SUMMARY
The discussion focuses on calculating the oblique shock angle (beta) for a supersonic airfoil using MATLAB. Users suggest utilizing MATLAB's numerical solving capabilities, specifically the 'fsolve' or 'solve' commands, to determine beta, especially in the absence of the Symbolic Math Toolbox. One participant mentions using Maple to derive a lengthy equation for beta, indicating the complexity of the calculations involved. The conversation highlights the need for iterative methods to achieve accurate results in supersonic flow analysis.
PREREQUISITES
- Understanding of supersonic aerodynamics and oblique shock theory
- Familiarity with MATLAB programming and its numerical solving functions
- Knowledge of the geometry of airfoils and their impact on lift and drag
- Experience with alternative computational tools like Maple or Mathematica
NEXT STEPS
- Research MATLAB's 'fsolve' and 'solve' functions for numerical solutions
- Study the equations governing oblique shock waves in supersonic flow
- Explore the use of Maple for complex mathematical computations
- Learn about iterative methods for solving nonlinear equations in aerodynamics
USEFUL FOR
Aerospace engineers, MATLAB programmers, and students working on supersonic flow simulations will benefit from this discussion, particularly those focused on lift and drag calculations for airfoils.