aircraft for Level, 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%

✖Weight of Body is the force acting on the object due to gravity.ⓘ Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle [W_body]

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Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle Solution

STEP 0: Pre-Calculation Summary

Formula Used

Weight of Body = Dynamic Pressure*Area*Lift Coefficient
W_body = P_dynamic*A*C_L
This formula uses 4 Variables

Variables Used

Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
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

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

Evaluating ... ...

W_body = 220

STEP 3: Convert Result to Output's Unit

220 Newton --> No Conversion Required

FINAL ANSWER

220 Newton <-- Weight of Body

(Calculation completed in 00.004 seconds)

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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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< Thrust and Power Requirements Calculators

Thrust Angle for Unaccelerated Level Flight for given Lift

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

Weight of Aircraft in Level, Unaccelerated Flight

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

Thrust for Level and Unaccelerated Flight

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

Thrust Angle for Unaccelerated Level Flight for given Drag

LaTeX Go Thrust Angle = acos(Drag Force/Thrust)

Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle Formula

LaTeX Go

Weight of Body = Dynamic Pressure*Area*Lift Coefficient
W_body = P_dynamic*A*C_L

What is the most aerodynamic shape?

For speeds lower than the speed of sound, the most aerodynamically efficient shape found is the teardrop.

How to Calculate Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle?

Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle calculator uses Weight of Body = Dynamic Pressure*Area*Lift Coefficient to calculate the Weight of Body, The Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle of the aircraft is balanced by the aerodynamic forces acting on it, at this flight condition, the aircraft is neither climbing nor descending, and its velocity remains constant, negligible thrust angle means that the thrust vector is aligned almost perfectly with the aircraft's longitudinal axis, contributing primarily to forward propulsion rather than vertical lift. Weight of Body is denoted by W_body symbol.

How to calculate Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle using this online calculator? To use this online calculator for Weight of Aircraft for Level, 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 Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle calculation can be explained with given input values -> 88 = 10*20*1.1.

FAQ

What is Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle?

The Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle of the aircraft is balanced by the aerodynamic forces acting on it, at this flight condition, the aircraft is neither climbing nor descending, and its velocity remains constant, negligible thrust angle means that the thrust vector is aligned almost perfectly with the aircraft's longitudinal axis, contributing primarily to forward propulsion rather than vertical lift and is represented as W_body = P_dynamic*A*C_L or Weight of Body = 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 Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle?

The Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle of the aircraft is balanced by the aerodynamic forces acting on it, at this flight condition, the aircraft is neither climbing nor descending, and its velocity remains constant, negligible thrust angle means that the thrust vector is aligned almost perfectly with the aircraft's longitudinal axis, contributing primarily to forward propulsion rather than vertical lift is calculated using Weight of Body = Dynamic Pressure*Area*Lift Coefficient. To calculate Weight of Aircraft for Level, 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 Weight of Body?

In this formula, Weight of Body uses Dynamic Pressure, Area & Lift Coefficient. We can use 3 other way(s) to calculate the same, which is/are as follows -

Weight of Body = Lift Force+(Thrust*sin(Thrust Angle))
Weight of Body = Lift Coefficient*Thrust/Drag Coefficient
Weight of Body = Thrust*Lift-to-Drag Ratio

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