Wall Enthalpy over Flat Plate using Stanton Number Calculator

✖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 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 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 [ρ_∞]			+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 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 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 over Flat Plate using Stanton Number [h_w]

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Wall Enthalpy over Flat Plate using Stanton Number Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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.
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.
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.
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.
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.

STEP 1: Convert Input(s) to Base Unit

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

STEP 2: Evaluate Formula

Substituting Input Values in Formula

h_w = h_aw-q_w/(ρ_∞*V_∞*St) --> 127.7714-12000/(2.1*100*2)

Evaluating ... ...

h_w = 99.1999714285714

STEP 3: Convert Result to Output's Unit

99.1999714285714 Joule per Kilogram --> No Conversion Required

FINAL ANSWER

99.1999714285714 ≈ 99.19997 Joule per Kilogram <-- Wall Enthalpy

(Calculation completed in 00.006 seconds)

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

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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

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< 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)

Wall Enthalpy over Flat Plate using Stanton Number Formula

LaTeX Go

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

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 Wall Enthalpy over Flat Plate using Stanton Number?

Wall Enthalpy over Flat Plate using Stanton Number calculator uses Wall Enthalpy = Adiabatic Wall Enthalpy-Local Heat Transfer Rate/(Freestream Density*Freestream Velocity*Stanton Number) to calculate the Wall Enthalpy, Wall Enthalpy over Flat Plate using Stanton Number formula is defined as a measure of the total heat transfer coefficient that takes into account the heat transfer due to convection and radiation over a flat plate in a viscous flow case, providing a comprehensive understanding of the heat transfer phenomenon. Wall Enthalpy is denoted by h_w symbol.

How to calculate Wall Enthalpy over Flat Plate using Stanton Number using this online calculator? To use this online calculator for Wall Enthalpy over Flat Plate using Stanton Number, enter Adiabatic Wall Enthalpy (h_aw), Local Heat Transfer Rate (q_w), Freestream Density (ρ_∞), Freestream Velocity (V_∞) & Stanton Number (St) and hit the calculate button. Here is how the Wall Enthalpy over Flat Plate using Stanton Number calculation can be explained with given input values -> 73.42857 = 127.7714-12000/(2.1*100*2).

FAQ

What is Wall Enthalpy over Flat Plate using Stanton Number?

Wall Enthalpy over Flat Plate using Stanton Number formula is defined as a measure of the total heat transfer coefficient that takes into account the heat transfer due to convection and radiation over a flat plate in a viscous flow case, providing a comprehensive understanding of the heat transfer phenomenon and is represented as h_w = h_aw-q_w/(ρ_∞*V_∞*St) or Wall Enthalpy = Adiabatic Wall Enthalpy-Local Heat Transfer Rate/(Freestream Density*Freestream Velocity*Stanton Number). The Adiabatic Wall Enthalpy is the heat content of a system under adiabatic conditions, relevant for understanding thermal dynamics in hypersonic vehicles, 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 Freestream Density is the mass per unit volume of air in the flow field surrounding a hypersonic vehicle, crucial for understanding aerodynamic performance, 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 Stanton Number is a dimensionless quantity that characterizes the heat transfer between a fluid and a surface, particularly in the context of hypersonic vehicles.

How to calculate Wall Enthalpy over Flat Plate using Stanton Number?

Wall Enthalpy over Flat Plate using Stanton Number formula is defined as a measure of the total heat transfer coefficient that takes into account the heat transfer due to convection and radiation over a flat plate in a viscous flow case, providing a comprehensive understanding of the heat transfer phenomenon is calculated using Wall Enthalpy = Adiabatic Wall Enthalpy-Local Heat Transfer Rate/(Freestream Density*Freestream Velocity*Stanton Number). To calculate Wall Enthalpy over Flat Plate using Stanton Number, you need Adiabatic Wall Enthalpy (h_aw), Local Heat Transfer Rate (q_w), Freestream Density (ρ_∞), Freestream Velocity (V_∞) & Stanton Number (St). With our tool, you need to enter the respective value for Adiabatic Wall Enthalpy, Local Heat Transfer Rate, Freestream Density, Freestream Velocity & Stanton Number 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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