Coefficient of Drag over Flat under Freestream Flow Conditions Solution

STEP 0: Pre-Calculation Summary
Formula Used
Drag Coefficient = Drag Force/(0.5*Freestream density*Freestream Velocity^2*Reference Area)
CD = FD/(0.5*ρ*V^2*S)
This formula uses 5 Variables
Variables Used
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.
Drag Force - (Measured in Newton) - Drag Force is the resisting force experienced by an object moving through a fluid.
Freestream density - (Measured in Kilogram per Cubic Meter) - Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.
Freestream Velocity - (Measured in Meter per Second) - The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.
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 planform area is called the reference wing area or simply wing area.
STEP 1: Convert Input(s) to Base Unit
Drag Force: 82 Newton --> 82 Newton No Conversion Required
Freestream density: 2.1 Kilogram per Cubic Meter --> 2.1 Kilogram per Cubic Meter No Conversion Required
Freestream Velocity: 100 Meter per Second --> 100 Meter per Second No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
CD = FD/(0.5*ρ*V^2*S) --> 82/(0.5*2.1*100^2*5.08)
Evaluating ... ...
CD = 0.00153730783652043
STEP 3: Convert Result to Output's Unit
0.00153730783652043 --> No Conversion Required
FINAL ANSWER
0.00153730783652043 0.001537 <-- Drag Coefficient
(Calculation completed in 00.004 seconds)

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Amrita School of Engineering (ASE), Vallikavu
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15 Approximate Results Applied to Hypersonic Vehicles Calculators

Freestream Velocity over Flat Plate using Stanton Number
Go Freestream Velocity = Local Heat Transfer Rate/(Stanton Number*Freestream density*(Adiabatic Wall Enthalpy-Wall Enthalpy))
Freestream Density over Flat Plate using Stanton Number
Go Freestream density = Local Heat Transfer Rate/(Stanton Number*Freestream Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))
Freestream Stanton Number for Flat Plate
Go Stanton Number = Local Heat Transfer Rate/(Freestream density*Freestream Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))
Adiabatic Wall Enthalpy over Flat Plate using Stanton Number
Go Adiabatic Wall Enthalpy = Local Heat Transfer Rate/(Freestream density*Freestream Velocity*Stanton Number)+Wall Enthalpy
Local Heat Transfer over Flat Plate using Stanton Number
Go Local Heat Transfer Rate = Stanton Number*Freestream density*Freestream Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)
Wall Enthalpy over Flat Plate using Stanton Number
Go Wall Enthalpy = Adiabatic Wall Enthalpy-Local Heat Transfer Rate/(Freestream density*Freestream Velocity*Stanton Number)
Free Stream Velocity over Flat Plate using Drag Force
Go Freestream Velocity = sqrt(Drag Force/(0.5*Freestream density*Reference Area*Drag Coefficient))
Coefficient of Drag over Flat under Freestream Flow Conditions
Go Drag Coefficient = Drag Force/(0.5*Freestream density*Freestream Velocity^2*Reference Area)
Freestream Density over Flat under Freestream Flow Conditions
Go Freestream density = Drag Force/(0.5*Drag Coefficient*Freestream Velocity^2*Reference Area)
Drag Force over Flat Plate
Go Drag Force = 0.5*Freestream density*Freestream Velocity^2*Reference Area*Drag Coefficient
Free Stream Velocity over Flat Plate with Freestream Conditions
Go Freestream Velocity = sqrt(2*(Total Specific Enthalpy-Freestream Specific Enthalpy))
Pressure Ratio for Insulated Flat Plate, Weak Interaction
Go Pressure Ratio = 1 +0.31*Viscous Interaction Similarity Parameter+0.05*Viscous Interaction Similarity Parameter^2
Free Stream Enthalpy over Flat Plate with Freestream Conditions
Go Freestream Specific Enthalpy = Total Specific Enthalpy-(Freestream Velocity^2)/2
Total Enthalpy over Flat Plate with Freestream Conditions
Go Total Specific Enthalpy = Freestream Specific Enthalpy+(Freestream Velocity^2)/2
Pressure Ratio for Insulated Flat Plate, Strong Interaction
Go Pressure Ratio = 0.514*Viscous Interaction Similarity Parameter+0.759

Coefficient of Drag over Flat under Freestream Flow Conditions Formula

Drag Coefficient = Drag Force/(0.5*Freestream density*Freestream Velocity^2*Reference Area)
CD = FD/(0.5*ρ*V^2*S)

What is drag force?

A drag force is the resistance force caused by the motion of a body through a fluid, such as water or air. A drag force acts opposite to the direction of the oncoming flow velocity.

How to Calculate Coefficient of Drag over Flat under Freestream Flow Conditions?

Coefficient of Drag over Flat under Freestream Flow Conditions calculator uses Drag Coefficient = Drag Force/(0.5*Freestream density*Freestream Velocity^2*Reference Area) to calculate the Drag Coefficient, The Coefficient of drag over flat under freestream flow conditions formula is defined as the function of freestream density, freestream velocity, reference area, and drag coefficient. Drag Coefficient is denoted by CD symbol.

How to calculate Coefficient of Drag over Flat under Freestream Flow Conditions using this online calculator? To use this online calculator for Coefficient of Drag over Flat under Freestream Flow Conditions, enter Drag Force (FD), Freestream density ), Freestream Velocity (V) & Reference Area (S) and hit the calculate button. Here is how the Coefficient of Drag over Flat under Freestream Flow Conditions calculation can be explained with given input values -> 0.001537 = 82/(0.5*2.1*100^2*5.08).

FAQ

What is Coefficient of Drag over Flat under Freestream Flow Conditions?
The Coefficient of drag over flat under freestream flow conditions formula is defined as the function of freestream density, freestream velocity, reference area, and drag coefficient and is represented as CD = FD/(0.5*ρ*V^2*S) or Drag Coefficient = Drag Force/(0.5*Freestream density*Freestream Velocity^2*Reference Area). Drag Force is the resisting force experienced by an object moving through a fluid, Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air & The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
How to calculate Coefficient of Drag over Flat under Freestream Flow Conditions?
The Coefficient of drag over flat under freestream flow conditions formula is defined as the function of freestream density, freestream velocity, reference area, and drag coefficient is calculated using Drag Coefficient = Drag Force/(0.5*Freestream density*Freestream Velocity^2*Reference Area). To calculate Coefficient of Drag over Flat under Freestream Flow Conditions, you need Drag Force (FD), Freestream density ), Freestream Velocity (V) & Reference Area (S). With our tool, you need to enter the respective value for Drag Force, Freestream density, Freestream Velocity & Reference Area and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
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