A MATLAB Function that Outputs the required data for the preliminary design of the Airframe. it is just an initial version of what would be achived in building MATLAB/Python Functions/Scripts/Program/Libraries that facilitate and efficiently increase the speed of the Aerospace engineer performed job!
Outputs the required data for the preliminary design of the Airframe
Input parameters:
- MTOW: Maximum Take-off weight of the plane
- Static_Margin: Static Margin is The difference between the actual CG location and the neutral point
- AR_Wing: Aspect Ratio of the Wing
- V_stall: Stall velocity
- Cl_max: Maximum coefficient of lift
- TR: Taper Ratio
- Volume_Hori: Horizontal Tail volume coefficient
- Volume_Vert: Vertical Tail volume coefficient
- SHori_per_SWing: Horizontal Tail Area devided by Vertical Tail Area
- AR_Hori: Aspect Ratio of the Horizontal Tail
- NeutralP_X: Neutral point on the X-axis
Output: Displays the needed data for the Airframe design in Preliminary stage including if the CAD Model is not provided
Note!!! At first in your analysis consider the NeutralP_X to be nan then use XLFR5 to find the NeutralP_X in advanced stage of your analysis, finally come and insert it again to continue!!!
Note!!! New updates will be provided soon!
license has its own file, and it is under AeroSpace_CairoUniversity GitHub Community License. I am the main contributor.
React
Typescript
Django
Laravel
Facebook
Microsoft
Google
Alibaba
D3
Tencent