Enthalpy of Wall using Stanton Number Calculator

✖The Adiabatic Wall Enthalpy is the total enthalpy of a gas at the wall of a hypersonic vehicle, considering the heat transfer and friction effects.ⓘ Adiabatic Wall Enthalpy [h_aw]			+10% -10%
✖The Local Heat Transfer Rate is the amount of heat transferred per unit area per unit time from the surface to the fluid in a hypersonic boundary layer.ⓘ Local Heat Transfer Rate [q_w]			+10% -10%
✖The Static Density is the density of air at a given altitude and temperature, used to model the boundary layer in hypersonic flow conditions.ⓘ Static Density [ρ_e]			+10% -10%
✖The Static Velocity is the velocity of the fluid in the boundary layer at a given point, describing the flow characteristics near the surface.ⓘ Static Velocity [u_e]			+10% -10%
✖The Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow.ⓘ Stanton Number [St]			+10% -10%

✖The Wall Enthalpy is the total heat content of the wall boundary layer in a hypersonic flow, including both sensible and latent heat components.ⓘ Enthalpy of Wall using Stanton Number [h_w]

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Enthalpy of Wall using Stanton Number Solution

STEP 0: Pre-Calculation Summary

Formula Used

Wall Enthalpy = Adiabatic Wall Enthalpy-Local Heat Transfer Rate/(Static Density*Static Velocity*Stanton Number)
h_w = h_aw-q_w/(ρ_e*u_e*St)
This formula uses 6 Variables

Variables Used

Wall Enthalpy - (Measured in Joule per Kilogram) - The Wall Enthalpy is the total heat content of the wall boundary layer in a hypersonic flow, including both sensible and latent heat components.
Adiabatic Wall Enthalpy - (Measured in Joule per Kilogram) - The Adiabatic Wall Enthalpy is the total enthalpy of a gas at the wall of a hypersonic vehicle, considering the heat transfer and friction effects.
Local Heat Transfer Rate - (Measured in Watt per Square Meter) - The Local Heat Transfer Rate is the amount of heat transferred per unit area per unit time from the surface to the fluid in a hypersonic boundary layer.
Static Density - (Measured in Kilogram per Cubic Meter) - The Static Density is the density of air at a given altitude and temperature, used to model the boundary layer in hypersonic flow conditions.
Static Velocity - (Measured in Meter per Second) - The Static Velocity is the velocity of the fluid in the boundary layer at a given point, describing the flow characteristics near the surface.
Stanton Number - The Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow.

STEP 1: Convert Input(s) to Base Unit

Adiabatic Wall Enthalpy: 102 Joule per Kilogram --> 102 Joule per Kilogram No Conversion Required
Local Heat Transfer Rate: 12000 Watt per Square Meter --> 12000 Watt per Square Meter No Conversion Required
Static Density: 1200 Kilogram per Cubic Meter --> 1200 Kilogram per Cubic Meter No Conversion Required
Static Velocity: 8.8 Meter per Second --> 8.8 Meter per Second No Conversion Required
Stanton Number: 0.4 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

h_w = h_aw-q_w/(ρ_e*u_e*St) --> 102-12000/(1200*8.8*0.4)

Evaluating ... ...

h_w = 99.1590909090909

STEP 3: Convert Result to Output's Unit

99.1590909090909 Joule per Kilogram --> No Conversion Required

FINAL ANSWER

99.1590909090909 ≈ 99.15909 Joule per Kilogram <-- Wall Enthalpy

(Calculation completed in 00.007 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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Indian Institute of Technology (IIT), Bombay

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< Local Heat Transfer for Hypersonic Flow Calculators

Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number

LaTeX Go Thermal Conductivity = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Nusselt Number*(Adiabatic Wall Temperature-Wall Temperature))

Local Heat Transfer Rate using Nusselt's Number

LaTeX Go Local Heat Transfer Rate = (Nusselt Number*Thermal Conductivity*(Adiabatic Wall Temperature-Wall Temperature))/(Distance from Nose Tip to Required Base Diameter)

Nusselt Number for Hypersonic Vehicle

LaTeX Go Nusselt Number = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Thermal Conductivity*(Adiabatic Wall Temperature-Wall Temperature))

Stanton Number for Hypersonic Vehicle

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

Enthalpy of Wall using Stanton Number Formula

LaTeX Go

Wall Enthalpy = Adiabatic Wall Enthalpy-Local Heat Transfer Rate/(Static Density*Static Velocity*Stanton Number)
h_w = h_aw-q_w/(ρ_e*u_e*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

How to Calculate Enthalpy of Wall using Stanton Number?

Enthalpy of Wall using Stanton Number calculator uses Wall Enthalpy = Adiabatic Wall Enthalpy-Local Heat Transfer Rate/(Static Density*Static Velocity*Stanton Number) to calculate the Wall Enthalpy, Enthalpy of Wall using Stanton Number formula is defined as a measure of the total energy of the wall in a hypersonic flow boundary layer, which is a critical parameter in understanding heat transfer and fluid dynamics in high-speed flows. Wall Enthalpy is denoted by h_w symbol.

How to calculate Enthalpy of Wall using Stanton Number using this online calculator? To use this online calculator for Enthalpy of Wall using Stanton Number, enter Adiabatic Wall Enthalpy (h_aw), Local Heat Transfer Rate (q_w), Static Density (ρ_e), Static Velocity (u_e) & Stanton Number (St) and hit the calculate button. Here is how the Enthalpy of Wall using Stanton Number calculation can be explained with given input values -> 99.15909 = 102-12000/(1200*8.8*0.4).

FAQ

What is Enthalpy of Wall using Stanton Number?

Enthalpy of Wall using Stanton Number formula is defined as a measure of the total energy of the wall in a hypersonic flow boundary layer, which is a critical parameter in understanding heat transfer and fluid dynamics in high-speed flows and is represented as h_w = h_aw-q_w/(ρ_e*u_e*St) or Wall Enthalpy = Adiabatic Wall Enthalpy-Local Heat Transfer Rate/(Static Density*Static Velocity*Stanton Number). The Adiabatic Wall Enthalpy is the total enthalpy of a gas at the wall of a hypersonic vehicle, considering the heat transfer and friction effects, The Local Heat Transfer Rate is the amount of heat transferred per unit area per unit time from the surface to the fluid in a hypersonic boundary layer, The Static Density is the density of air at a given altitude and temperature, used to model the boundary layer in hypersonic flow conditions, The Static Velocity is the velocity of the fluid in the boundary layer at a given point, describing the flow characteristics near the surface & The Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow.

How to calculate Enthalpy of Wall using Stanton Number?

Enthalpy of Wall using Stanton Number formula is defined as a measure of the total energy of the wall in a hypersonic flow boundary layer, which is a critical parameter in understanding heat transfer and fluid dynamics in high-speed flows is calculated using Wall Enthalpy = Adiabatic Wall Enthalpy-Local Heat Transfer Rate/(Static Density*Static Velocity*Stanton Number). To calculate Enthalpy of Wall using Stanton Number, you need Adiabatic Wall Enthalpy (h_aw), Local Heat Transfer Rate (q_w), Static Density (ρ_e), Static Velocity (u_e) & Stanton Number (St). With our tool, you need to enter the respective value for Adiabatic Wall Enthalpy, Local Heat Transfer Rate, Static Density, Static 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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