propeller_bemt_analysis
Analyze propeller performance by calculating thrust, torque, power, and efficiency at multiple RPMs using Blade Element Momentum Theory.
Instructions
Analyze propeller performance using Blade Element Momentum Theory.
Args: propeller_geometry: Propeller geometry (diameter_m, pitch_m, num_blades, etc.) operating_conditions: Operating conditions (rpm_list, velocity_ms, altitude_m) analysis_options: Optional analysis settings
Returns: Formatted string with propeller performance analysis including thrust, torque, power, efficiency, and advance ratio at each RPM.
Raises: No exceptions are raised directly; errors are returned as formatted strings. ImportError is caught when propulsion packages are not installed.
Note: BEMT iteratively solves for the inflow angle (phi) at each blade element by balancing: 1. Blade Element Theory: Local lift and drag from 2D airfoil data at the effective angle of attack (alpha = phi - pitch_angle). 2. Momentum Theory: Axial and tangential momentum changes through an annular ring of the rotor disk. Convergence is achieved when the induced velocity factors (a, a') satisfy both theories simultaneously. The advance ratio J = V / (n*D) characterizes the operating condition.
Input Schema
| Name | Required | Description | Default |
|---|---|---|---|
| propeller_geometry | Yes | ||
| operating_conditions | Yes | ||
| analysis_options | No |
Output Schema
| Name | Required | Description | Default |
|---|---|---|---|
| result | Yes |