An Overview of Active Flow Control Enhanced Vertical Tail Technology Development

Lin, John C.; Andino, Marlyn Y.; Alexander, Michael G.; Whalen, Edward A.; Spoor, Marc; Tran, John; Wygnanski, I.

doi:10.2514/6.2016-0056

Cited by 63 publications

(35 citation statements)

References 12 publications

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“…Andino et al 22 and Lin et al discussed actuator spacing results and reported that the trends are based on momentum coefficient. Lin et al 24 also discussed flight testing with AFC on the Boeing 757 ecoDemonstrator where the results indicated flow reattachment over the rudder and a smoother flight.…”

Section: Introductionmentioning

confidence: 95%

“…Their work included cases at flight Reynolds numbers. Full-scale experiments at flight Reynolds numbers were carried out by Andino et al 22 , Whalen et al 23 , and Lin et al 24 on a Boeing 757 vertical tail retrofit with sweeping jets. Results showed that the performance enhancement seen on subscale models exists on full-scale tails and that active flow control is a viable option for future aerospace usage.…”

Section: Introductionmentioning

confidence: 99%

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Performance Enhancement of an Airfoil Model with a Control Surface using Synthetic Jets

Monastero

Amitay

2016

8th AIAA Flow Control Conference

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Synthetic-jet-based active flow control for separation control over a vertical tail is an ongoing area of research, the goal of which is reducing the size of the vertical tail on commercial airplanes. Before placing the actuators on an airplane, a detailed understanding of the effect different jets and test parameters have on side force enhancement must be obtained. Previous work investigated the performance enhancement of 1/19 th scale and 1/9 th scale vertical tail models and showed that the side force could be augmented by as much as 34%. The authors found an unexpected relationship between jet spacing (and number of jets) and side force enhancement that did not agree between the two models, where, under specific conditions, increasing the spacing between actuators increased the side force on the larger 1/9 th scale model while decreasing it on the smaller 1/19 th scale model. To further understand the interactions among jets as spacing varied, a new model was designed and tested in the Rensselaer Polytechnic Institute (RPI) Subsonic Wind Tunnel. The model was designed such that it is capable of varying sweep angle, rudder characteristics (chord length and deflection), and various actuator parameters. The experiments discussed in this paper focus on the unswept case with the rudder at a moderate deflection angle of 20 o and the sensitivity of the side force produced by the unswept model to different parameters. The flow field around the new model was first characterized using particle image velocimetry and pressure measurements. The effect of synthetic jet flow control was found to significantly modify the pressure distribution globally around the model, which resulted in up to 17% improvement in the side force. The effect of sideslip angle and jet spacing were also studied and found to agree with the trends observed in previous work. The work discussed here is the foundation for continuing tests on a swept configuration of the model. These future tests will study how the addition of spanwise flow and variations in separation severity affect the performance trends as spacing is varied. Nomenclature= area-based momentum coefficient produced by a single jet c = total chord c r = rudder chord F + = non-dimensional actuation frequency n = number of active jets in the array Re c = chord-based Reynolds number S = model planform area

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Section: Introductionmentioning

confidence: 95%

Section: Introductionmentioning

confidence: 99%

Performance Enhancement of an Airfoil Model with a Control Surface using Synthetic Jets

Monastero

Amitay

2016

8th AIAA Flow Control Conference

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“…The first drag reduction technology employed an array of pneumatic-based AFC devices called the sweeping jet actuators 5 (Figure 1) on the vertical tail of the Boeing 757 for side force enhancement (Figure 2). 6 These devices were of the same geometry and configuration that was successfully tested on a full-scale Boeing 757 vertical tail model in NASA Ames' National Full-Scale Aerodynamics Complex (NFAC) 40'x80' wind tunnel. 7,8 A NASA sponsored system integration study on a mid-sized twin aisle airplane indicated using AFC would allow designers to scale-down the vertical tail of a mid-sized twin aisle airplane and reduce aircraft drag by 0.4%, which would reduce fuel burn.…”

mentioning

confidence: 99%

Active Flow Control (AFC) and Insect Accretion and Mitigation (IAM) System Design and Integration on the Boeing 757 ecoDemonstrator

