Aerospace MCP

"""Aerodynamics analysis tools for the Aerospace MCP server.""" import json import logging logger = logging.getLogger(__name__) def wing_vlm_analysis( wing_config: dict, flight_conditions: dict, analysis_options: dict | None = None ) -> str: """Analyze wing aerodynamics using Vortex Lattice Method or simplified lifting line theory. Args: wing_config: Wing configuration (span_m, chord_m, sweep_deg, etc.) flight_conditions: Flight conditions (airspeed_ms, altitude_m, alpha_deg) analysis_options: Optional analysis settings Returns: Formatted string with aerodynamic analysis results """ try: from ..integrations.aero import wing_vlm_analysis as _wing_analysis result = _wing_analysis(wing_config, flight_conditions, analysis_options) # Format response result_lines = ["Wing Aerodynamic Analysis (VLM)", "=" * 50] # Wing configuration result_lines.extend( [ "Configuration:", f" Span: {wing_config.get('span_m', 0):.1f} m", f" Chord: {wing_config.get('chord_m', 0):.1f} m", f" Aspect Ratio: {result.get('aspect_ratio', 0):.1f}", f" Sweep: {wing_config.get('sweep_deg', 0):.1f}°", "", ] ) # Flight conditions result_lines.extend( [ "Flight Conditions:", f" Airspeed: {flight_conditions.get('airspeed_ms', 0):.1f} m/s", f" Altitude: {flight_conditions.get('altitude_m', 0):.0f} m", f" Angle of Attack: {flight_conditions.get('alpha_deg', 0):.1f}°", "", ] ) # Results result_lines.extend( [ "Aerodynamic Results:", f" Lift Coefficient: {result.get('cl', 0):.3f}", f" Drag Coefficient: {result.get('cd', 0):.4f}", f" L/D Ratio: {result.get('cl_cd_ratio', 0):.1f}", f" Lift (N): {result.get('lift_n', 0):.0f}", f" Drag (N): {result.get('drag_n', 0):.0f}", "", ] ) # Add JSON data json_data = json.dumps(result, indent=2) result_lines.extend(["JSON Data:", json_data]) return "\n".join(result_lines) except ImportError: return "Wing analysis not available - install aerodynamics packages" except Exception as e: logger.error(f"Wing analysis error: {str(e)}", exc_info=True) return f"Wing analysis error: {str(e)}" def airfoil_polar_analysis( airfoil_name: str, reynolds_number: float = 1000000, mach_number: float = 0.1, alpha_range_deg: list[float] | None = None, ) -> str: """Generate airfoil polar data (CL, CD, CM vs alpha) using database or advanced methods. Args: airfoil_name: Airfoil name (e.g., 'NACA2412', 'NACA0012') reynolds_number: Reynolds number mach_number: Mach number alpha_range_deg: Optional angle of attack range, defaults to [-10, 20] deg Returns: Formatted string with airfoil polar data """ try: from ..integrations.aero import airfoil_polar_analysis as _airfoil_analysis alpha_range_deg = alpha_range_deg or list(range(-10, 21, 2)) result = _airfoil_analysis( airfoil_name, reynolds_number, mach_number, alpha_range_deg ) # Format response result_lines = [f"Airfoil Polar Analysis: {airfoil_name}", "=" * 60] result_lines.extend( [ f"Reynolds Number: {reynolds_number:.0e}", f"Mach Number: {mach_number:.3f}", "", f"{'Alpha (°)':>8} {'CL':>8} {'CD':>8} {'CM':>8} {'L/D':>8}", ] ) result_lines.append("-" * 50) for point in result.get("polar_data", []): result_lines.append( f"{point.get('alpha_deg', 0):8.1f} {point.get('cl', 0):8.4f} " f"{point.get('cd', 0):8.5f} {point.get('cm', 0):8.4f} " f"{point.get('cl_cd_ratio', 0):8.1f}" ) # Add JSON data json_data = json.dumps(result, indent=2) result_lines.extend(["", "JSON Data:", json_data]) return "\n".join(result_lines) except ImportError: return "Airfoil analysis not available - install aerodynamics packages" except Exception as e: logger.error(f"Airfoil analysis error: {str(e)}", exc_info=True) return f"Airfoil analysis error: {str(e)}" def calculate_stability_derivatives(wing_config: dict, flight_conditions: dict) -> str: """Calculate basic longitudinal stability derivatives for a wing. Args: wing_config: Wing configuration parameters flight_conditions: Flight conditions Returns: JSON string with stability derivatives """ try: from ..integrations.aero import calculate_stability_derivatives as _stability result = _stability(wing_config, flight_conditions) return json.dumps(result, indent=2) except ImportError: return "Stability analysis not available - install aerodynamics packages" except Exception as e: logger.error(f"Stability analysis error: {str(e)}", exc_info=True) return f"Stability analysis error: {str(e)}" 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)}"