Ratio Of New And Old Temperature Calculator

Temperature Ratio Formula:

\[ T_{shockratio} = \left(1 + \frac{(\gamma - 1)}{2} \cdot \frac{V_n}{c_{old}}\right)^2 \]

Specific Heat Ratio (γ):

(dimensionless)

Normal Velocity (Vn):

m/s

Old Speed of Sound (c_old):

m/s

Temperature Ratio (T_shockratio):

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1. What is Temperature Ratio across Shock?

The temperature ratio across shock is the ratio of downstream temperature to upstream temperature across a shock wave. It quantifies the temperature change that occurs when a fluid passes through a shock wave, which is crucial in aerodynamics and compressible flow analysis.

2. How Does the Calculator Work?

The calculator uses the temperature ratio formula:

\[ T_{shockratio} = \left(1 + \frac{(\gamma - 1)}{2} \cdot \frac{V_n}{c_{old}}\right)^2 \]

Where:

\( \gamma \) — Specific heat ratio of the gas
\( V_n \) — Normal velocity to the shock wave (m/s)
\( c_{old} \) — Speed of sound before the shock (m/s)

Explanation: This formula calculates the temperature ratio across a normal shock wave based on the specific heat ratio, normal velocity component, and upstream speed of sound.

3. Importance of Temperature Ratio Calculation

Details: Calculating temperature ratio across shock waves is essential for understanding energy transfer, thermodynamic changes, and flow behavior in supersonic and hypersonic flows, particularly in aerospace engineering and gas dynamics.

4. Using the Calculator

Tips: Enter the specific heat ratio (γ > 1), normal velocity (positive value), and old speed of sound (positive value). All values must be valid physical quantities.

5. Frequently Asked Questions (FAQ)

Q1: What is a typical range for specific heat ratio (γ)?
A: For diatomic gases like air, γ ≈ 1.4; for monatomic gases like argon, γ ≈ 1.67; values range between 1 and 5/3 for most gases.

Q2: How does normal velocity relate to shock strength?
A: Higher normal velocity relative to the speed of sound results in stronger shocks and higher temperature ratios across the shock wave.

Q3: What physical phenomena does this temperature ratio represent?
A: It represents the temperature increase due to compression and energy dissipation across a shock wave in compressible flow.

Q4: Are there limitations to this formula?
A: This formula applies to ideal gases with constant specific heats across normal shock waves in steady, adiabatic flow.

Q5: How is this used in practical applications?
A: This calculation is used in aircraft design, rocket propulsion, wind tunnel testing, and analysis of high-speed flow phenomena.