Area Ratio Formula:
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Definition: This calculator computes the nozzle area ratio (A/A*) for a given Mach number in compressible fluid flow.
Purpose: It helps aerospace engineers and fluid dynamicists design nozzles and analyze compressible flow conditions.
The calculator uses the isentropic flow relation:
Where:
Explanation: The formula relates the flow area to the critical (throat) area for isentropic flow of an ideal gas.
Details: Accurate area ratio calculations are essential for designing convergent-divergent nozzles in rockets, jet engines, and wind tunnels.
Tips: Enter the Mach number (must be > 0) and specific heat ratio (default 1.4 for air). The calculator will compute the corresponding area ratio.
Q1: What is the physical meaning of A/A*?
A: It represents how much the flow area must expand or contract to achieve a particular Mach number in isentropic flow.
Q2: What's a typical value for γ?
A: For air, γ ≈ 1.4. For monatomic gases (like helium), γ ≈ 1.67. For diatomic gases at high temperature, γ ≈ 1.3.
Q3: Can this be used for subsonic and supersonic flows?
A: Yes, the formula works for both subsonic (M < 1) and supersonic (M > 1) flows, but not at exactly M = 1 at the throat.
Q4: What if I know A/A* and want to find M?
A: You would need to solve the equation numerically as there's no closed-form solution for M given A/A*.
Q5: Does this account for real gas effects?
A: No, this assumes ideal gas behavior and isentropic flow. For real gases, additional corrections may be needed.