Transformed Conical Variable with Cone Angle in Hypersonic Flow Calculator

✖Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle.ⓘ Wave Angle [β]			+10% -10%
✖Semi Angle of Cone is the semi-vertical angle formed by the cone.ⓘ Semi Angle of Cone [α]			+10% -10%

✖The Transformed Conical Variable is the ratio of base radius of cone to product of the slenderness ratio and height of cone at which the radius is taken.ⓘ Transformed Conical Variable with Cone Angle in Hypersonic Flow [θ_-]

⎘ Copy

👎

Formula

✖

Transformed Conical Variable with Cone Angle in Hypersonic Flow

Formula

`"θ"_{"-"} = ("β"*(180/pi))/"α"`

Example

`"1.900115"=("0.286rad"*(180/pi))/"8.624rad"`

Calculator

LaTeX

Reset

👍

Download Approximate Methods of Hypersonic Inviscid Flowfields Formulas PDF PDF Image

Transformed Conical Variable with Cone Angle in Hypersonic Flow Solution

STEP 0: Pre-Calculation Summary

Formula Used

Transformed Conical Variable = (Wave Angle*(180/pi))/Semi Angle of Cone
θ_- = (β*(180/pi))/α
This formula uses 1 Constants, 3 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

Transformed Conical Variable - The Transformed Conical Variable is the ratio of base radius of cone to product of the slenderness ratio and height of cone at which the radius is taken.
Wave Angle - (Measured in Radian) - Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle.
Semi Angle of Cone - (Measured in Radian) - Semi Angle of Cone is the semi-vertical angle formed by the cone.

STEP 1: Convert Input(s) to Base Unit

Wave Angle: 0.286 Radian --> 0.286 Radian No Conversion Required
Semi Angle of Cone: 8.624 Radian --> 8.624 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

θ_- = (β*(180/pi))/α --> (0.286*(180/pi))/8.624

Evaluating ... ...

θ_- = 1.90011513691344

STEP 3: Convert Result to Output's Unit

1.90011513691344 --> No Conversion Required

FINAL ANSWER

1.90011513691344 ≈ 1.900115 <-- Transformed Conical Variable

(Calculation completed in 00.004 seconds)

You are here -

Home » Engineering » Mechanical » Fluid Mechanics » Hypersonic Flow » Approximate Methods of Hypersonic Inviscid Flowfields » Transformed Conical Variable with Cone Angle in Hypersonic Flow

Credits

Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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

Verified by Anshika Arya

National Institute Of Technology (NIT), Hamirpur

Anshika Arya has verified this Calculator and 2500+ more calculators!

< 11 Approximate Methods of Hypersonic Inviscid Flowfields Calculators

Non-Dimensional Parallel Velocity Component for High Mach Number

Go Non Dimensionalized Upstream Parallel Velocity = 1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1)

Non-Dimensional Pressure for High Mach Number

Go Non Dimensionalized Pressure For High Mech Number = 2*(sin(Wave Angle))^2/(Specific Heat Ratio+1)

Transformed Conical Variable with Wave Angle

Go Transformed Conical Variable With Wave Angle = (Wave Angle*(180/pi))/Slenderness Ratio

Transformed Conical Variable

Go Transformed Conical Variable = Radius of Cone/(Slenderness Ratio*Height of Cone)

Non-Dimensional Radius for Hypersonic Vehicles

Go Non Dimensionalized Radius = Radius of Cone/(Slenderness Ratio*Height of Cone)

Non-Dimensional Perpendicular Velocity Component for High Mach Number

Go Non Dimensionalized Velocity = (sin(2*Wave Angle))/(Specific Heat Ratio-1)

Transformed Conical Variable with Cone Angle in Hypersonic Flow

Go Transformed Conical Variable = (Wave Angle*(180/pi))/Semi Angle of Cone

Non-Dimensional Pressure

Go Non Dimensionalized Pressure = Pressure/(Density*Freestream Velocity^2)

