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1 | | -Model: |
2 | | - VSM: Vortex Step Method |
3 | | - LLT: Lifting Line Theory |
4 | | -PanelDistribution: |
5 | | - LINEAR: Linear distribution |
6 | | - COSINE: Cosine distribution |
7 | | - COSINE_VAN_GARREL: van Garrel cosine distribution |
8 | | - SPLIT_PROVIDED: Split provided sections |
9 | | - UNCHANGED: Keep original sections |
10 | | -InitialGammaDistribution: |
11 | | - ELLIPTIC: Elliptic distribution |
12 | | - ZEROS: Constant distribution |
| 1 | +# ============================================================================= |
| 2 | +# VSM Settings Configuration File |
| 3 | +# ============================================================================= |
| 4 | +# |
| 5 | +# This YAML file configures the Vortex Step Method (VSM) aerodynamic solver |
| 6 | +# for wing analysis. All simulation parameters are centralized here. |
| 7 | +# |
| 8 | +# FILE STRUCTURE: |
| 9 | +# ├── condition: Flight conditions (wind speed, angles, rates) |
| 10 | +# ├── wings: Wing geometry and discretization settings |
| 11 | +# └── solver_settings: Numerical solver parameters and convergence criteria |
| 12 | +# |
| 13 | +# AERODYNAMIC MODELS: |
| 14 | +# VSM: Vortex Step Method - Full 3D potential flow with wake modeling |
| 15 | +# LLT: Lifting Line Theory - Classical 1D approach for high aspect ratios |
| 16 | +# |
| 17 | +# PANEL DISTRIBUTIONS: |
| 18 | +# LINEAR: Uniform panel spacing along wingspan |
| 19 | +# COSINE: Cosine clustering (more panels at tips) |
| 20 | +# COSINE_VAN_GARREL: Van Garrel's modified cosine distribution |
| 21 | +# SPLIT_PROVIDED: Use predefined section splits from geometry |
| 22 | +# UNCHANGED: Preserve original geometry discretization |
| 23 | +# |
| 24 | +# INITIAL CIRCULATION DISTRIBUTIONS: |
| 25 | +# ELLIPTIC: Elliptical distribution (optimal for efficiency) |
| 26 | +# ZEROS: Start with zero circulation (cold start) |
| 27 | +# |
| 28 | +# SOLVER TYPES: |
| 29 | +# LOOP: Iterative fixed-point solver |
| 30 | +# NEWTON: Newton-Raphson nonlinear solver |
| 31 | +# |
| 32 | +# USAGE NOTES: |
| 33 | +# - n_panels should be divisible by n_groups for proper load balancing |
| 34 | +# - Higher n_panels improves accuracy but increases computation time |
| 35 | +# - Lower relaxation_factor if convergence issues occur |
| 36 | +# |
| 37 | +# ============================================================================= |
13 | 38 |
|
| 39 | +# ============================================================================= |
| 40 | +# FLIGHT CONDITIONS |
| 41 | +# ============================================================================= |
| 42 | +# Define the flight state for the aerodynamic analysis |
| 43 | +condition: |
| 44 | + wind_speed: 10.0 # [m/s] Free stream velocity magnitude |
| 45 | + alpha: 5.0 # [°] Angle of attack (pitch angle relative to flow) |
| 46 | + beta: 0.0 # [°] Sideslip angle (yaw angle relative to flow) |
| 47 | + yaw_rate: 0.0 # [°/s] Yaw rate (for dynamic analysis, 0 for static) |
| 48 | + |
| 49 | +# ============================================================================= |
| 50 | +# WING CONFIGURATION |
| 51 | +# ============================================================================= |
| 52 | +# Define wing geometry files and discretization parameters |
14 | 53 | wings: |
15 | | - - name: main_wing |
16 | | - n_panels: 40 |
17 | | - n_groups: 40 |
18 | | - spanwise_panel_distribution: LINEAR |
19 | | - spanwise_direction: [0.0, 1.0, 0.0] |
20 | | - remove_nan: true |
| 54 | + - name: V3_Kite # Wing identifier for output labeling |
| 55 | + yaml_path: data/TUDELFT_V3_KITE/wing_geometry_CAD_CFD_polars_pchip_fitted.yaml |
| 56 | + n_panels: 36 # Total number of panels along wingspan |
| 57 | + n_groups: 1 # Number of panel groups (must divide n_panels) |
| 58 | + spanwise_panel_distribution: LINEAR # Panel spacing algorithm |
| 59 | + spanwise_direction: [0.0, 1.0, 0.0] # Unit vector defining wingspan direction |
| 60 | + remove_nan: true # Remove NaN values from polar data |
| 61 | + |
| 62 | +# ============================================================================= |
| 63 | +# SOLVER CONFIGURATION |
| 64 | +# ============================================================================= |
| 65 | +# Numerical method settings and convergence criteria |
21 | 66 | solver_settings: |
22 | | - n_panels: 40 |
23 | | - n_groups: 40 |
24 | | - aerodynamic_model_type: VSM |
25 | | - density: 1.225 # air density [kg/m³] |
26 | | - max_iterations: 1500 |
27 | | - rtol: 1e-5 # relative error [-] |
28 | | - tol_reference_error: 0.001 |
29 | | - relaxation_factor: 0.03 # relaxation factor for convergence |
30 | | - artificial_damping: false # whether to apply artificial damping |
31 | | - k2: 0.1 # artificial damping parameter |
32 | | - k4: 0.0 # artificial damping parameter |
33 | | - type_initial_gamma_distribution: ELLIPTIC |
34 | | - core_radius_fraction: 1e-20 |
35 | | - mu: 1.81e-5 # dynamic viscosity [N·s/m²] |
36 | | - calc_only_f_and_gamma: false # whether to only output f and gamma |
| 67 | + # --- Core Aerodynamic Model --- |
| 68 | + aerodynamic_model_type: VSM # VSM=3D vortex method, LLT=lifting line theory |
| 69 | + solver_type: LOOP # LOOP=fixed-point iteration, NEWTON=Newton-Raphson |
| 70 | + |
| 71 | + # --- Physical Properties --- |
| 72 | + density: 1.225 # [kg/m³] Air density (ISA sea level) |
| 73 | + mu: 1.81e-5 # [N·s/m²] Dynamic viscosity (ISA sea level) |
| 74 | + |
| 75 | + # --- Convergence Control --- |
| 76 | + max_iterations: 5000 # Maximum solver iterations before timeout |
| 77 | + rtol: 1e-6 # Relative tolerance for convergence |
| 78 | + tol_reference_error: 0.001 # Reference error tolerance |
| 79 | + relaxation_factor: 0.01 # [0.001-0.1] Under-relaxation for stability |
| 80 | + |
| 81 | + # --- Numerical Stability --- |
| 82 | + artificial_damping: false # Enable artificial damping for unstable cases |
| 83 | + k2: 0.1 # 2nd-order damping coefficient |
| 84 | + k4: 0.0 # 4th-order damping coefficient |
| 85 | + core_radius_fraction: 1e-20 # Vortex core radius (fraction of chord) |
| 86 | + |
| 87 | + # --- Initial Conditions --- |
| 88 | + type_initial_gamma_distribution: ELLIPTIC # Starting circulation distribution |
| 89 | + |
| 90 | + # --- Output Control --- |
| 91 | + calc_only_f_and_gamma: false # true=compute only forces & circulation |
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