A performance study was made of the application of a jet-flap to a reaction-drive rotor for a heavy-lift helicopter mission and for a high-speed-helicopter maneuverability (200 knots, 2g) mission. The results of the study are as follows: As a result of the increase in maximum airfoil lift coefficient achieved by the jet-flap, rotoed with the jet-flap to approximately 59% of a nonjet-flap rotor. As a result of the saving in rotor solidity, and hence in rotor weight, the jet-flap configuration had a 21% higher productivity than a nonjet-flap configuration. Of the three propulsion systems studied utilizing a jet-flap (hot cycle, warm cycle, cold cycle) the hot cycle gave the largest increase in productivity. The 200 knot 2g mission is performed best with a warm cycle propulsion system. The jet-flap permits designing for a rotor blade loading coefficient C sub T/sigma = .170 at 2g without encountering blade stall. The jet-flap rotor permits a 200 knot 2g maneuver without suffering the penalty of an unreasonable rotor solidity that would be required by a nonjet-flap rotor. (Author)
A Performance Application Study of a Jet-Flap Helicopter Rotor
1972
96 pages
Report
No indication
English
Aircraft , Helicopters , High speed , Jet flaps , Rotor lift , Lift , Maneuverability , Mechanical drives , Rotor speed
Smart Flap for Helicopter Rotor Blade Performance Improvement
British Library Conference Proceedings | 1993
|Study of jet propelled helicopter rotor with jet flap
Engineering Index Backfile | 1961
|Improvement of Servo-Flap Rotor Design Parameters for Helicopter Performance
British Library Conference Proceedings | 2011
|