Improved Representation of High-Lift Devices for a Multidisciplinary Conceptual Aircraft Design Process

Werner-Spatz, Christian; Heinze, Wolfgang; Horst, Peter

doi:10.2514/1.42845

Cited by 16 publications

(11 citation statements)

References 12 publications

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“…To calculate the aerodynamic characteristics of the STOL aircraft, a multiple lifting line method with modeling of flap deflections in combination with twodimensional (2-D) Reynolds-averaged Navier-Stokes (RANS) airfoil data are used [20]. For the preliminary design in the first stage of the project, propeller slipstream effects are neglected for the calculation of the aerodynamic characteristics.…”

Section: Design Of the Reference Short Takeoff And Landing Aircraftmentioning

confidence: 99%

“…For the preliminary design in the first stage of the project, propeller slipstream effects are neglected for the calculation of the aerodynamic characteristics. The system aspects of an IBF approach are already included in PrADO by an aircraft system model from Koeppen [21], which has been supplemented by Werner-Spatz et al [20] to a pneumatic line for compressed air supply. This design module calculates the masses and c.g.…”

Section: Design Of the Reference Short Takeoff And Landing Aircraftmentioning

confidence: 99%

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Aerodynamic Installation Effects of an Over-the-Wing Propeller on a High-Lift Configuration

Müller¹,

Heinze²,

Kožulović³

et al. 2014

Journal of Aircraft

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Preliminary design studies indicate that a cruise-efficient short takeoff and landing aircraft has enhanced takeoff performance at competitive direct operating costs when using high-speed propellers in combination with internally blown flaps. The original tractor configuration is compared to an over-the-wing propeller, which allows for noise shielding. An additional geometry with partially embedded rotor similar to a channel wing is considered to increase the beneficial interaction. This paper shows the aerodynamic integration effects with a focus on climb performance and provides an assessment of the three aforementioned configurations for a simplified wing segment at takeoff conditions. Steady Reynolds-averaged Navier-Stokes simulations have been conducted using an actuator disk model and were evaluated based on the overall design. Interacting with the blown flap, the conventional tractor propeller induces large lift and drag increments due to the vectored sliptream. Although this effect is much smaller for an overthe-wing configuration, by halving the lift augmentation, the lift-to-drag ratio and the propulsive efficiency are considerably improved. Besides a moderate lift gain, the main advantage of a channel wing design is the location of the thrust vector close to the center of gravity resulting in a smaller nosedown pitching moment due to thrust. A disadvantage of over-the-wing propellers is the inhomogeneous inflow at higher velocity, which leads to oscillating blade loads and reduced efficiency.lift coefficient of aircraft C M;y = M y ∕q ∞ · S ref · MAC, pitching moment coefficient of aircraft C P;s = shaft power coefficient C T = 2 · T∕q ∞ · S ref , thrust coefficient of aircraft c = chord length of rectangular wing segment c d = section drag coefficient c l = section lift coefficient c m = section pitching moment coefficient c p = p − p ∞ ∕q ∞ , pressure coefficient D P = propeller diameter p = static pressure q ∞ = dynamic pressure of freestream S ref = wing area of reference aircraft s = semispan of rectangular wing segment T = thrust of one engine T inst = T − ΔD, installed thrust t∕t max = relative blade element thrust V ∞ = freestream velocity α = angle of attack α e = effective angle of attack at blade element β 75= propeller blade pitch angle (at 75% radius) η P = propeller efficiency η Pro = propulsive efficiency ρ ∞ = density of freestream Subscripts x,y,z = Cartesian coordinates

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Section: Design Of the Reference Short Takeoff And Landing Aircraftmentioning

confidence: 99%

Section: Design Of the Reference Short Takeoff And Landing Aircraftmentioning

confidence: 99%

Aerodynamic Installation Effects of an Over-the-Wing Propeller on a High-Lift Configuration

