2,092 research outputs found
Spitsbergen [cartographic material].
No full textPlate [2] from: Atlas, behoorende tot de Verhandeling / van R.G. Bennet en J. van Wijk, Roelandsz. Dordrecht : bij J. de Vos & Comp., 1829.; Koeman, BEN 1.; Also available online http://nla.gov.au/nla.map-ra105-s2
Kaart van Nieuw Nederland [cartographic material] : behoorende tot de, door het Provinciaal Utrechtsch Genootschap bekroonde verhandeling.
No full textPlate [4] from: Atlas, behoorende tot de Verhandeling / van R.G. Bennet en J. van Wijk, Roelandsz. Dordrecht : bij J. de Vos & Comp., 1829.; Koeman, BEN 1.; Also available online http://nla.gov.au/nla.map-ra105-s4
Kaart van Japan [cartographic material] : behoorende tot de, door het Provinciaal Utrechtsch Genootschap bekroonde verhandeling.
No full textPlate [8] from: Atlas, behoorende tot de Verhandeling / van R.G. Bennet en J. van Wijk, Roelandsz. Dordrecht : bij J. de Vos & Comp., 1829.; Koeman, BEN 1.; Also available online http://nla.gov.au/nla.map-ra105-s8
Kaart der Noordelyke Yszee volgens de waarnemingen van vroegere Nederlandsche Zeelieden [cartographic material].
No full textPlate [1] from: Atlas, behoorende tot de Verhandeling / van R.G. Bennet en J. van Wijk, Roelandsz. Dordrecht : bij J. de Vos & Comp., 1829.; Koeman, BEN 1.; Also available online http://nla.gov.au/nla.map-ra105-s1. Insets: Mauritius of Jan Mayen Eil. 1611 -- Nederlandsche ontdekkingen langs de kust van oost-Groenland
Kaart van Straat Magellaan, Straat Le Maire, het Vuurland en Kaap Hoorn [cartographic material].
No full textPlate [3] from: Atlas, behoorende tot de Verhandeling / van R.G. Bennet en J. van Wijk, Roelandsz. Dordrecht : bij J. de Vos & Comp., 1829.; Koeman, BEN 1.; Also available online http://nla.gov.au/nla.map-ra105-s3. Inset: Kaart van het Dirk Gerrits Land : tegenwoordig bekend onder den naam van Nieuw Zuid Shetland
Stille Zuid Zee no. 2 [cartographic material].
No full textScale [ca. 1:9 000 000]. Map of the Pacific Ocean showing tracks of explorers, including Schouten 1616 and Roggeveen 1722.; Plate [7] from: Atlas, behoorende tot de Verhandeling / van R.G. Bennet en J. van Wijk, Roelandsz. Dordrecht : bij J. de Vos & Comp., 1829.; Koeman, Ben 1.; Tooley, 1456.; Also available in an electronic version via the Internet at: http://nla.gov.au/nla.map-t1456. Inset: Nieuw Zeeland : ontdekt door Tasman, 1642
Kaart van Nieuw Holland, Nieuw Guinea, en omliggende eilanden, behoorende tot de, door het provinciaal utrechisch genootschap bekroondeVerhandeling [cartographic material] /
No full textScale [ca. 1:12 000 000]. Map of Australia and Papua New Guinea with relief shown by hachures.; Plate [5] from: Atlas, behoorende tot de Verhandeling / van R.G. Bennet en J. van Wijk, Roelandsz. Dordrecht : bij J. de Vos & Comp., 1829.; Prime meridian: Greenwich.; Koeman, Ben 1.; Also available in an electronic version via the Internet at: http://nla.gov.au/nla.map-rm3579
A Method for the Conceptual Design of Hybrid Electric Aircraft
No full textThe growing interest into hybrid electric propulsion as a possible solution to reduce in-flight emissions has led to the investigations of many innovative propulsive system architectures that couple higher system efficiency with improved aerodynamic propulsion integration strategies. The paper presents amethodology to model and size generic hybrid electric propulsion system at the conceptual level allowing for a rapid exploration of the vast design space. The generalization of the propulsive system using a basic propulsive power unit object is discussed highlighting the control parameters needed to fully define the propulsive system architecture. Three case studies for a 2035 turbo-prop regional aircraft using parallel, series/parallel and distributed series configurations showthat improvements to the fuel and energy consumption are affected by the system morphology, its control strategy and the maturity level assumed for its components. Using conservative estimations for the battery and electric components performances indicate that the best configurations can only provide a fuel reduction of around 5% while weighting 25% more than the reference design. Using more optimistic assumptions leads to a larger feasible design space where the best performing configuration, the series/parallel one, realizes more substantial fuel and energy reductions of 28% and 14% with a 24% higher take-off mass.Accepted Author Manuscript DOI: 10.2514/6.2019-1587.c1 Correction: A Method for the Conceptual Design of Hybrid Electric Aircraft Author(s) Name: Jacopo Zamboni(1); Roelof Vos(1); Mathias Emeneth(2); Alexander Schneegans(2) Author(s) Affiliations: 1. Delft University of Technology, Delft, Netherlands. 