Development of circulation control technology for application to advanced subsonic transport aircraft

1993 ◽  
Author(s):  
ROBERT ENGLAR ◽  
MARILYN SMITH ◽  
SEAN KELLEY ◽  
RICHARD ROVER, III
Keyword(s):  
Control Technology ◽  
Circulation Control ◽  
Transport Aircraft

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.

Roll aerodynamic characteristics study of an unmanned aerial vehicle based on circulation control technology

2017 ◽  
Vol 233 (3) ◽  
pp. 871-882
Author(s):  
Kun Chen ◽  
Zhiwei Shi ◽  
Jiachen Zhu ◽  
Haiyang Wang ◽  
Junquan Fu
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Flight Control ◽  
Attitude Control ◽  
Aerodynamic Force ◽  
Flight Test ◽  
Scale Model ◽  
Maximum Efficiency ◽  
Control Technology ◽  
Circulation Control ◽  
Aerial Vehicle

To explore the control efficiency of circulation flow control technology, a circulation control actuator with an independent gas source has been designed and applied in roll attitude control of a small unmanned aerial vehicle. The circulation control devices are arranged at the two ends of the wing on an unmanned aerial vehicle scale model, the changes in aerodynamic force and aerodynamic moment caused by turning on the actuator are measured in a wind tunnel, and the flow field characteristics are analysed using particle image velocimetry technology. The flight control effect of the roll attitude is verified via a flight test. Experimental and flight test results show that the control of roll attitude can be achieved by turning on the circulation control actuator on one side, and the maximum efficiency that the circulation control generates is equivalent to 8° aileron deflection with production of a favorable yaw moment to achieve a coordinated turn. The circulation control actuator can increase lift and reduce drag when opened on both sides simultaneously. The maximum lift-to-drag ratio of the UAV increased from 5 to 9, and this approach can also suppress flow separation and delay stall at high angles of attack. The aileron or trailing edge flaps can be replaced with circulation control actuators, and the circulation control technology can also be applied to aerodynamic performance improvement and flight control in other types of aircraft.

Circulation Control Technology Applied to Propulsive High Lift Systems

1984 ◽  
Author(s):  
Robert J. Englar ◽  
James H. Nichols ◽  
Michael J. Harris ◽  
Joseph C. Eppel ◽  
Michael D. Shovlin
Keyword(s):  
Control Technology ◽  
Circulation Control ◽  
High Lift

Application of circulation control to advanced subsonic transport aircraft. Part II - Transport application

1994 ◽  
Vol 31 (5) ◽  
pp. 1169-1177 ◽  
Author(s):  
Robert J. Englar ◽  
Marilyn J. Smith ◽  
Sean M. Kelley ◽  
Richard C. Rover
Keyword(s):  
Circulation Control ◽  
Transport Aircraft

Application of Circulation Control to Advanced Subsonic Transport Aircraft, Part I - Airfoil Development

1994 ◽  
Vol 31 (5) ◽  
pp. 1160-1168 ◽  
Author(s):  
Robert J. Englar ◽  
Marilyn J. Smith ◽  
Sean M. Kelley ◽  
Richard C. Rover
Keyword(s):  
Circulation Control ◽  
Transport Aircraft

Design and cost analysis of integration of fluidic oscillator into a flap structure

2017 ◽  
Vol 232 (16) ◽  
pp. 2978-2988 ◽  
Author(s):  
J Li ◽  
J Colton
Keyword(s):  
Flow Control ◽  
Active Flow Control ◽  
Leading Edge ◽  
Control Technology ◽  
Fluidic Oscillator ◽  
Transport Aircraft ◽  
High Production ◽  
Manufacturing Assembly ◽  
The Cost ◽  
Active Flow

Integration of active flow control technology into civil transport aircraft is a highly desired objective due to the potential reductions in part count, weight, and recurring manufacturing costs. This study develops an optimal design for integrating a fluidic oscillator into the leading-edge of a trailing-edge flap structure on a civil transport aircraft. The design incorporates design specifications set by members of the aerospace industry, robust design methodologies, and simulation studies to create three separate designs that can be mass-produced. An analysis of the manufacturing, assembly, material, and weight reveals the cost of the design with respect to its production rate, which ranges from about $4090 per aircraft for low-production volumes to about $2600 per aircraft for high-production volumes. As a result, this study provides a basis for the design of manufacturing and assembly techniques to integrate active flow control technology into civil transport aircraft.

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