Alexander

Harris

Spoor

et al. 2016

16th AIAA Aviation Technology, Integration, and Operations Conference

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This paper presents a systems overview of how the Boeing and NASA team designed, analyzed, fabricated, and integrated the Active Flow Control (AFC) technology and Insect AccretionMitigation (IAM) systems on the Boeing 757 ecoDemonstrator. The NASA Environmentally Responsible Aviation (ERA) project partnered with Boeing to demonstrate these two technology systems on a specially outfitted Boeing 757 ecoDemonstrator during the spring of 2015. The AFC system demonstrated attenuation of flow separation on a highly deflected rudder and increased the side force generated. This AFC system may enable a smaller vertical tail to provide the control authority needed in the event of an engine failure during takeoff while still operating in a conventional manner over the rest of the flight envelope. The AFC system consisted of ducting to obtain air from the Auxiliary Power Unit (APU), a control valve to modulate the system mass flow, a heat exchanger to lower the APU air temperature, and additional ducting to deliver the air to the AFC actuators located on the vertical tail. The IAM system demonstrated how to mitigate insect residue adhesion on a wing's leading edge. Something as small as insect residue on a leading edge can cause turbulent wedges that interrupt laminar flow, resulting in an increase in drag and fuel use. The IAM system consisted of NASA developed Engineered Surfaces (ES) which were thin aluminum sheet substrate panels with coatings applied to the exterior. These ES were installed on slats 8 and 9 on the right wing of the 757 ecoDemonstrator. They were designed to support panel removal and installation in one crew shift. Each slat accommodated 4 panels. Both the AFC and IAM flight test were the culmination of several years of development and produced valuable data for the advancement of modern aircraft designs.

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“…The most obvious possibility, therefore, is to supply the HLAFC system with bleed air coming from either the main engines, or the APU, or both. In fact, recent flight test demonstrations that showcased AFC applied to the vertical tail used APU bleed air to supply the AFC actuators [6,7].…”

Section: Hlafc Architectures Consideredmentioning

confidence: 99%

“…The fundamental principle of AFC is to improve aircraft performance by modifying the airflow surrounding the vehicle through the addition of an acceptable amount of flow energy. Recent work in this field has included theoretical studies [1][2][3], experimental research [4,5], and some flight-test demonstrations [6,7].…”

Section: Introductionmentioning

confidence: 99%

Parametric Approach to Assessing Performance of High-Lift Device Active Flow Control Architectures

et al. 2017

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Active Flow Control is at present an area of considerable research, with multiple potential aircraft applications. While the majority of research has focused on the performance of the actuators themselves, a system-level perspective is necessary to assess the viability of proposed solutions. This paper demonstrates such an approach, in which major system components are sized based on system flow and redundancy considerations, with the impacts linked directly to the mission performance of the aircraft. Considering the case of a large twin-aisle aircraft, four distinct active flow control architectures that facilitate the simplification of the high-lift mechanism are investigated using the demonstrated approach. The analysis indicates a very strong influence of system total mass flow requirement on architecture performance, both for a typical mission and also over the entire payload-range envelope of the aircraft.

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An Overview of Active Flow Control Enhanced Vertical Tail Technology Development

Cited by 63 publications

References 12 publications

Performance Enhancement of an Airfoil Model with a Control Surface using Synthetic Jets

Performance Enhancement of an Airfoil Model with a Control Surface using Synthetic Jets

Active Flow Control (AFC) and Insect Accretion and Mitigation (IAM) System Design and Integration on the Boeing 757 ecoDemonstrator

Parametric Approach to Assessing Performance of High-Lift Device Active Flow Control Architectures

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