Freestream Density over Flat Plate using Stanton Number Calculator

✖The Local Heat Transfer Rate is the measure of heat energy transfer per unit area in hypersonic vehicles, crucial for understanding thermal management and material performance.ⓘ Local Heat Transfer Rate [q_w]			+10% -10%
✖The Stanton Number is a dimensionless quantity that characterizes the heat transfer between a fluid and a surface, particularly in the context of hypersonic vehicles.ⓘ Stanton Number [St]			+10% -10%
✖The Freestream Velocity is the speed of fluid flow far away from any influence of objects, crucial for analyzing hypersonic vehicle performance and aerodynamic characteristics.ⓘ Freestream Velocity [V_∞]			+10% -10%
✖The Adiabatic Wall Enthalpy is the heat content of a system under adiabatic conditions, relevant for understanding thermal dynamics in hypersonic vehicles.ⓘ Adiabatic Wall Enthalpy [h_aw]			+10% -10%
✖The Wall Enthalpy is the measure of energy transfer at the surface of hypersonic vehicles, reflecting the thermal conditions experienced during high-speed flight.ⓘ Wall Enthalpy [h_w]			+10% -10%

✖The Freestream Density is the mass per unit volume of air in the flow field surrounding a hypersonic vehicle, crucial for understanding aerodynamic performance.ⓘ Freestream Density over Flat Plate using Stanton Number [ρ_∞]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Hypersonic Flow Formula PDF PDF Image

Freestream Density over Flat Plate using Stanton Number Solution

STEP 0: Pre-Calculation Summary

Formula Used

Freestream Density = Local Heat Transfer Rate/(Stanton Number*Freestream Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))
ρ_∞ = q_w/(St*V_∞*(h_aw-h_w))
This formula uses 6 Variables

Variables Used

Freestream Density - (Measured in Kilogram per Cubic Meter) - The Freestream Density is the mass per unit volume of air in the flow field surrounding a hypersonic vehicle, crucial for understanding aerodynamic performance.
Local Heat Transfer Rate - (Measured in Watt per Square Meter) - The Local Heat Transfer Rate is the measure of heat energy transfer per unit area in hypersonic vehicles, crucial for understanding thermal management and material performance.
Stanton Number - The Stanton Number is a dimensionless quantity that characterizes the heat transfer between a fluid and a surface, particularly in the context of hypersonic vehicles.
Freestream Velocity - (Measured in Meter per Second) - The Freestream Velocity is the speed of fluid flow far away from any influence of objects, crucial for analyzing hypersonic vehicle performance and aerodynamic characteristics.
Adiabatic Wall Enthalpy - (Measured in Joule per Kilogram) - The Adiabatic Wall Enthalpy is the heat content of a system under adiabatic conditions, relevant for understanding thermal dynamics in hypersonic vehicles.
Wall Enthalpy - (Measured in Joule per Kilogram) - The Wall Enthalpy is the measure of energy transfer at the surface of hypersonic vehicles, reflecting the thermal conditions experienced during high-speed flight.

STEP 1: Convert Input(s) to Base Unit

Local Heat Transfer Rate: 12000 Watt per Square Meter --> 12000 Watt per Square Meter No Conversion Required
Stanton Number: 2 --> No Conversion Required
Freestream Velocity: 100 Meter per Second --> 100 Meter per Second No Conversion Required
Adiabatic Wall Enthalpy: 127.7714 Joule per Kilogram --> 127.7714 Joule per Kilogram No Conversion Required
Wall Enthalpy: 99.2 Joule per Kilogram --> 99.2 Joule per Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

ρ_∞ = q_w/(St*V_∞*(h_aw-h_w)) --> 12000/(2*100*(127.7714-99.2))

Evaluating ... ...

ρ_∞ = 2.1000021000021

STEP 3: Convert Result to Output's Unit

2.1000021000021 Kilogram per Cubic Meter --> No Conversion Required

FINAL ANSWER

2.1000021000021 ≈ 2.100002 Kilogram per Cubic Meter <-- Freestream Density

(Calculation completed in 00.004 seconds)

You are here -

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

Credits

Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has created this Calculator and 300+ more calculators!

Verified by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has verified this Calculator and 100+ more calculators!

