Fanno Flow Calculator | Compressible Duct Flow with Friction

📝 Configuration

Inlet Mach number ($M_1$):

Darcy Friction Factor ($f$):

Pipe Diameter ($D$) [mm]:

Pipe Length ($L$) [meters]:

Specific Heat Ratio ($\gamma$):

Inlet Stagnation Temp ($T_{01}$) [K] — Optional:

Inlet Stagnation Pressure ($P_{01}$) [kPa] — Optional:

Quick Presets:

📊 Results & Diagrams

Configure inputs and click Calculate Fanno Flow to view results.

📘 Calculation Methodology

Mathematical Model & Theory

Fanno flow refers to steady 1D compressible flow of an ideal gas in a constant-area duct with friction, assuming the duct is adiabatic (no heat transfer). Wall friction causes stagnation pressure losses and accelerates subsonic flows, while decelerating supersonic flows towards choking ($M=1$).

The Fanno relations are governed by the friction parameter equation:

$$\frac{f L^*}{D} = \frac{1-M^2}{\gamma M^2} + \frac{\gamma+1}{2\gamma} \ln\left[\frac{(\gamma+1)M^2}{2 + (\gamma-1)M^2}\right]$$

Static temperature and pressure ratios relative to the critical sonic state ($M^* = 1.0$) are computed as follows:

$$\frac{T}{T^*} = \frac{\gamma+1}{2+(\gamma-1)M^2}, \quad \frac{P}{P^*} = \frac{1}{M} \sqrt{\frac{\gamma+1}{2+(\gamma-1)M^2}}$$

Academic References

Shapiro, Ascher H.: The Dynamics and Thermodynamics of Compressible Fluid Flow, Ronald Press.
Anderson, John D.: Modern Compressible Flow, McGraw-Hill.

Worked Engineering Example

Problem Statement:
Air ($\gamma = 1.4$) enters a $D = 50\text{ mm}$ duct with Darcy friction factor $f = 0.02$ at $M_1 = 0.5$. Calculate the critical choking length $L^*$ and the exit Mach $M_2$ for a duct length $L = 1.0\text{ m}$.

Step-by-step Solution:
1. Evaluate the Fanno friction parameter $\frac{f L^*}{D}$ for $M_1 = 0.5$:
$$\frac{f L_1^*}{D} = \frac{1 - 0.25}{1.4 \times 0.25} + \frac{2.4}{2.8} \ln\left[\frac{2.4 \times 0.25}{2 + 0.4 \times 0.25}\right] = 1.0691$$ 2. Calculate the choking length $L_1^*$:
$$L_1^* = \frac{1.0691 \times 0.05\text{ m}}{0.02} = 2.6727\text{ m}$$ 3. Evaluate the remaining choking parameter at exit (2):
$$\frac{f L_2^*}{D} = 1.0691 - \frac{0.02 \times 1.0\text{ m}}{0.05\text{ m}} = 1.0691 - 0.400 = 0.6691$$ 4. Invert Fanno friction relation numerically for $\frac{f L_2^*}{D} = 0.6691$ to find $M_2$ on the subsonic branch:
$$M_2 = 0.5609$$ Final Results:
• Critical pipe length: 2.67 m
• Exit Mach: 0.5609