Non-Dimensional Density for High Mach Number

Go Non Dimensionalized Density = (Specific Heat Ratio+1)/(Specific Heat Ratio-1)

Slenderness Ratio with Cone Radius for Hypersonic Vehicle

Go Slenderness Ratio For Hypersonic Vehicles = Radius of Cone/Height of Cone

Non-Dimensional Density

Go Non Dimensionalized Density = Density/Liquid Density

Transformed Conical Variable with Cone Angle in Hypersonic Flow Formula

Transformed Conical Variable = (Wave Angle*(180/pi))/Semi Angle of Cone
θ_- = (β*(180/pi))/α

What is wave angle?

Wave angle is the shock angle created by the oblique shock, this is not similar to the mach angle, it is formed when body moves at hypersonic speed in a fluid

How to Calculate Transformed Conical Variable with Cone Angle in Hypersonic Flow?

Transformed Conical Variable with Cone Angle in Hypersonic Flow calculator uses Transformed Conical Variable = (Wave Angle*(180/pi))/Semi Angle of Cone to calculate the Transformed Conical Variable, Transformed Conical Variable with Cone Angle in Hypersonic Flow is a fundamental concept in aerodynamics and fluid mechanics, particularly in the study of high-speed flows encountered in hypersonic flight, this formula characterizes the transformation of flow variables in hypersonic flows over a conical surface. It is instrumental in understanding the behavior of aerodynamic parameters such as pressure, density, and temperature in hypersonic flight regimes. Transformed Conical Variable is denoted by θ_- symbol.

How to calculate Transformed Conical Variable with Cone Angle in Hypersonic Flow using this online calculator? To use this online calculator for Transformed Conical Variable with Cone Angle in Hypersonic Flow, enter Wave Angle (β) & Semi Angle of Cone (α) and hit the calculate button. Here is how the Transformed Conical Variable with Cone Angle in Hypersonic Flow calculation can be explained with given input values -> 1.940588 = (0.286*(180/pi))/8.624.

FAQ

What is Transformed Conical Variable with Cone Angle in Hypersonic Flow?

Transformed Conical Variable with Cone Angle in Hypersonic Flow is a fundamental concept in aerodynamics and fluid mechanics, particularly in the study of high-speed flows encountered in hypersonic flight, this formula characterizes the transformation of flow variables in hypersonic flows over a conical surface. It is instrumental in understanding the behavior of aerodynamic parameters such as pressure, density, and temperature in hypersonic flight regimes and is represented as θ_- = (β*(180/pi))/α or Transformed Conical Variable = (Wave Angle*(180/pi))/Semi Angle of Cone. Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle & Semi Angle of Cone is the semi-vertical angle formed by the cone.

How to calculate Transformed Conical Variable with Cone Angle in Hypersonic Flow?

Transformed Conical Variable with Cone Angle in Hypersonic Flow is a fundamental concept in aerodynamics and fluid mechanics, particularly in the study of high-speed flows encountered in hypersonic flight, this formula characterizes the transformation of flow variables in hypersonic flows over a conical surface. It is instrumental in understanding the behavior of aerodynamic parameters such as pressure, density, and temperature in hypersonic flight regimes is calculated using Transformed Conical Variable = (Wave Angle*(180/pi))/Semi Angle of Cone. To calculate Transformed Conical Variable with Cone Angle in Hypersonic Flow, you need Wave Angle (β) & Semi Angle of Cone (α). With our tool, you need to enter the respective value for Wave Angle & Semi Angle of Cone 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 Transformed Conical Variable?

In this formula, Transformed Conical Variable uses Wave Angle & Semi Angle of Cone. We can use 1 other way(s) to calculate the same, which is/are as follows -

Transformed Conical Variable = Radius of Cone/(Slenderness Ratio*Height of Cone)

Home

FREE PDFs

🔍 Search