Standard Atmosphere Calculator
up to 81 km altitude Altitude: metersfeet Delta T (K): Airspeed: m/skm/hmphknots Reference Length: metersfeet Select Unit System: Standard International Units (SI)English Units Calculate Results
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NASA Benchmarks
Within the field of computational fluid dynamics (CFD), NASA benchmarks hold significant importance as they serve as fundamental standards for validating simulation methods and software. These benchmarks are essential in ensuring the accuracy and reliability of open-source software used in aerospace and engineering applications. Here, you’ll find a variety of validation cases designed for different
NAFEMS Benchmarks
In the realm of structural analysis, NAFEMS benchmarks are vital reference points for validating finite element method (FEM) and finite element analysis (FEA) simulations. They provide essential standards to ensure the accuracy and reliability of open-source software in engineering applications. Here, you can find a range of validation cases for various scenarios, all crucial for
2D NACA 0012 Airfoil with Xfoil
Description Calculate the lift and drag for NACA 0012 airfoil at given Reynolds and Mach number. Reference Analysis type Isotherm, incompressible Tools used Geometry Boundary conditions Isotherm, incompressible flow Fluid properties Dry air at standard seal level: Computation target The quantities of interest for comparison are as follows: where amax is the maximum angle of attack