Müller¹,

Heinze²,

Kožulović³

et al. 2014

Journal of Aircraft

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“…In addition, the design tool is built to be able to incorporate multidisciplinary results for building surrogates, which can give reasonably accurate predictions at the overall aircraft level. Following a typical aircraft conceptual/preliminary design logic [30,[40][41][42]-especially the very comprehensive aircraft design platforms developed at the TU Braunschweig (PRADO tool [43]) and at the RWTH Aachen University (MICADO tool [42]) in Germany, some features and modelling strategies are illustrated as follows. It has to be noted that the tool developed within the EWL project has a very good compromise between complexity and fidelity levels, which is more suitable for aircraft technology assessment for such a joint research project as compared to other tools already being developed.…”

Section: General Approachmentioning

confidence: 99%

Exploring Vehicle Level Benefits of Revolutionary Technology Progress via Aircraft Design and Optimization

et al. 2018

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Abstract:It is always a strong motivation for aeronautic researchers and engineers to reduce the aircraft emissions or even to achieve emission-free air transport. In this paper, the impacts of different game-changing technologies together on the reduction of aircraft fuel consumption and emissions are studied. In particular, a general tool has been developed for the technology assessment, integration and also for the overall aircraft multidisciplinary design optimization. The validity and robustness of the tool has been verified through comparative and sensitivity studies. The overall aircraft level technology assessment and optimization showed that promising fuel efficiency improvements are possible. Though, additional strategies are required to reach the aviation emission reduction goals for short and medium range configurations.

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“…However, the high turn around time of RANS simulations make them unsuitable to perform optimization of 3D high lift geometry at the preliminary design stages, which is the focus of this work. In this context, Werner-Spatz et al 11 evaluated the DLR multiple lifting line method LIFTING LINE coupled with a sectional polar interpolation method to include non-linear effects into the analysis. Results demonstrated the superiority of this rapid method against semi empirical methods which are highly calibrated for a certain high-lift system type.…”

Section: Introductionmentioning

confidence: 99%

A Rapid Approach to the Aerodynamic Design of a Flexible High-Lift Wing

Trapani

Savill

Kipouros

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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The development and application of a rapid methodology for the optimization of HighLift configurations is here presented. The proposed framework includes a quasi-threedimensional method to simulate the aerodynamic performance, a rapid method for the estimation of the static aero-elastic effects, and two multi-objective optimization algorithms: the well-know NSGA-II and the innovative multi-objective Tabu Search. After an extensive validation study of both the aerodynamic simulation and the aero-structure coupling method, the framework is used to optimize the landing performance of the KH3Y configuration. The deployment settings of the full-span slat and of the two single-slotted flap elements, inboard and outboard, are identified as design variables. The maximum lift coefficient and the lift over drag ratio at the approach angle of attack are used as objective functions. Two optimization setups are executed to assess the influence of the wing flexibility on the revealed Pareto Front. In both cases the selected optimization algorithm has been able to improve the performance of the datum. Moreover, the results show the importance of considering aero-structure influences early on in the design process. Finally, parallel coordinate visualization techniques are used to analyze the peculiar Search Pattern revealed. NomenclatureK Stiffness matrix S Flexibility matrix u Displacements array Z Forces and moments array cd Drag coefficient cl Lift coefficient cl appr Lift coefficient at approach angle of attack L/D appr Lift to Drag ratio at approach angle of attack M Number of wing sections spanwise * EngD Researcher, School of Engineering, Centre for Propulsion. Student Member. g.trapani@cranfield.ac.uk

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Improved Representation of High-Lift Devices for a Multidisciplinary Conceptual Aircraft Design Process

Cited by 16 publications

References 12 publications

Aerodynamic Installation Effects of an Over-the-Wing Propeller on a High-Lift Configuration

Aerodynamic Installation Effects of an Over-the-Wing Propeller on a High-Lift Configuration

Exploring Vehicle Level Benefits of Revolutionary Technology Progress via Aircraft Design and Optimization

A Rapid Approach to the Aerodynamic Design of a Flexible High-Lift Wing

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