Add to ORKGA comprehensive rotorcraft analysis model was used to predict blade aerodynamic and structural loads for comparison with flight test data. The data were obtained from an SA349/2 helicopter with an advanced geometry rotor. Sensitivity of the correlation to wake geometry, blade dynamics, and blade aerodynamic effects was investigated. Blade chordwise pressure coefficients were predicted for the blade transonic regimes using the model coupled with two finite-difference codes
A passive means of tailoring helicopter rotor blades to improve performance and reduce loads was eva...
In 2018, a full-scale isolated proprotor test was conducted in the USAF National Full-Scale Aerodyna...
Using the quasi-steady, full potential code, ROT22, pressures were calculated on straight and swept ...
Airloads measured on a two-bladed helicopter rotor in flight during the Ames' Tip Aerodynamic and Ac...
A cooperative program was undertaken by research organizations in England, France, Australia and the...
Pressure data at 90 percent blade radius for a helicopter main rotor with RC-SC2 blade sections was ...
An investigation was conducted in the NASA Langley Transonic Dynamics Tunnel to evaluate an advanced...
Comparisons were made of the performance and blade vibratory loads characteristics for an advanced r...
Pressure data at 90 percent blade radius were obtained for a helicopter main rotor with 10-64C blade...
The forces and moments at the rotor hub of an Aerospatiale SA349/2 helicopter were investigated. The...
The test envelope included hover, forward-flight speed sweeps from 33 to 74 m/sec (65 to 144 knots),...
An investigation was conducted in the Langley Transonic Dynamics Tunnel to evaluate differences betw...
Data from 23 flight conditions, including level flights ranging from advance ratio mu = 0.14 to 0.37...
A flight investigation produced data on performance and rotor loads for a teetering rotor, AH-1G hel...
Two different schemes are presented for including the effect of rotor wakes on the finite-difference...
A passive means of tailoring helicopter rotor blades to improve performance and reduce loads was eva...
In 2018, a full-scale isolated proprotor test was conducted in the USAF National Full-Scale Aerodyna...
Using the quasi-steady, full potential code, ROT22, pressures were calculated on straight and swept ...
Airloads measured on a two-bladed helicopter rotor in flight during the Ames' Tip Aerodynamic and Ac...
A cooperative program was undertaken by research organizations in England, France, Australia and the...
Pressure data at 90 percent blade radius for a helicopter main rotor with RC-SC2 blade sections was ...
An investigation was conducted in the NASA Langley Transonic Dynamics Tunnel to evaluate an advanced...
Comparisons were made of the performance and blade vibratory loads characteristics for an advanced r...
Pressure data at 90 percent blade radius were obtained for a helicopter main rotor with 10-64C blade...
The forces and moments at the rotor hub of an Aerospatiale SA349/2 helicopter were investigated. The...
The test envelope included hover, forward-flight speed sweeps from 33 to 74 m/sec (65 to 144 knots),...
An investigation was conducted in the Langley Transonic Dynamics Tunnel to evaluate differences betw...
Data from 23 flight conditions, including level flights ranging from advance ratio mu = 0.14 to 0.37...
A flight investigation produced data on performance and rotor loads for a teetering rotor, AH-1G hel...
Two different schemes are presented for including the effect of rotor wakes on the finite-difference...
A passive means of tailoring helicopter rotor blades to improve performance and reduce loads was eva...
In 2018, a full-scale isolated proprotor test was conducted in the USAF National Full-Scale Aerodyna...
Using the quasi-steady, full potential code, ROT22, pressures were calculated on straight and swept ...