< Approximate Results Applied to Hypersonic Vehicles Calculators

Freestream Velocity over Flat Plate using Stanton Number

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

Freestream Density over Flat Plate using Stanton Number

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

Freestream Stanton Number for Flat Plate

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

Local Heat Transfer over Flat Plate using Stanton Number

LaTeX Go Local Heat Transfer Rate = Stanton Number*Freestream Density*Freestream Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)

Freestream Density over Flat Plate using Stanton Number Formula

LaTeX Go

Freestream Density = Local Heat Transfer Rate/(Stanton Number*Freestream Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))
ρ_∞ = q_w/(St*V_∞*(h_aw-h_w))

What is Stanton Number?

The Stanton number, St, is a dimensionless number that measures the ratio of heat transferred into a fluid to the thermal capacity of fluid. It is used to characterize heat transfer in forced convection flows.

How to Calculate Freestream Density over Flat Plate using Stanton Number?

Freestream Density over Flat Plate using Stanton Number calculator uses Freestream Density = Local Heat Transfer Rate/(Stanton Number*Freestream Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)) to calculate the Freestream Density, Freestream Density over Flat Plate using Stanton Number formula is defined as a measure of the air density in the freestream flow over a flat plate, which is essential in understanding the heat transfer and frictional characteristics of the plate in viscous flow conditions. Freestream Density is denoted by ρ_∞ symbol.

How to calculate Freestream Density over Flat Plate using Stanton Number using this online calculator? To use this online calculator for Freestream Density over Flat Plate using Stanton Number, enter Local Heat Transfer Rate (q_w), Stanton Number (St), Freestream Velocity (V_∞), Adiabatic Wall Enthalpy (h_aw) & Wall Enthalpy (h_w) and hit the calculate button. Here is how the Freestream Density over Flat Plate using Stanton Number calculation can be explained with given input values -> 21.42857 = 12000/(2*100*(127.7714-99.2)).

FAQ

What is Freestream Density over Flat Plate using Stanton Number?

Freestream Density over Flat Plate using Stanton Number formula is defined as a measure of the air density in the freestream flow over a flat plate, which is essential in understanding the heat transfer and frictional characteristics of the plate in viscous flow conditions and is represented as ρ_∞ = q_w/(St*V_∞*(h_aw-h_w)) or Freestream Density = Local Heat Transfer Rate/(Stanton Number*Freestream Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)). The Local Heat Transfer Rate is the measure of heat energy transfer per unit area in hypersonic vehicles, crucial for understanding thermal management and material performance, The Stanton Number is a dimensionless quantity that characterizes the heat transfer between a fluid and a surface, particularly in the context of hypersonic vehicles, The Freestream Velocity is the speed of fluid flow far away from any influence of objects, crucial for analyzing hypersonic vehicle performance and aerodynamic characteristics, The Adiabatic Wall Enthalpy is the heat content of a system under adiabatic conditions, relevant for understanding thermal dynamics in hypersonic vehicles & The Wall Enthalpy is the measure of energy transfer at the surface of hypersonic vehicles, reflecting the thermal conditions experienced during high-speed flight.

How to calculate Freestream Density over Flat Plate using Stanton Number?

Freestream Density over Flat Plate using Stanton Number formula is defined as a measure of the air density in the freestream flow over a flat plate, which is essential in understanding the heat transfer and frictional characteristics of the plate in viscous flow conditions is calculated using Freestream Density = Local Heat Transfer Rate/(Stanton Number*Freestream Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)). To calculate Freestream Density over Flat Plate using Stanton Number, you need Local Heat Transfer Rate (q_w), Stanton Number (St), Freestream Velocity (V_∞), Adiabatic Wall Enthalpy (h_aw) & Wall Enthalpy (h_w). With our tool, you need to enter the respective value for Local Heat Transfer Rate, Stanton Number, Freestream Velocity, Adiabatic Wall Enthalpy & Wall Enthalpy 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 Local Heat Transfer Rate, Stanton Number, Freestream Velocity, Adiabatic Wall Enthalpy & Wall Enthalpy. We can use 1 other way(s) to calculate the same, which is/are as follows -

Freestream Density = Drag Force/(0.5*Drag Coefficient*Freestream Velocity^2*Reference Area)

Home

FREE PDFs

🔍 Search