Add to ORKGAn investigation was conducted in the Langley Transonic Dynamics Tunnel to obtain data to permit evaluation of paddle-type tip technology for possible use in future U.S. advanced rotor designs. Data was obtained for both a baseline main-rotor blade and a main-rotor blade with a paddle-type tip. The baseline and paddle-type tip blades were compared with regard to rotor performance, oscillatory pitch-link loads, and 4-per-rev vertical fixed-system loads. Data was obtained in hover and forward flight over a nominal range of advance ratios from 0.15 to 0.425. Results indicate that the paddle-type tip offers no performance improvements in either hover or forward flight. Pitch-link oscillatory loads for the paddle-type tip are higher than for the...
Data for rotors using unconventional airfoils are of interest to permit an evaluation of this techno...
Pressure data at 90 percent blade radius were obtained for a helicopter main rotor with 10-64C blade...
Hovering characteristics of rotor having airfoil section designed for utility type helicopte
this report as a "BERP-type" blade. The intent of using these two blade sets was to evalua...
An investigation was conducted in the Langley Transonic Dynamics Tunnel to evaluate differences betw...
Wind-tunnel tests of an aeroelastically designed helicopter rotor model were carried out to determin...
Six interchangeable tip shapes were tested: a square (baseline) tip, an ogee tip, a subwing tip, a s...
A flight investigation produced data on performance and rotor loads for a teetering rotor, AH-1G hel...
An investigation was conducted in the NASA Langley Transonic Dynamics Tunnel to evaluate an advanced...
The Langley transonic dynamics tunnel was used to determine the degree of correlation between rotor ...
A passive means of tailoring helicopter rotor blades to improve performance and reduce loads was eva...
A rotor configuration called the free-tip rotor was analytically investigated for its potential to i...
Two rotor systems for the UH-1 helicopter were tested in hover and forward flight. The baseline syst...
The test envelope included hover, forward-flight speed sweeps from 33 to 74 m/sec (65 to 144 knots),...
Performance of a 27 percent scale model rotor designed for the AH-64 helicopter (alternate rotor) wa...
Data for rotors using unconventional airfoils are of interest to permit an evaluation of this techno...
Pressure data at 90 percent blade radius were obtained for a helicopter main rotor with 10-64C blade...
Hovering characteristics of rotor having airfoil section designed for utility type helicopte
this report as a "BERP-type" blade. The intent of using these two blade sets was to evalua...
An investigation was conducted in the Langley Transonic Dynamics Tunnel to evaluate differences betw...
Wind-tunnel tests of an aeroelastically designed helicopter rotor model were carried out to determin...
Six interchangeable tip shapes were tested: a square (baseline) tip, an ogee tip, a subwing tip, a s...
A flight investigation produced data on performance and rotor loads for a teetering rotor, AH-1G hel...
An investigation was conducted in the NASA Langley Transonic Dynamics Tunnel to evaluate an advanced...
The Langley transonic dynamics tunnel was used to determine the degree of correlation between rotor ...
A passive means of tailoring helicopter rotor blades to improve performance and reduce loads was eva...
A rotor configuration called the free-tip rotor was analytically investigated for its potential to i...
Two rotor systems for the UH-1 helicopter were tested in hover and forward flight. The baseline syst...
The test envelope included hover, forward-flight speed sweeps from 33 to 74 m/sec (65 to 144 knots),...
Performance of a 27 percent scale model rotor designed for the AH-64 helicopter (alternate rotor) wa...
Data for rotors using unconventional airfoils are of interest to permit an evaluation of this techno...
Pressure data at 90 percent blade radius were obtained for a helicopter main rotor with 10-64C blade...
Hovering characteristics of rotor having airfoil section designed for utility type helicopte