Design of a prototype of light amphibious PrandtlPlane

Frediani, Aldo; Cipolla, Vittorio; Oliviero, Fabrizio

doi:10.2514/6.2015-0700

Cited by 28 publications

(35 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…According to previous research carried out at the University of Pisa (Frediani et al, 2007;Frediani et al, 2015), focused on the application of the PrandtlPlane configuration to light subsonic aircraft, the preliminary assessment of the aforementioned flight mechanic requirements can be performed by using Vortex-Lattice Methods. In particular, the use of the code AVL (Drela and Youngren, 2017) has been successfully implemented, both as evaluation or optimization tool (Rizzo, 2009), by means of a specific modelling strategy based on the replacement of the fuselage with a lifting surface with a similar planform (Figure 4).…”

Section: Flight Mechanic Analysis Through Vortex-lattice Methods In Smentioning

confidence: 99%

“…Aircraft Engineering and Aerospace Technology 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 A i r c r a f t E n g i n e e r i n g a n d A e r o s p a c e T e c h n o l o g y As described in details in (Frediani et al, 2015), both numerical and experimental activities, including flight tests on scaled models, performed within the project IDINTOS, have shown the following advantages of the PrandtlPlane configuration:…”

Section: Page 3 Of 41mentioning

confidence: 99%

See 1 more Smart Citation

Preliminary stability analysis methods for PrandtlPlane aircraft in subsonic conditions

Cipolla

Salem

Bachi

2019

AEAT

Self Cite

View full text Add to dashboard Cite

The present paper aims to assess the reliability and the limitations of analysing the flight stability of a boxwing aircraft configuration known as PrandtlPlane by means of methods conceived for conventional aircraft and well known in literature. Design/methodology/approach: Results obtained by applying vortex lattice methods to PrandtlPlane configuration, validated previously with wind tunnel tests, are compared to the output of a "Roskam-like" method, here defined in order to model the PrandtlPlane features. Findings: The comparisons have shown that the "Roskam-like" model gives accurate predictions for both the Longitudinal Stability Margin and Dihedral Effect, whereas the Directional Stability is always overestimated. Research limitations/implications: The method here proposed and related achievements are valid only for subsonic conditions. The poor reliability related to lateral-directional derivatives estimations may be improved implementing different models known from literature. Practical implications: The possibility to apply a faster method as the "Roskam-like" here presented has two main implications: 1) it allows to implement faster analyses in the conceptual and preliminary design of PrandtlPlane, providing also a tool for the definition of the design space in case of optimization approaches 2) it allows to implement scaling procedure, in order to study families of PrandtlPlanes or different aircraft categories. Social implications: This paper is part of the activities carried out during the PARSIFAL project, which aims to demonstrate that the introduction of PrandtlPlane as air transport mean can fuel consumption and noise impact, providing a sustainable answer to the growing air passenger demand envisaged for the next decades. Originality/value: The originality of this paper lies in the attempt of adopting analysis method conceived for conventional airplanes for the analysis of a novel configuration. The value of the work is represented by the knowledge concerning experimental results and design methods on the PrandtlPlane configuration, here made available in order to define a new analysis tool.

show abstract

Section: Flight Mechanic Analysis Through Vortex-lattice Methods In Smentioning

confidence: 99%

Section: Page 3 Of 41mentioning

confidence: 99%

Preliminary stability analysis methods for PrandtlPlane aircraft in subsonic conditions

Cipolla

Salem

Bachi

2019

AEAT

Self Cite

View full text Add to dashboard Cite

show abstract

“…Other mitigation measures included placing more priority on structural reinforcements against out-of-plane bending moments (as also recommended by Wolkovitch [22] for the joined-wing configuration), and increasing the fore wing skin thickness [62]. Frediani went on to consider applications in commercial aviation [63,64] and for personal use [65], with each aircraft designed for lower Mach numbers, as recommended by Lange et al [60].…”

Section: The Box Wingmentioning

confidence: 99%

Aerodynamic Shape Optimization of a Box-Wing Regional Aircraft Based on the Reynolds-Averaged Navier-Stokes Equations

Chau

2017

35th AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

The box wing is an unconventional aircraft configuration that has the potential to provide major savings in fuel consumption relative to the conventional cantilever wing. In order to further develop and evaluate this potential, high-fidelity aerodynamic shape optimization is applied to the aerodynamic design of a box wing and a cantilever wing, based on the Embraer E190 regional jet, with the latter serving as a performance baseline. The optimization framework consists of B-spline parameterization, free-form and axial deformation geometry control, an integrated mesh-movement scheme based on the theory of linear elasticity, a Newton-Krylov-Schur flow solver for the Reynolds-averaged Navier-Stokes equations, a gradient-based optimizer, and the discrete-adjoint method for gradient evaluation. Results indicate that a box-wing with a heightto-span ratio of 0.26 burns 7.61% less fuel at cruise than a conventional baseline of the same span and lift. Aerodynamic trends and trade-offs are investigated, and a weight sensitivity study is performed.ii Acknowledgements First and foremost, I would like to thank my supervisor, Professor David Zingg. I cannot thank him enough for the opportunity to work on such a state-of-the-art problem, which has proven to be challenging, but incredibly rewarding. I also have him to thank for the invaluable knowledge and experience that I have gained during these past few years. His passion for computational aerodynamics and environmentally-friendly aircraft design is something to be envied, and will always serve as a pillar of inspiration. I would also like to thank the UTIAS community for creating a welcoming and fun work environment. To the computational aerodynamics group, thank you for all of the helpful feedback you have given me over the years, and for making my late nights in the lab palatable. In particular, I would like to thank Dr. Shahriar Khosravi for the many interesting discussions on aerodynamics and structures, and Dr. Thomas Reist for his invaluable technical guidance and discussions on aircraft design.

show abstract

“…The main characteristics and the advantages of the PrandtlPlane configuration have been discussed in previous works ( [2], [3], [4], [5], [6], [7]) showing also the possible disadvantages and, in particular, flutter characteristics. The particular aspects to be faced in the case of a very large freighter regard the interaction between structures and Flight Mechanics and Controls.…”

Section: Figure 2 Example Of Prandtlplane Freightermentioning

confidence: 99%

Aerodynamic optimization of a large PrandtlPlane configuration

Cappelli¹,

Costa²,

Cipolla

et al. 2016

Aerotec. Missili Spaz.

View full text Add to dashboard Cite

The purpose of this paper is to present design procedures and tools for the aerodynamic optimization of a large freighter aircraft with a PrandtlPlane configuration. Suitable optimization tools have been developed and are shortly described in the paper; sensitivity analyses for high speed flight conditions have been performed, and, also, low speed performances are evaluated to provide a complete preliminary design of the PrandtlPlane freighter.

show abstract

Design of a prototype of light amphibious PrandtlPlane

Cited by 28 publications

References 2 publications

Preliminary stability analysis methods for PrandtlPlane aircraft in subsonic conditions

Preliminary stability analysis methods for PrandtlPlane aircraft in subsonic conditions

Aerodynamic Shape Optimization of a Box-Wing Regional Aircraft Based on the Reynolds-Averaged Navier-Stokes Equations

Aerodynamic optimization of a large PrandtlPlane configuration

Contact Info

Product

Resources

About