REF: SM YAHYA · RADHAKRISHNAN

SHOCK WAVE ANALYZER

NORMAL · OBLIQUE · PRANDTL-MEYER EXPANSION

⚡ Compressible Flow Calculator
γ=1.4, R=287 J/kg·K. Oblique shock: correct weak-shock bisection solver.
Normal shock: M₁ > 1. Flow always becomes subsonic. Entropy rises, total pressure drops.
▸ Normal Shock Results

NACA AIRFOIL GENERATOR

4-DIGIT · 5-DIGIT · 6-DIGIT · FULL AERODYNAMIC ANALYSIS

✈ Airfoil Profile Generator
Enter NACA code → generates shape + all aerodynamic performance charts (Cl, Cd, L/D, Cm, Cp, Polar).
Format: MPTT — M=max camber(%÷100), P=camber position(×10%), TT=thickness(%)
Examples: 0012 (symmetric), 2412, 4412, 0009, 6412
Format: LPPTT — L=design CL(×0.15), PP=position(×0.05c), TT=thickness(%)
Example: 23012 → CL≈0.3, position=15%, 12% thickness
6-series approximation using modified camber with laminar bucket characteristics.
Format: Standard Selig/Lednicer .dat file format (X, Y coordinates).
📄
Upload .dat File
Drop file here or click to browse

ISENTROPIC FLOW

VARIABLE γ · MACH NUMBER · AREA RATIO · FLOW PROPERTIES

📊 Isentropic Flow Calculator
Full isentropic relations for any Mach number and any γ. Includes PM function and Mach angle.
▸ Isentropic Flow Results
📋 Isentropic Flow Table — Custom γ
Enter any γ (e.g. 1.4 for air, 1.3 for combustion gas, 1.67 for monatomic). Set Mach range and step size.

SHOCK WAVE CHARTS

θ-β-M · NORMAL SHOCK PROPERTIES · PRANDTL-MEYER · TOTAL PRESSURE

📉 Interactive Shock Diagrams
All charts computed for γ=1.4. Switch tabs to explore different diagrams.
θ-β-M diagram: each curve = one upstream Mach number. X = shock wave angle β, Y = deflection angle θ. Peak of curve = θ_max (detachment point). Dashed white = sonic line M₂=1 separating weak/strong shock solutions. Highlighted curve (white/bold) = selected M₁.