Progress in Efficient Active High-Lift

Kauth, Felix; Narjes, Gerrit; Müller, J.; Seume, Joerg R.; Vasista, Srinivas; Müller, T. S.; François, Daniela G.; Sayed, Yosef El; Semaan, Richard; Behr, Christian; Schwerter, Martin; Leester-Schädel, Monika; Nolte, Felix; Giesecke, Daniel; Atalayer, Çağlar; Radespiel, Rolf

doi:10.2514/6.2017-3559

Cited by 10 publications

(6 citation statements)

References 19 publications

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“…Therefore, the SFB 880 gathers all relevant research fields to efficient clusters. In other contributions to this conference overviews of the "aerodynamics", "aeroacoustics" and "flight dynamics" clusters will be presented as well [3][4][5]. A configuration for a turbo-propeller powered aircraft equipped with a micro-compressor blown flap system has been designed combining circulation control with deflected propeller slipstream effects, depicted in Figure 1 with the basic aircraft data given in Table 1.…”

Section: Introductionmentioning

confidence: 99%

Flight Mechanical Challenges of STOL Aircraft Using Active High Lift

Diekmann¹

2019

Journal of Aircraft

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This paper focuses on the flight mechanical characteristics of an active high-lift supported transport type aircraft. The presented configuration combines a boundary-layer controlled flaps system with the benefits of propeller slipstream deflection. The underlying aerodynamic models and assumptions are provided. The extraordinary flight performances especially at low airspeed will be pointed out, as well as potential weaknesses. Special attention is paid to the unusually strong aerodynamic couplings in the lateral motion. Therefore, flight dynamics characteristics will be presented and their challenges discussed. The key influences are pointed out and an outlook will be given, how to exploit this knowledge for safe and satisfactory aircraft operation and handling.

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Section: Introductionmentioning

confidence: 99%

Flight Mechanical Challenges of STOL Aircraft Using Active High Lift

Diekmann¹

2019

Journal of Aircraft

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“…Recent aircraft studies have focused on both aerodynamic improvements and environmental aspects (Delfs et al 2017;Kauth et al 2017;Diekmann 2019;Lin et al 2019;Wild 2020).…”

Section: Overviewmentioning

confidence: 99%

Numerical Study of Flow Control on Simplified High-Lift Configurations

2023

JAFM

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Enhancement in the aerodynamic performance of wings and airfoils is very notable when Active Flow Control (AFC) is applied to Short Take-off and Landing aircraft (STOL). The present numerical study shows the application of steady, pulsed and synthetic tangential jets applied to the plain flap shoulder of a modified NASA Trapezoidal Wing. Pulsed jets are modeled by sinusoidal and square waveforms while synthetic jets are modeled only by pure sine waveform. The freestream airflow conditions are Mach number equal to 0.2 and Reynolds number equal to 4.3 million based on the mean aerodynamic chord. The presented simulations are two-dimensional and based on RANS for steady jet cases and URANS for pulsed and synthetic cases, compiled with the open-source suite SU2 and adapted for time varying boundary conditions. Numerical results for modified configurations based on the same baseline wing profile considering different leading edges, jet slot height, flap position, blowing mass flow, type and frequency of the jets are presented. Curves of pressure coefficient distribution revealed a substantial influence upstream of the AFC, around the slat and main element. The jet slot height analysis showed that the lift gain is also influenced by the slot size due to the change of the local flow velocity considering the same blowing momentum coefficient. Regarding the jet frequency, no significant differences on the lift coefficients were found between the reduced frequencies F+ equal to 1 and 2. Results of aerodynamic loads showed an improved lift coefficient in relation to the baseline airfoil when pulsed and steady jets are employed. Pulsed jets under square waveform were effective even at high deflected flap condition at 50°, with a significant gain in the lift coefficient of 36%, in relation to the uncontrolled case, combined with a drag reduction of 20%, and a decrease in mass flow up to 49% in relation to the steady jet for the same lift gain. Although sine and square waveform results presented similar improvements for lift, the drag is around 15% higher for the former. When compared with the steady jet case, the mass flow reduction is 36% for the sinewave. Synthetic jets with zero-net-mass-flux proved superior to the baseline conventional multi-element airfoil only with deployed flap at 50°, where a modest lift improvement of 5% was observed.

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“…An essential feature of the reference aircraft is its active high-lift system, which comprises a flexible wing leading-edge device ('droop nose') [5], and a combination of boundary layer suction on the airfoil and Coanda jet blowing at the flap [6]. The required mass flow of pressurized air is provided by six electrically driven compressors, which are distributed along each wing of the aircraft [7,8]. This concept of a wing-integrated electrically powered high-lift system (EPHLS) is shown in Figure 2 [9].…”

Section: Max Take-off Mass 42178 Kgmentioning

confidence: 99%

“…Inverter design for EPHLS and efficiency calculation. (a) reference inverter design with 100 kW[8]; (b) inverter efficiency for the six advanced high-lift systems and different switching frequencies from 10 up to 60 kHz.…”

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confidence: 99%

Design Considerations for the Electrical Power Supply of Future Civil Aircraft with Active High-Lift Systems

Mueller

Bensmann

et al. 2018

Energies

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Active high-lift systems of future civil aircraft allow noise reduction and the use of shorter runways. Powering high-lift systems electrically have a strong impact on the design requirements for the electrical power supply of the aircraft. The active high-lift system of the reference aircraft design considered in this paper consists of a flexible leading-edge device together with a combination of boundary-layer suction and Coanda-jet blowing. Electrically driven compressors distributed along the aircraft wings provide the required mass flow of pressurized air. Their additional loads significantly increase the electric power demand during takeoff and landing, which is commonly provided by electric generators attached to the aircraft engines. The focus of the present study is a feasibility assessment of alternative electric power supply concepts to unburden or eliminate the generator coupled to the aircraft engine. For this purpose, two different concepts using either fuel cells or batteries are outlined and evaluated in terms of weight, efficiency, and technology availability. The most promising, but least developed alternative to the engine-powered electric generator is the usage of fuel cells. The advantages are high power density and short refueling time, compared to the battery storage concept.

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Progress in Efficient Active High-Lift

Cited by 10 publications

References 19 publications

Flight Mechanical Challenges of STOL Aircraft Using Active High Lift

Flight Mechanical Challenges of STOL Aircraft Using Active High Lift

Numerical Study of Flow Control on Simplified High-Lift Configurations

Design Considerations for the Electrical Power Supply of Future Civil Aircraft with Active High-Lift Systems

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