Aircraft Design as an Iterative Process Requiring Multiple Computations

Aircraft design necessitates repeated iterative processes and substantial computational efforts. To efficiently handle these calculations, we have developed a suite of MATLAB programs. These programs include:

- [program_1.m] Overall Aircraft Parameter Calculation Program: Computes key design parameters such as weight, balance, and performance metrics using iterative optimization algorithms.

- [program_2.m] Aircraft Aerodynamic Curve Calculation Program: Generates lift, drag, and moment coefficients across various flight conditions through aerodynamic modeling and curve-fitting techniques.

- [program_3.m] Wing Load Distribution Calculation Program: Determines spanwise load distribution using structural analysis methods and integration algorithms.

- [program_4.m] Longitudinal Dynamic Stability Calculation Program for Cruise Conditions: Analyzes pitch stability derivatives and dynamic response characteristics during cruise using state-space modeling.

- [program_5.m] Lateral-Directional Stability Calculation Program: Evaluates roll and yaw stability parameters through derivative calculations and control system analysis.

- [program_6.rar] Level Flight Speed Range Calculation Program: Determines operational speed envelopes using performance equations and constraint analysis methods.

- [program_7.rar] Propeller Characteristics Calculation Program: Computes propeller efficiency, thrust, and power coefficients based on blade element theory and performance maps.

These programs serve as essential tools in our design process, enabling accurate computation and evaluation of various aircraft parameters. The source code incorporates numerical methods, aerodynamic models, and stability analysis algorithms. If you're interested in examining the implementation details, you can access the source code through the links provided above.