Systems and certification issues for active flow control systems for seperation control on civil transport aircraft

2008 ◽  
Author(s):  
Stephen Liddle ◽  
William Crowther
Keyword(s):  
Flow Control ◽  
Control Systems ◽  
Active Flow Control ◽  
Transport Aircraft ◽  
Active Flow

scholarly journals Active Flow Control Systems Architectures for Civil Transport Aircraft

2010 ◽  
Vol 47 (6) ◽  
pp. 1966-1981 ◽  
Author(s):  
M. Jabbal ◽  
S. C. Liddle ◽  
W. J. Crowther
Keyword(s):  
Flow Control ◽  
Control Systems ◽  
Active Flow Control ◽  
Transport Aircraft ◽  
Systems Architectures ◽  
Active Flow

Techniques for the Design of Active Flow Control Systems in Heavy Vehicles

2015 ◽  
Author(s):  
David E. Manosalvas ◽  
Thomas D. Economon ◽  
Francisco Palacios ◽  
Antony Jameson
Keyword(s):  
Flow Control ◽  
Control Systems ◽  
Active Flow Control ◽  
Heavy Vehicles ◽  
Active Flow

Helicopter Fuselage Model Drag Reduction by Active Flow Control Systems

2019 ◽  
Vol 64 (2) ◽  
pp. 1-15 ◽  
Author(s):  
Fabrizio De Gregorio
Keyword(s):  
Experimental Investigation ◽  
Flow Control ◽  
Control Systems ◽  
Flow Separation ◽  
Laboratory Tests ◽  
Active Flow Control ◽  
Aerodynamic Characteristics ◽  
Pulsed Jets ◽  
Wide Range ◽  
Active Flow

A comprehensive experimental investigation of a helicopter blunt fuselage model was carried out to evaluate the effectiveness of active flow control (AFC) systems in reducing parasite fuselage drag. The main objective was to demonstrate the capability of different active technologies to decrease fuselage drag by alleviating the flow separation in the loading ramp region of large transport helicopters. The work was performed on a simplified blunt fuselage at model scale. Two different flow control actuators were considered for evaluation: steady blowing and unsteady blowing (i. e., pulsed jets). Laboratory tests of each individual actuator were performed to assess their performance and properties. The fuselage model was investigated with and without the AFC systems located along the loading ramp edges. Significant drag reductions were achieved for a wide range of fuselage angles of attack and sideslip angles without negatively affecting other aerodynamic characteristics.

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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