Design of a Droopnose Configuration for a Coanda Active Flap Application

Burnazzi, Marco; Radespiel, Rolf

doi:10.2514/6.2013-487

Cited by 23 publications

(15 citation statements)

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“…Therefore, the design was updated (REF2-2013 ), leading to a larger vertical and horizontal tail plane. Furthermore, the wing is now equipped with a smart droopnose 17,18 to prevent an early leading edge stall. Table 1 depicts some of the aerodynamic parameters of the latest version of the aircraft.…”

Section: Test Configurationmentioning

confidence: 99%

Numerical Investigation of the Dynamic Behavior of a High-Lift Configuration with Circulation Control

Keller

Rudnik

2015

33rd AIAA Applied Aerodynamics Conference

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The scope of this paper is to demonstrate the feasibility of a numerical evaluation of dynamic derivatives of a 3D high-lift configuration. Furthermore, the influence of active lift augmentation systems on the longitudinal dynamic derivatives shall be illustrated. Therefore, forced pitching and plunging motions at different boundary conditions were simulated. The investigation started with a comprehensive sensitivity study regarding algorithmic and configurational parameters on a representative 2D-model. The results show the impact of frequency, amplitude, flap deflection and blowing coefficient. Based on the preliminary 2D study, boundary conditions were selected for the simulation of the entire aircraft in landing configuration. The dynamic derivatives were successfully evaluated based on the linearization method. Neither thrust, nor blowing showed significant impact on the longitudinal dynamic derivatives.

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Section: Test Configurationmentioning

confidence: 99%

Numerical Investigation of the Dynamic Behavior of a High-Lift Configuration with Circulation Control

Keller

Rudnik

2015

33rd AIAA Applied Aerodynamics Conference

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“…This non-dimensional height was also used for a recent circulation control application with a deflected plain flap of a high wing aircraft which was found to lead to good results in terms of efficiency of the flow control system. 1 The slot length corresponds to 20 · h slot and is chosen so that the flow can develop a boundary layer profile before leaving the slot with its viscous walls. Behind the slot a small step exists which can be found in reality, too.…”

Section: Geometry Setupmentioning

confidence: 99%

Numerical Investigation of Tangential Blowing at the Rudder of a Vertical Tailplane Airfoil

Kröhnert

2014

32nd AIAA Applied Aerodynamics Conference

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A numerical 2D investigation of a vertical tailplane airfoil using active flow control with tangential blowing over the rudder shoulder is conducted. The intention of the flow control application is to increase the maximum lift or side force which can be created by the vertical tailplane at critical conditions like the one-engine-inoperative failure case. On the highly deflected rudder a large separation can be found without blowing. With tangential blowing it is shown that fully attached flow can be achieved. The flow simulations performed are based on the Reynolds-averaged Navier-Stokes equations. The parameters momentum coefficient, slot height and angle of attack of the oncoming flow are varied to assess sensitivities and the influence on the results. Furthermore, the influence of a geometric detail in the vicinity of the slot exit is investigated, namely the existence or omission of a step behind the slot exit. Finally, the influence of the turbulence model is studied where besides the Spalart and Allmaras turbulence model with rotational and curvature correction (SARC) also the SAO and RSM turbulence models are applied. NomenclatureAFC Active Flow Control DLR Deutsches Zentrum für Luft-und Raumfahrt (German Aerospace Center) OEI One-engine-inoperative RANS Reynolds-averaged Navier-Stokes [equations] RSM Reynolds stress model SAO Spalart and Allmaras turbulence model, original version SARC Spalart and Allmaras turbulence model with vortical and rotational flow correction VTP Vertical tailplane 2D Two dimensional 3D Three dimensional A ref Reference area [m 2 ] A j Area of the slot orifice [m 2 ] b Span [m] c Chord length [m] C d Drag coefficient [-] C l Lift coefficient [-]

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“…Afterwards, wind-tunnel experiments on a 2D airfoil with porous trailing edge were conducted to further validate the numerical model. 25 This numerical model is now being used to study a number of test cases where a porous trailing edge is implemented on the modified DLR F15 airfoil with droop nose and Coanda blowing 30,31 with an aim to identify a porous material with acceptable losses in lift while maintaining promising material properties for noise reduction. A number of configurations with different momentum coefficients C µ of the Coanda blowing are being considered at this time to vary the amount of flow separation.…”

Section: Aerodynamic Assessment Of Porous Materials (Sub Project B5)mentioning

confidence: 99%

Aircraft and technology for low noise short take-off and landing

Delfs

Appel

Bernicke

et al. 2017

35th AIAA Applied Aerodynamics Conference

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This paper discusses characteristic multidisciplinary issues related to quiet short takeoff and landing for civil transport aircraft with a typical short to medium range mission. The work reported here is focussing on the noise aspects and is embedded in the collaborative research centre CRC880 in Braunschweig, Germany. This long term aircraft research initiative focusses on a new transport aircraft segment for operation on airports with shorter runway length in commercial air transport. This calls for a community-friendly aircraft designed for operations much closer to the home of its passengers than today. This scenario sets challenging, seemingly contradictory aircraft technology requirements, namely those for extreme lift augmentation at low noise. The Research Centre CRC880 has therefore devised a range of technology projects that aim at significant noise reductions and at the generation of efficient and flexible high lift. The research also addresses flight dynamics of aircraft at takeoff and landing. Two companion papers, reporting about the research in the field of "Efficient high lift" 1 and "Flight dynamics" 2 complete the presentation of the CRC880. It is envisaged that in general significant noise reduction-compared to a reference turbofan driven aircraft of year 2000 technology-necessarily requires component noise reduction in combination with a low noise a/c concept. Results are presented from all the acoustics related projects of CRC880 which cover the aeroacoustic simulation of the source noise reduction by flow permeable materials, the characterization, development, manufacturing and operation of (porous) materials especially tailored to aeroacoustics, new UHBR turbofan arrangements for minimum exterior noise due to acoustic shielding as well as the prediction of jet noise vibration excitation of cabin noise by UHBR engines compared to conventional turbofans at cruise.

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Design of a Droopnose Configuration for a Coanda Active Flap Application

Cited by 23 publications

References 1 publication

Numerical Investigation of the Dynamic Behavior of a High-Lift Configuration with Circulation Control

Numerical Investigation of the Dynamic Behavior of a High-Lift Configuration with Circulation Control

Numerical Investigation of Tangential Blowing at the Rudder of a Vertical Tailplane Airfoil

Aircraft and technology for low noise short take-off and landing

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