1. What is the Oblique Shock Angle Equation?

The oblique shock angle equation calculates the wave angle (β) formed when a supersonic flow encounters a wedge or corner. This is fundamental in aerodynamics and compressible flow analysis.

2. How Does the Calculator Work?

The calculator uses the oblique shock angle equation:

Where:

• \( m \) — Mach number (dimensionless)
• \( \gamma \) — Specific heat ratio (dimensionless)
• \( \beta \) — Shock wave angle (radians)

Explanation: The equation relates the shock angle to the incoming Mach number and the gas properties through the specific heat ratio.

3. Importance of Oblique Shock Calculations

Details: Oblique shock analysis is crucial for designing supersonic aircraft, missiles, and rocket nozzles, as well as understanding high-speed flow phenomena.

4. Using the Calculator

Tips: Enter Mach number (must be >1) and specific heat ratio (γ=1.4 for air). The calculator will output the shock angle in degrees.

5. Frequently Asked Questions (FAQ)

Q1: What is the physical meaning of the shock angle?
A: The shock angle is the angle between the shock wave and the upstream flow direction.

Q2: What's a typical value for γ?
A: For air at standard conditions, γ ≈ 1.4. For monatomic gases it's 1.67, for diatomic 1.4, and for polyatomic ≈1.3.

Q3: What happens at Mach 1?
A: The equation breaks down at Mach 1 as oblique shocks only form in supersonic flow (Mach >1).

Q4: Are there limitations to this equation?
A: This is the ideal gas solution. Real gas effects become important at very high temperatures.

Q5: How does shock angle vary with Mach number?
A: For a given deflection angle, shock angle decreases as Mach number increases.