get_airfoil_database
Access aerodynamic coefficients from an airfoil database to support aircraft performance analysis and flight planning calculations.
Instructions
Get available airfoil database with aerodynamic coefficients.
Returns: JSON string with airfoil database
Input Schema
TableJSON Schema
| Name | Required | Description | Default |
|---|---|---|---|
No arguments | |||
Output Schema
TableJSON Schema
| Name | Required | Description | Default |
|---|---|---|---|
| result | Yes |
Implementation Reference
- Main handler function for the 'get_airfoil_database' tool. Imports AIRFOIL_DATABASE from integrations and returns it as a formatted JSON string.
def get_airfoil_database() -> str: """Get available airfoil database with aerodynamic coefficients. Returns: JSON string with airfoil database """ try: from ..integrations.aero import AIRFOIL_DATABASE return json.dumps(AIRFOIL_DATABASE, indent=2) except ImportError: return "Airfoil database not available" except Exception as e: logger.error(f"Airfoil database error: {str(e)}", exc_info=True) return f"Airfoil database error: {str(e)}" - aerospace_mcp/fastmcp_server.py:99-104 (registration)Registration of the get_airfoil_database tool (and related aerodynamics tools) in the FastMCP server.
# Aerodynamics tools mcp.tool(wing_vlm_analysis) mcp.tool(airfoil_polar_analysis) mcp.tool(calculate_stability_derivatives) mcp.tool(get_airfoil_database) - aerospace_mcp/fastmcp_server.py:20-25 (registration)Import of the get_airfoil_database handler from tools.aerodynamics.
from .tools.aerodynamics import ( airfoil_polar_analysis, calculate_stability_derivatives, get_airfoil_database, wing_vlm_analysis, ) - The AIRFOIL_DATABASE dictionary containing coefficients for common airfoils, used by the tool handler.
AIRFOIL_DATABASE = { "NACA0012": { "cl_alpha": 6.28, # per radian "cl0": 0.0, # zero-angle lift coefficient (symmetric) "cd0": 0.006, "cl_max": 1.4, "alpha_stall_deg": 15.0, "cm0": 0.0, # symmetric airfoil }, "NACA2412": { "cl_alpha": 6.28, "cl0": 0.25, # zero-angle lift coefficient (cambered) "cd0": 0.007, "cl_max": 1.6, "alpha_stall_deg": 16.0, "cm0": -0.05, }, "NACA4412": { "cl_alpha": 6.28, "cl0": 0.40, # zero-angle lift coefficient (4% camber) "cd0": 0.008, "cl_max": 1.7, "alpha_stall_deg": 17.0, "cm0": -0.08, }, "NACA6412": { "cl_alpha": 6.28, "cl0": 0.55, # zero-angle lift coefficient (6% camber) "cd0": 0.007, "cl_max": 1.8, "alpha_stall_deg": 18.0, "cm0": -0.12, }, "CLARKY": { "cl_alpha": 6.0, "cl0": 0.30, # zero-angle lift coefficient (cambered) "cd0": 0.008, "cl_max": 1.5, "alpha_stall_deg": 14.0, "cm0": -0.06, }, }