Static Density Equation using Stanton Number Calculator

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

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Static Density Equation using Stanton Number Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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.
Stanton Number - The Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow.
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.
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.
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.

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: 0.4 --> No Conversion Required
Static Velocity: 8.8 Meter per Second --> 8.8 Meter per Second No Conversion Required
Adiabatic Wall Enthalpy: 102 Joule per Kilogram --> 102 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_e = q_w/(St*u_e*(h_aw-h_w)) --> 12000/(0.4*8.8*(102-99.2))

Evaluating ... ...

ρ_e = 1217.53246753247

STEP 3: Convert Result to Output's Unit

1217.53246753247 Kilogram per Cubic Meter --> No Conversion Required

FINAL ANSWER

1217.53246753247 ≈ 1217.532 Kilogram per Cubic Meter <-- Static Density

(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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PSG College of Technology (PSGCT), Coimbatore

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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))

Static Density Equation using Stanton Number Formula

LaTeX Go

Static Density = Local Heat Transfer Rate/(Stanton Number*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))
ρ_e = q_w/(St*u_e*(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 the fluid.

How to Calculate Static Density Equation using Stanton Number?

Static Density Equation using Stanton Number calculator uses Static Density = Local Heat Transfer Rate/(Stanton Number*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)) to calculate the Static Density, Static Density Equation using Stanton Number formula is defined as a measure of the effective density of a fluid in a hypersonic boundary layer, which is essential in understanding the flow behavior and heat transfer characteristics in high-speed flows. Static Density is denoted by ρ_e symbol.

How to calculate Static Density Equation using Stanton Number using this online calculator? To use this online calculator for Static Density Equation using Stanton Number, enter Local Heat Transfer Rate (q_w), Stanton Number (St), Static Velocity (u_e), Adiabatic Wall Enthalpy (h_aw) & Wall Enthalpy (h_w) and hit the calculate button. Here is how the Static Density Equation using Stanton Number calculation can be explained with given input values -> 1217.532 = 12000/(0.4*8.8*(102-99.2)).

FAQ

What is Static Density Equation using Stanton Number?

Static Density Equation using Stanton Number formula is defined as a measure of the effective density of a fluid in a hypersonic boundary layer, which is essential in understanding the flow behavior and heat transfer characteristics in high-speed flows and is represented as ρ_e = q_w/(St*u_e*(h_aw-h_w)) or Static Density = Local Heat Transfer Rate/(Stanton Number*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)). 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 Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow, 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 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 Wall Enthalpy is the total heat content of the wall boundary layer in a hypersonic flow, including both sensible and latent heat components.

How to calculate Static Density Equation using Stanton Number?

Static Density Equation using Stanton Number formula is defined as a measure of the effective density of a fluid in a hypersonic boundary layer, which is essential in understanding the flow behavior and heat transfer characteristics in high-speed flows is calculated using Static Density = Local Heat Transfer Rate/(Stanton Number*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)). To calculate Static Density Equation using Stanton Number, you need Local Heat Transfer Rate (q_w), Stanton Number (St), Static Velocity (u_e), 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, Static 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.

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