2. PACE America, Inc., Seattle, WA, United States. Correction Notice 1: In the first paragraph of section C.1 “Parallel Architecture” on page 13, the electric power ratio symbol should read φ, not ϕ. In the first paragraph of section C.1 “Parallel Architecture” on page 13, the shaft power ratio symbol should read ϕ, not φ. Correction Notice 2: In the third paragraph of section C.2 “Parallel/Series Architecture” on page 13, the inboard PPU is characterized by a constant shaft power ratio of 0, not 1; the outboard PPU is characterized by a shaft power ratio of 1 (fully electric shaft), not 0. Correction Notice 3: In the fifth paragraph of section C.3 “Distributed Series Architecture” on page 14, the shaft power ratio is set permanently to 1, not 0. Correction Notice 4: In the caption of Figure 13 on page 19, the upper right sub-figure refers to the results of the series/parallel configuration, not of the parallel configuration. The upper left sub-figure refers to the results of the parallel configuration, not of the series/parallel configuration.Flight Performance and Propulsio
Experimental Investigation of Over-the-Wing Propeller–Boundary-Layer Interaction
No full textThis experimental study focuses on the aerodynamic interaction between an over-the-wing (OTW) propeller and a wing boundary layer. An OTW propeller is positioned above the hinge line of a wing with a trailing-edge flap. Measurements are carried out with and without axial pressure gradients by deflecting the flap and by extending the flat upper surface of the wing in the streamwise direction, respectively. Surface-pressure taps, microphones, and particle image velocimetry are combined to quantify both the time-averaged and unsteady interaction effects. Results show that the propeller generates an adverse pressure gradient on the wing surface that scales linearly with thrust and decreases with increasing blade-tip clearance. The pressure gradient is partially caused by slipstream contraction, which decelerates the flow near the wall. Additionally, the surface-pressure fluctuations generated beneath the propeller blades and slipstream are stronger than the time-averaged pressure increase due to flow deceleration. Consequently, the propeller triggers flow separation over the hinge line when the flap is deflected. A parametric study of different propeller locations indicates that increasing the tip clearance is not an effective way to mitigate flow separation. However, displacing the propeller half a radius upstream of the hinge line creates a Coandă effect, which allows the flow to remain attached.Green Open Access added to TU Delft Institutional Repository ‘You share, we take care!’ – Taverne project https://www.openaccess.nl/en/you-share-we-take-care Otherwise as indicated in the copyright section: the publisher is the copyright holder of this work and the author uses the Dutch legislation to make this work public.Flight Performance and PropulsionWind Energ
Aerodynamic Interaction Between an Over-the-Wing Propeller and the Wing Boundary-Layer in Adverse Pressure Gradients
No full textThis experimental study focuses on the aerodynamic interaction effects that occur between an over-the-wing (OTW) propeller and a wing boundary-layer. An OTW propeller is positioned above the hinge-line of a wing featuring a plain flap. The measurements are carried out with and without axial pressure gradients by deflecting the flap and by extending the wing in streamwise direction to simulate a flat-plate configuration, respectively. Wing pressure taps and phase-free particle-image-velocimetry (PIV) are used to quantify the time-averaged interaction effects, while embedded microphones and phase-locked PIV are used to analyze unsteady interaction effects. Results show that the propeller generates an adverse pressure gradient on the wing surface which increases linearly with thrust and decreases as the blade tipclearance is increased. The pressure gradient is partially caused by the slipstream contraction, which creates a streamwise velocity deficit near the wall immediately behind the propeller disk. Moreover, the rotation of the propeller blades generates pressure fluctuations on the surface, the amplitude of which exceeds both the pressure fluctuations produced by the tip-vortices and the time-averaged pressure effect of the slipstream. Consequently, the propeller triggers flow separation when the flap is deflected. A parametric study of different propeller locations indicates that increasing the tip-clearance is not an effective way to mitigate flow separation. However, displacing the propeller half a radius upstream induces a Coanda effect which allows the flow to remain attached
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