scholarly journals Flow Control on Helicopter-Rotor Blades Via Active Gurney Flap

2018 ◽  
Vol 2018 (1) ◽  
pp. 98-118
Author(s):  
Wieńczysław Stalewski
Keyword(s):  
Three Dimensional ◽  
Lower Surface ◽  
Point Of View ◽  
Rotor Blades ◽  
Helicopter Rotor ◽  
Cfd Simulations ◽  
Helicopter Rotor Blades ◽  
Gurney Flap ◽  
Rotorcraft Performance

Abstract The Active Gurney Flap (AGF) is a small, flat tab cyclically deployed and retracted at lower surface of the rotor blade near its trailing edge. It is expected that the device may improve performance of modern helicopters. The main goal of presented investigations was to develop research methodology and next to use it in studies on phenomena occurring in the flow around helicopter-rotor blades equipped with AGF. Conducted CFD simulations aimed at validation of the developed methodology as well as at significant supplementing and extension of results of experimental research. Simplified sensitivity analysis has been conducted aiming at determination of geometric and motion-control parameters of the AGF, optimal from point of view of helicopter-performance improvement. Fully three-dimensional simulations of the rotor flight aimed at determination of flight conditions, in which the use of Active Gurney Flaps could significantly improve the rotorcraft performance.

Determination of the principal directions of composite helicopter rotor blades with arbitrary cross sections

2000 ◽  
Vol 14 (3) ◽  
pp. 291-297
Author(s):  
Taek-Yul Oh ◽  
Myung-Jin Choi ◽  
Yong-Seok Yu ◽  
Kyung-Duck Chae
Keyword(s):  
Cross Sections ◽  
Rotor Blades ◽  
Helicopter Rotor ◽  
Helicopter Rotor Blades ◽  
Principal Directions

scholarly journals Quieter and Greener rotorcraft: concurrent aerodynamic and acoustic optimization

2021 ◽  
Author(s):  
Gunther Wilke
Keyword(s):  
Pareto Front ◽  
Goal Function ◽  
Rotor Blades ◽  
Helicopter Rotor ◽  
Pareto Optimal ◽  
Cfd Simulations ◽  
Pareto Optimal Set ◽  
Trade Offs ◽  
Helicopter Rotor Blades ◽  
Optimal Set

AbstractWithin the DLR project VicToria an aerodynamic and aero-acoustic optimization of helicopter rotor blades is performed. During the optimization, three independent flight conditions are considered: hover, cruise and descent flight. The first two flight conditions drive the power requirements of the helicopter rotor, while the descent flight is the loudest flight condition for current helicopter generations. To drive down the required power and the emitted noise, a multi-objective design approach coupled with surrogate models is utilized to find a Pareto optimal set of rotors. This approach allows to identify the trade-offs to be made when laying emphasis on either goal function. The underlying CFD simulations utilize fourth-order accurate spatial schemes to capture the vortex dominated flow of helicopter rotor blades. The paper presents the validation of the setups, the optimization results and the off-design analysis of a chosen set of blades from the Pareto front. The conclusion is that the utilization of the Pareto front approach is necessary to find good rotor designs, while the utilization of high-order methods allows for efficient CFD setups.

Determination of Load Distributions on Main Helicopter Rotor Blades and Strength Analysis of Its Structural Components

2014 ◽  
Vol 27 (6) ◽  
pp. 04014032 ◽  
Author(s):  
S. Maksimovic ◽  
M. Kozic ◽  
S. Stetic-Kozic ◽  
K. Maksimović ◽  
I. Vasović ◽  
...  
Keyword(s):  
Rotor Blades ◽  
Helicopter Rotor ◽  
Strength Analysis ◽  
Structural Components ◽  
Load Distributions ◽  
Helicopter Rotor Blades

Circulation Control Span-Wise Blowing Location Optimization for a Helicopter Rotor Blade

2010 ◽  
Author(s):  
Alan M. Didion ◽  
Jonathan Kweder ◽  
Mary Ann Clarke ◽  
James E. Smith
Keyword(s):  
Stress Reduction ◽  
Rotor Blades ◽  
Helicopter Rotor ◽  
Base Line ◽  
Control Technology ◽  
Circulation Control ◽  
High Lift ◽  
Location Optimization ◽  
Helicopter Rotor Blades ◽  
Length Reduction

Circulation control technology has proven itself useful in the area of short take-off and landing (STOL) fixed wing aircraft by decreasing landing and takeoff distances, increasing maneuverability and lift at lower speeds. The application of circulation control technology to vertical take-off and landing (VTOL) rotorcraft could also prove quite beneficial. Successful adaptation to helicopter rotor blades is currently believed to yield benefits such as increased lift, increased payload capacity, increased maneuverability, reduction in rotor diameter and a reduction in noise. Above all, the addition of circulation control to rotorcraft as controlled by an on-board computer could provide the helicopter with pitch control as well as compensate for asymmetrical lift profiles from forward flight without need for a swashplate. There are an infinite number of blowing slot configurations, each with separate benefits and drawbacks. This study has identified three specific types of these configurations. The high lift configuration would be beneficial in instances where such power is needed for crew and cargo, little stress reduction is offered over the base line configuration. The stress reduction configuration on the other hand, however, offers little extra lift but much in the way of increased rotor lifespan and shorter rotor length. Finally, the middle balanced configuration offers a middle ground between the two extremes. With this configuration, the helicopter benefits in all categories of lift, stress reduction and blade length reduction.

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