HELICOPTER AERODYNAMICS CARs

ADVANCED HELICOPTER AERODYNAMICS SIMULATION Full Mod Description for Arma Reforger (shortened to ~4800 chars) OVERVIEW Adds realistic aerodynamic simulation for all helicopters in Arma Reforger. Each helicopter gets a unique profile based on real specs. Flight physics use aviation formulas for effects like ground effect, ETL, VRS, etc. SUPPORTED HELICOPTERS UH-1H Huey — rotor radius 7.32 m, 2 blades, mass 3629 kg, power 1100 kW Mi-8MT Hip — rotor radius 10.65 m, 5 blades, mass 11100 kg, power 3280 kW Mi-24 Hind — rotor radius 8.65 m, 5 blades, mass 10500 kg, power 3240 kW Unknown helicopters get auto-generated profiles from rotor radius and RPM. KEY AERODYNAMIC EFFECTS Ground Effect lift when hovering near ground (< 2× rotor radius). Formula: classic induced velocity reduction. Boost: UH-1H ~30%, Mi-8MT ~40%, Mi-24 ~35%. Fades with forward speed. Translational Lift (ETL) rotor efficiency during forward flight. Starts ~2 m/s, peaks 18–25 m/s, persists higher. Boost: UH-1H ~20%, Mi-8MT ~25%, Mi-24 ~30% (wing lift). Vortex Ring State (VRS) Severe lift loss during fast vertical descent at low horizontal speed. Triggers: descent >5 m/s AND forward speed <8 m/s. Loss: up to 40%. Exit: accelerate forward >8–10 m/s. Settling with Power Power-required increase when descending into own downwash. Losses: light descent ~minimal, medium ~35%, heavy → transitions to VRS (~50% loss). Retreating Blade Stall (RBS) Max forward speed limit. Retreating blade loses lift at high speed. Onset: ~70–80 m/s depending on helicopter. Density Altitude Thrust loss at higher altitude due to lower air density. ~15% drop at 3000 m (ISA model). MOMENTUM THEORY Induced velocity: √(Thrust / (2 × ρ × disk area)) in hover; decreases in forward flight. Thrust coefficient: dimensionless thrust metric. Inflow ratio: vertical flow / tip speed. POWER MODEL Required power = induced + profile + parasite. Power margin: % of available engine power remaining. <10% margin → underpower warning. FLAPPING DYNAMICS Co...