Re- controlling the prop torque-
- The closest example we have for inference is perhaps the AH-56 Cheyenne – I understand it did pretty well and had achieved a dash speed of around 210 Kts during flight testing. Of course, it did have wings with asymmetric incidence angles – perhaps to offset the prop torque?
- So then, given the fact that the Cheyenne (a single rotor configuration) managed the prop torque (with a bit of help from its wings), there’s perhaps little reason why the X-2 with two rigid rotors (and far superior control power) can’t manage it.
- The Cheyenne had a collective mounted twist grip to control its prop pitch – the pilot could dial in the required prop pitch angle and haul up on the collective – that’s quite the dream solution for a pilot to accelerate an attack helicopter!!
- However, I understand it also incorporated an automatic system to reduce prop pitch, so as to prevent main rotor RPM decay, in the event of engine failure – I’m sure the X-2 will be having something similar...
- So then - just a question from a simple dim-bulb test pilot -
-what's the fuss all about?