Drag for Level and Unaccelerated Flight at Negligible Thrust Angle Calculator

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Lift and Drag Requirements

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✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.ⓘ Dynamic Pressure [P_dynamic]			+10% -10%
✖The area is the amount of two-dimensional space taken up by an object.ⓘ Area [A]			+10% -10%
✖Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.ⓘ Drag Coefficient [C_D]			+10% -10%

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

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Formula

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Drag for Level and Unaccelerated Flight at Negligible Thrust Angle

Formula

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

Example

`"100N"="10Pa"*"20m²"*"0.5"`

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Drag for Level and Unaccelerated Flight at Negligible Thrust Angle Solution

STEP 0: Pre-Calculation Summary

Formula Used

Drag Force = Dynamic Pressure*Area*Drag Coefficient
F_D = P_dynamic*A*C_D
This formula uses 4 Variables

Variables Used

Drag Force - (Measured in Newton) - Drag Force is the resisting force experienced by an object moving through a fluid.
Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.
Area - (Measured in Square Meter) - The area is the amount of two-dimensional space taken up by an object.
Drag Coefficient - Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.

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
Drag Coefficient: 0.5 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

F_D = P_dynamic*A*C_D --> 10*20*0.5

Evaluating ... ...

F_D = 100

STEP 3: Convert Result to Output's Unit

100 Newton --> No Conversion Required

FINAL ANSWER

100 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 at Negligible Thrust Angle Formula

Drag Force = Dynamic Pressure*Area*Drag Coefficient
F_D = P_dynamic*A*C_D

Does drag increase with altitude?

The Reynolds-Number decreases with an increasing altitude, which means that drag increases with an increasing altitude.

How to Calculate Drag for Level and Unaccelerated Flight at Negligible Thrust Angle?

Drag for Level and Unaccelerated Flight at Negligible Thrust Angle calculator uses Drag Force = Dynamic Pressure*Area*Drag Coefficient to calculate the Drag Force, The Drag for Level and Unaccelerated Flight at Negligible Thrust Angle is the product of dynamic pressure, reference area, and drag coefficient. Drag Force is denoted by F_D symbol.

How to calculate Drag for Level and Unaccelerated Flight at Negligible Thrust Angle using this online calculator? To use this online calculator for Drag for Level and Unaccelerated Flight at Negligible Thrust Angle, enter Dynamic Pressure (P_dynamic), Area (A) & Drag Coefficient (C_D) and hit the calculate button. Here is how the Drag for Level and Unaccelerated Flight at Negligible Thrust Angle calculation can be explained with given input values -> 40 = 10*20*0.5.

FAQ

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

The Drag for Level and Unaccelerated Flight at Negligible Thrust Angle is the product of dynamic pressure, reference area, and drag coefficient and is represented as F_D = P_dynamic*A*C_D or Drag Force = Dynamic Pressure*Area*Drag Coefficient. Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid, The area is the amount of two-dimensional space taken up by an object & Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.

How to calculate Drag for Level and Unaccelerated Flight at Negligible Thrust Angle?

The Drag for Level and Unaccelerated Flight at Negligible Thrust Angle is the product of dynamic pressure, reference area, and drag coefficient is calculated using Drag Force = Dynamic Pressure*Area*Drag Coefficient. To calculate Drag for Level and Unaccelerated Flight at Negligible Thrust Angle, you need Dynamic Pressure (P_dynamic), Area (A) & Drag Coefficient (C_D). With our tool, you need to enter the respective value for Dynamic Pressure, Area & Drag 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 Drag Force?

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

Drag Force = Thrust*(cos(Thrust angle))
Drag Force = Power/Freestream Velocity

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