Freestream Density over Flat under Freestream Flow Conditions Calculator

✖Drag Force is the resisting force experienced by an object moving through a fluid.ⓘ Drag Force [F_D]			+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%
✖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.ⓘ Freestream Velocity [V_∞]			+10% -10%
✖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.ⓘ Reference Area [S]			+10% -10%

✖Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.ⓘ Freestream Density over Flat under Freestream Flow Conditions [ρ_∞]

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Freestream Density over Flat under Freestream Flow Conditions

Formula

`"ρ"_{"∞"} = "F"_{"D"}/(0.5*"C"_{"D"}*"V"_{"∞"}^2*"S")`

Example

`"0.001467kg/m³"="82N"/(0.5*"2.2"*("100m/s")^2*"5.08m²")`

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Freestream Density over Flat under Freestream Flow Conditions Solution

STEP 0: Pre-Calculation Summary

Formula Used

Freestream density = Drag Force/(0.5*Drag Coefficient*Freestream Velocity^2*Reference Area)
ρ_∞ = F_D/(0.5*C_D*V_∞^2*S)
This formula uses 5 Variables

Variables Used

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.
Drag Force - (Measured in Newton) - Drag Force is the resisting force experienced by an object moving through a fluid.
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.
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
Drag Coefficient: 2.2 --> 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

ρ_∞ = F_D/(0.5*C_D*V_∞^2*S) --> 82/(0.5*2.2*100^2*5.08)

Evaluating ... ...

ρ_∞ = 0.00146743020758769

STEP 3: Convert Result to Output's Unit

0.00146743020758769 Kilogram per Cubic Meter --> No Conversion Required

FINAL ANSWER

0.00146743020758769 ≈ 0.001467 Kilogram per Cubic Meter <-- Freestream density

(Calculation completed in 00.004 seconds)

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Home » Engineering » Mechanical » Fluid Mechanics » Hypersonic Flow » Flat Plate for Viscous Flow Case » Approximate Results Applied to Hypersonic Vehicles » Freestream Density over Flat under Freestream Flow Conditions

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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

Freestream Density over Flat under Freestream Flow Conditions Formula

Freestream density = Drag Force/(0.5*Drag Coefficient*Freestream Velocity^2*Reference Area)
ρ_∞ = F_D/(0.5*C_D*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 Freestream Density over Flat under Freestream Flow Conditions?

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

How to calculate Freestream Density over Flat under Freestream Flow Conditions using this online calculator? To use this online calculator for Freestream Density over Flat under Freestream Flow Conditions, enter Drag Force (F_D), Drag Coefficient (C_D), Freestream Velocity (V_∞) & Reference Area (S) and hit the calculate button. Here is how the Freestream Density over Flat under Freestream Flow Conditions calculation can be explained with given input values -> 0.001467 = 82/(0.5*2.2*100^2*5.08).

FAQ

What is Freestream Density over Flat under Freestream Flow Conditions?

The Freestream density 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 ρ_∞ = F_D/(0.5*C_D*V_∞^2*S) or Freestream density = Drag Force/(0.5*Drag Coefficient*Freestream Velocity^2*Reference Area). Drag Force is the resisting force experienced by an object moving through a fluid, 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, 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 Freestream Density over Flat under Freestream Flow Conditions?

The Freestream density 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 Freestream density = Drag Force/(0.5*Drag Coefficient*Freestream Velocity^2*Reference Area). To calculate Freestream Density over Flat under Freestream Flow Conditions, you need Drag Force (F_D), Drag Coefficient (C_D), Freestream Velocity (V_∞) & Reference Area (S). With our tool, you need to enter the respective value for Drag Force, Drag Coefficient, 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.

How many ways are there to calculate Freestream density?

In this formula, Freestream density uses Drag Force, Drag Coefficient, Freestream Velocity & Reference Area. We can use 1 other way(s) to calculate the same, which is/are as follows -

Freestream density = Local Heat Transfer Rate/(Stanton Number*Freestream Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))

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