Rotors de-icing power question
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Rotors de-icing power question
While reading Mil Mi-8 tech docs I surprisingly saw that its TR de-icing system consumes way more electric power than MR one. To be exact it is 38 kW for a TR and only 26 kW for a MR. What could be the reason(s) that to de-ice times smaller surfaces needs much more power?
While reading Mil Mi-8 tech docs I surprisingly saw that its TR de-icing system consumes way more electric power than MR one. To be exact it is 38 kW for a TR and only 26 kW for a MR. What could be the reason(s) that to de-ice times smaller surfaces needs much more power?
Just a thought.
Are you sure? That was my initial thought too but then I did some searching and found this which indicates both rotors are de-ice. https://forums.eagle.ru/attachment.p...6&d=1447323413
of course, it may not be correct
of course, it may not be correct
Last edited by 212man; 10th Mar 2019 at 11:50.
Perhaps the m/r is better able to handle a bit of assymetric weight than the much more delicate t/r, requiring that to be deiced all at once rather than in sections?
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I'd suposed that probable reason is that TR is more prone to efficiency loss just because it has smaller chord and therefore same ice thickness ruins its aerodynamics faster than it does for bigger MR chord. Just inspired by a comparison between any MR chord and fixed wing chord.
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The enigma revealed! Found an old manual on Mi-8 equipment where it is clearly written: Ampermeter will show 160 A for TR current but in fact real current is 8 times less, i.e. 20-24 A. They just wanted to use one ampermeter for two very different levels of current in the simpliest way. Thanks to all replying!
