TRANSPIRE DYNAMICS · FLIGHT DYNAMICS CONCEPT SERIES · PART III TILTROTOR · CONVERSION CORRIDOR · DUAL FLOWFIELD TRANSPIREDYNAMICS.COM

MV-75 Cheyenne II:
through the corridor

Part III flies a third-generation tiltrotor — two proprotors on tilting shafts, a wing that takes over as you push the nacelles forward, and a conversion corridor where both lift sources share the load. Watch the dual flowfield tilt from downwash columns to propwash streams as you transition from hover to 280 knots.

6-DOF RIGID BODY DUAL PROPROTOR CONVERSION CORRIDOR YOU CAN STILL CRASH
◂ Part II — UH-60 three-dimensional flight
SEC 01 · THE SIMULATOR

Tiltrotor: two worlds, one corridor

Below is a six-degree-of-freedom MV-75 Cheyenne II — a V-280 Valor class tiltrotor with counter-rotating proprotors, a high-mounted wing, and V-tail ruddervators. Tilt the proprotors from vertical (helicopter) to horizontal (airplane) and watch lift production transfer from rotors to wing. The conversion corridor defines where that handoff is safe. Cockpit units are U.S. standard: knots, feet, ft/min.

LEGAL DISCLAIMERThis is an independent educational demonstration by Transpire Dynamics LLC. It is not affiliated with, endorsed by, or derived from any controlled technical data of Bell, Textron, or the U.S. Department of Defense. All aerodynamic parameters are sourced from publicly available literature. Not for flight training or operational planning.
KEY DIFFERENCE FROM V-22The MV-75 has fixed nacelles — only the proprotor shafts and gearboxes tilt. The engines remain stationary in the wingtip nacelles at all times. This eliminates the nacelle-induced pitching moment during conversion and reduces tip mass compared to the V-22 Osprey.
MV-75 · 6-DOF · ρ = 0.00238 SLUG/FT³ (SL STD) · GW 30,000 LB
TRIM: P 0.0° / R 0.0°
Feedback v1.17.11

Disclaimer

This is an independent educational concept demonstrator by Transpire Dynamics LLC. It is not affiliated with, endorsed by, or certified by the U.S. Army, Sikorsky, Lockheed Martin, or the U.S. Department of Defense.

All aerodynamic parameters are derived from publicly available, open-domain literature. Models are physics-based and derived from first principles, but optimized for real-time computation and not intended for full engineering analysis. High-fidelity work requires dedicated offline simulation tools.

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ft
deg
COL 50%
CYC 0 / 0
PED 0
Phase demonstrations — press one, then watch the message bar ENGINES: ON — NR governed (ideal step)
FLIGHT PROFILE — 60 s ROLLING WINDOW
AIRSPEED (KIAS) 0
ALTITUDE (FT AGL) 0
CONTROLS COL 20%
LAT LON COL % PED NAC °
CUSTOM —