Zero-Lift Drag Coefficient given required Thrust Calculator

✖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%
✖Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion.ⓘ Dynamic Pressure [P_dynamic]			+10% -10%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's platform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+10% -10%
✖The Coefficient of Drag Due to Lift represents the contribution of lift-induced drag to the total drag experienced by an aircraft.ⓘ Coefficient Of Drag Due to Lift [C_D,i]			+10% -10%

✖Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.ⓘ Zero-Lift Drag Coefficient given required Thrust [C_D,0]

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Zero-Lift Drag Coefficient given required Thrust Solution

STEP 0: Pre-Calculation Summary

Formula Used

Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Reference Area))-Coefficient Of Drag Due to Lift
C_D,0 = (T/(P_dynamic*S))-C_D,i
This formula uses 5 Variables

Variables Used

Zero Lift Drag Coefficient - Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.
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.
Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's platform area is called the reference wing area or simply wing area.
Coefficient Of Drag Due to Lift - The Coefficient of Drag Due to Lift represents the contribution of lift-induced drag to the total drag experienced by an aircraft.

STEP 1: Convert Input(s) to Base Unit

Thrust: 100 Newton --> 100 Newton No Conversion Required
Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Reference Area: 8 Square Meter --> 8 Square Meter No Conversion Required
Coefficient Of Drag Due to Lift: 0.93 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D,0 = (T/(P_dynamic*S))-C_D,i --> (100/(10*8))-0.93

Evaluating ... ...

C_D,0 = 0.32

STEP 3: Convert Result to Output's Unit

0.32 --> No Conversion Required

FINAL ANSWER

0.32 <-- Zero Lift Drag Coefficient

(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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< 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)

Zero-Lift Drag Coefficient given required Thrust Formula

LaTeX Go

Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Reference Area))-Coefficient Of Drag Due to Lift
C_D,0 = (T/(P_dynamic*S))-C_D,i

What is a zero-lift drag?

The drag acting on a body for zero lift force when it is immersed in a fluid is called the zero-lift drag.

How to Calculate Zero-Lift Drag Coefficient given required Thrust?

Zero-Lift Drag Coefficient given required Thrust calculator uses Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Reference Area))-Coefficient Of Drag Due to Lift to calculate the Zero Lift Drag Coefficient, The Zero-Lift Drag Coefficient given required Thrust is a measure of the drag experienced by an aircraft when it's not producing any lift, often during cruising or gliding, it's an essential parameter in aerodynamics, describing the inherent drag characteristics of an aircraft, including factors such as its shape, surface texture, and overall design. Zero Lift Drag Coefficient is denoted by C_D,0 symbol.

How to calculate Zero-Lift Drag Coefficient given required Thrust using this online calculator? To use this online calculator for Zero-Lift Drag Coefficient given required Thrust, enter Thrust (T), Dynamic Pressure (P_dynamic), Reference Area (S) & Coefficient Of Drag Due to Lift (C_D,i) and hit the calculate button. Here is how the Zero-Lift Drag Coefficient given required Thrust calculation can be explained with given input values -> 0.686 = (100/(10*8))-0.93.

FAQ

What is Zero-Lift Drag Coefficient given required Thrust?

The Zero-Lift Drag Coefficient given required Thrust is a measure of the drag experienced by an aircraft when it's not producing any lift, often during cruising or gliding, it's an essential parameter in aerodynamics, describing the inherent drag characteristics of an aircraft, including factors such as its shape, surface texture, and overall design and is represented as C_D,0 = (T/(P_dynamic*S))-C_D,i or Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Reference Area))-Coefficient Of Drag Due to Lift. The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air, Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's platform area is called the reference wing area or simply wing area & The Coefficient of Drag Due to Lift represents the contribution of lift-induced drag to the total drag experienced by an aircraft.

How to calculate Zero-Lift Drag Coefficient given required Thrust?

The Zero-Lift Drag Coefficient given required Thrust is a measure of the drag experienced by an aircraft when it's not producing any lift, often during cruising or gliding, it's an essential parameter in aerodynamics, describing the inherent drag characteristics of an aircraft, including factors such as its shape, surface texture, and overall design is calculated using Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Reference Area))-Coefficient Of Drag Due to Lift. To calculate Zero-Lift Drag Coefficient given required Thrust, you need Thrust (T), Dynamic Pressure (P_dynamic), Reference Area (S) & Coefficient Of Drag Due to Lift (C_D,i). With our tool, you need to enter the respective value for Thrust, Dynamic Pressure, Reference Area & Coefficient Of Drag Due to Lift 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 Zero Lift Drag Coefficient?

In this formula, Zero Lift Drag Coefficient uses Thrust, Dynamic Pressure, Reference Area & Coefficient Of Drag Due to Lift. We can use 2 other way(s) to calculate the same, which is/are as follows -

Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing))
Zero Lift Drag Coefficient = Coefficient Of Drag Due to Lift/3

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