Aerodynamic Assessment of Pylon-Mounted Over-the-Wing Engine Installations on a STOL Commercial Aircraft Concept

Savoni, Luciana; Rudnik, Ralf

doi:10.1007/978-3-319-64519-3_5

Cited by 4 publications

(5 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The computation at constant lift coefficient reveals a strong shock located at 75% local chord, as shown in Figure 4(b) depicting the pressure diagram at the engine expected spanwise location η = 0.31. Figure 4(a) clearly shows the large extent of the transonic area on the upper wing surface: the mitigation of the shock related wave drag is essential to yield a positive effect of the engine installation on the overall drag, as shown in previous investigations 4 . Furthermore, a trailing edge flow separation at the kink has been detected, extending around 25% span.…”

Section: Results For the Baseline Configurationmentioning

confidence: 52%

“…An ultra high bypass turbofan engine designed by the Institute of Jet Propulsion and Turbomachinery (IFAS) of the Technical University of Braunschweig has been integrated on the WB geometry in the reference position at the spanwise station η = 0.31. As demonstrated in the study of Hooker 5 and confirmed in the engine position variation analysis carried out on REF3 4,6 , this spanwise position is the most beneficial in cruise conditions in terms of interference effects between high speed wing flow and low speed engine flow. In the following phase, the pylon has been designed and adapted to the nacelle and wing geometry.…”

Section: Geometry Numerical Set-up and Test Casementioning

confidence: 62%

“…An increase in pylon length results in an increase in the final angle of attack at target lift coefficient. Due to the presence of the engine over the wing and to the highly twisted wing 3 of the baseline configuration, high angles of attack have been observed in all the previous studies 4,6 . More specifically, considering the same target lift coefficient equal to 0.46, the resulting angle of attack is 2.4° for the WB, 3.8° for the WBE with free-flying engine and 2.9° for the WBEP in the reference configuration.…”

Section: F Doe Preliminary Resultsmentioning

confidence: 84%

“…Figure 4: Isobars on the surface of the WB configuration (a) and Pressure diagram for the WB at the engine expected location η = 0.31 (b). 4 In a successive phase, the engine has been integrated in the reference spanwise position η = 0.31, first without any pylon, in order to investigate the effects due to the installation of the engine only, and then with the pylon. The results of the computation of the WBE configuration without pylon have been described in other studies 8 and will be omitted for the sake of brevity.…”

Section: Results For the Baseline Configurationmentioning

confidence: 99%

See 3 more Smart Citations

Pylon Design for a Short Range Transport Aircraft with Over-the-Wing Mounted UHBR Engines

Savoni

Rudnik

2018

2018 AIAA Aerospace Sciences Meeting

Self Cite

View full text Add to dashboard Cite

Over-the-wing mounted (OWM) engines, together with their design challenges and their potential in terms of aerodynamic benefits and positive installation effects, are investigated with CFD methods. The analysed reference configuration is a new concept of a civil transport aircraft with short takeoff and landing characteristics featuring a circulation control supported high lift system. The concept is intended to provide extraordinary airfield performance while meeting low noise standards. The reference aircraft will be firstly analysed in its wing/body layout. Successively, engine and pylon will be integrated and analysed. A description of the pylon design and parametrization will be given. The results of the wing/body/engine/pylon configuration computations will be discussed in order to assess the transonic flow phenomena taking place on the upper wing when an engine is integrated over the wing in cruise condition and the overall impact of the pylon on the flowfield. Particular attention will be reserved to the flow on the pylon, in order to identify aerodynamic characterisitscs, possible flow separations and to evaluate a strategy for an optimization process. The pylon optimization procedure will be described in detail, together with the tools used and the parameters defining the pylon shape. The preliminary results and trends of the Design of Experiment will eventually be discussed in order to provide an outlook on complete optimization scenarios for such configurations.

show abstract

Section: Results For the Baseline Configurationmentioning

confidence: 52%

Section: Geometry Numerical Set-up and Test Casementioning

confidence: 62%

Section: F Doe Preliminary Resultsmentioning

confidence: 84%

Section: Results For the Baseline Configurationmentioning

confidence: 99%

See 2 more Smart Citations

Pylon Design for a Short Range Transport Aircraft with Over-the-Wing Mounted UHBR Engines

Savoni

Rudnik

2018

2018 AIAA Aerospace Sciences Meeting

Self Cite

View full text Add to dashboard Cite

show abstract

“…For the aerodynamic studies a steady 3D RANS approach is used and the simulations are run with the Figure 3: First results of the integration studies of the podded engines for cruise flight conditions, see. 9 DLR flow solver TAU-Code. 11 For the integration studies a surface model of the aircrafts Wing-Body (WB) and UHBR engine are required, which were created with the commercial CAD tool CATIA V5.…”

Section: Aerodynamicsmentioning

confidence: 99%

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

Delfs

Appel

Bernicke

et al. 2017

35th AIAA Applied Aerodynamics Conference

Self Cite

View full text Add to dashboard Cite

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.

show abstract

Coupled Aeropropulsive Design Optimization of an Over-Wing Nacelle Configuration

Kaiyoom

Yildirim

Martins

2023

AIAA SCITECH 2023 Forum

View full text Add to dashboard Cite

Aerodynamic Assessment of Pylon-Mounted Over-the-Wing Engine Installations on a STOL Commercial Aircraft Concept

Cited by 4 publications

References 2 publications

Pylon Design for a Short Range Transport Aircraft with Over-the-Wing Mounted UHBR Engines

Pylon Design for a Short Range Transport Aircraft with Over-the-Wing Mounted UHBR Engines

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

Coupled Aeropropulsive Design Optimization of an Over-Wing Nacelle Configuration

Contact Info

Product

Resources

About