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

Implementation Reference

aerospace_mcp/tools/aerodynamics.py:160-176 (handler)

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,
)

aerospace_mcp/integrations/aero.py:36-77 (helper)

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,
    },
}

Aerospace MCP