All Physics Calculator Related Post

    Prandtl Number Calculator Calculation Mode: Manual InputSelect from Material Database Dynamic Viscosity μ (Pa·s or kg/m·s): Specific Heat Capacity Cp (J/kg·K): Thermal Conductivity k (W/m·K): Select Fluid/Material: Air at 20°CAir at 100°CWater at 20°CWater at 100°CEngine Oil (SAE 30)GlycerinMercuryHelium GasCarbon Dioxide Temperature (°C) – for reference: Prandtl Number Formula: Pr = (ν × […]

    Fanno Flow Calculator Known Parameter: Initial Mach Number (M₁)4fL*/D (Friction Length to Choke)P/P* RatioT/T* Ratioρ/ρ* Ratio Enter Value: Specific Heat Ratio (γ): Air (γ = 1.4)Helium (γ = 1.667)Hot Combustion Products (γ ≈ 1.3)High-Temperature Air (γ ≈ 1.33) Important: In Fanno flow, friction always drives the flow toward Mach = 1 (sonic choking).

    Rayleigh Flow Calculator Known Parameter: Initial Mach Number (M₁)T/T* RatioP/P* Ratioρ/ρ* Ratio Enter Value: Specific Heat Ratio (γ): Air (γ = 1.4)Monatomic Gas (γ = 1.667)Combustion Products (γ ≈ 1.3)Diatomic Gas Hot (γ ≈1.33) Tip: For subsonic flow (M < 1), heat addition increases Mach number toward 1 (choked). For supersonic flow (M

Compressive Flow Calculator Flow Type: Isentropic Nozzle (1D)Fanno Flow (Friction)Rayleigh Flow (Heat Addition)Normal Shock Input Parameters: Mach Number M: Specific Heat Ratio γ: Stagnation Pressure P₀ (Pa): Stagnation Temperature T₀ (K): Duct Length L (m): Hydraulic Diameter D (m): Friction Factor f: Heat Addition q (J/kg): Calculate Compressive Flow Enter parameters and click “Calculate Compressive

Sonic Boom Calculator Flight Profile: Level Supersonic CruiseDive (Accelerating)Boom Carpet (Ground) Aircraft & Flight Parameters: Flight Mach Number M: Flight Altitude h (m): Aircraft Length L (m): Aircraft Weight W (kg): Ambient Temperature T (°C): Relative Humidity (%): Calculate Sonic Boom Enter flight parameters and click “Calculate Sonic Boom” to get overpressure, arrival time, and

Shock Wave Calculator Shock Type: Normal Shock (1D)Oblique Shock (Wedge)Bow Shock (Blunt Body) Flow Conditions: Upstream Mach Number M₁: Specific Heat Ratio γ: Wedge Half-Angle θ (degrees): Upstream Pressure P₁ (Pa): Upstream Temperature T₁ (K): Upstream Density ρ₁ (kg/m³): Calculate Shock Wave Enter upstream conditions and click “Calculate Shock Wave” to get downstream properties and

Mach Number Calculator Calculation Mode: From Velocity & TemperatureFrom Altitude & Speed (IAS/TAS)Shock Wave Angle (Oblique) Input Parameters: Flow/Speed V (m/s): Temperature T (°C): Altitude (m): Indicated Airspeed (knots): Specific Heat Ratio γ: Shock Angle β (degrees): Calculate Mach Number Enter parameters and click “Calculate Mach Number” to get M, speed of sound, and flow

Lift Coefficient Calculator Airfoil Type: NACA 0012 (Symmetric)NACA 2412 (Cambered)Flat PlateCustom (Thin Airfoil Theory) Flight Conditions: Free-Stream Velocity V (m/s): Air Density ρ (kg/m³): Chord Length c (m): Wing Area S (m²): Angle of Attack α (degrees): Dynamic Viscosity μ (Pa·s): Calculate Lift Coefficient Enter parameters and click “Calculate Lift Coefficient” to get C_L, lift

Drag Coefficient Calculator Object Shape: SphereCylinder (Cross-flow)Airfoil (NACA 0012)Passenger CarFlat Plate (Perpendicular)CubeCustom (Input C_D) Flow Conditions: Free-Stream Velocity V (m/s): Air Density ρ (kg/m³): Reference Area A (m²): Characteristic Length L (m): Dynamic Viscosity μ (Pa·s): Angle of Attack α (degrees): Calculate Drag Coefficient Enter parameters and click “Calculate Drag Coefficient” to get C_D, drag

Boundary Layer Calculator Flow Configuration: Flat Plate (Blasius)Pipe Entrance RegionAirfoil (Approximate) Flow Parameters: Free-Stream Velocity U (m/s): Distance from Leading Edge x (m): Fluid Density ρ (kg/m³): Dynamic Viscosity μ (Pa·s): Calculate Boundary Layer Enter flow parameters and click “Calculate Boundary Layer” to get thickness, shear stress, and regime. About the Boundary Layer Calculator The