Abstract
The aim of this work is the development of a methodology to predict lift characteristics for transport aircraft in the whole flight envelope, useful in the preliminary aircraft design stage. The purpose is an attempt to improve the classical methodologies for wing load distribution and lift prediction, applicable to both clean and flapped configuration. This has been obtained considering the airfoils’ aerodynamic characteristics until stall and post-stall conditions during the process, and modifying 2D characteristics in the case of high-lift devices to take into account 3D effects introduced by the devices themselves. The method is a modification of standard vortex-lattice procedures which are capable of predicting wing aerodynamic characteristics. As regards the clean configuration, the enhanced method works by integrating airfoil characteristics, whereas as far as the high-lift devices’ effect is concerned, the improved method works by substituting clean airfoil aerodynamic characteristics for the flapped aerodynamics ones, and introducing a correction to evaluate the 3D effects induced by the high-lift devices’ geometrical discontinuities. The methodology is explained separately for these two configurations. The results of the developed method have been compared with CFD and experimental data showing good agreement, making available a fast and reliable method useful in preliminary aircraft design phase.
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Notes
Abbreviations
- 2D:
-
Two-dimensional
- 3D:
-
Three-dimensional
- AGILE:
-
Aircraft third-Generation MDO for Innovative Collaboration of Heterogeneous Teams of Experts
- AR:
-
Wing aspect ratio
- b :
-
Wing span
- CFD:
-
Computational fluid dynamics
- \(C_{l}\) :
-
Two-dimensional lift coefficient
- \(C^{\mathrm{clean}}_{{l}}\) :
-
Two-dimensional lift coefficient in clean configuration
- \(C^{\mathrm{hl}}_{{l}}\) :
-
Two-dimensional lift coefficient in high-lift configuration (high-lift devices deployed)
- \(C_{{l}_\mathrm{MAX}}\) :
-
Two-dimensional maximum lift coefficient
- \(C_{L}\) :
-
Three-dimensional lift coefficient
- \(C_{{L}_\mathrm{MAX}}\) :
-
Three-dimensional maximum lift coefficient
- \(C_\mathrm{r}\) :
-
Wing root chord
- \(C_\mathrm{t}\) :
-
Wing tip chord
- DAF:
-
Design of aircraft and flight technologies research group
- F :
-
Downwash influence function
- h :
-
Altitude
- HiLiftPW:
-
High-lift prediction workshop
- JPAD:
-
Java program tool chain for aircraft design
- M :
-
Mach number
- N :
-
One-half of total number vortex points
- MDO:
-
Multidisciplinary design optimization
- S :
-
Wing area
- V :
-
Free-stream velocity
- \(X_{\mathrm{LE}}\) :
-
Wing sections leading-edge coordinates along x-axis
- y :
-
Wing station along span (y-axis)
- \(\alpha\) :
-
Geometric angle of attack
- \(\alpha _{0l}\) :
-
Angle of attack which produces a 2D zero-lift condition
- \(\alpha _\mathrm{e}\) :
-
Effective angle of attack
- \(\alpha _\mathrm{s}\) :
-
Angle of attack at stall condition
- \(\alpha_\mathrm{w}\) :
-
Wing angle of attack
- \(\delta\) :
-
Zone between no-flap and deflected flap wing section
- \(\eta\) :
-
Non-dimensional spanwise coordinate
- \(\varGamma\) :
-
Circulation strength
- \(\varLambda _{\mathrm{LE}}\) :
-
Wing sweep angle at leading edge
- \(\nu\) :
-
Number of designating vortices’ control points
References
Roskam, J.: Airplane Design, Part VI, pp. 245–264. DAR Corporation, Kansas (1987)
Sforza, P.M.: Commercial Airplane Design Principles, pp. 145–179. Elsevier Science, Oxford (2014)
Torenbeek, E.: Synthesis of Subsonic Airplane Design: An Introduction to the Preliminary Design of Subsonic General Aviation and Transport Aircraft, with Emphasis on Layout, Aerodynamic Design, Propulsion and Performance, pp. 217–257. Springer, Delft (1976)
Nicolai, L.M., Charichner, G.E.: Fundamentals of Aircraft and Airship Design, pp. 221–253. AIAA, Reston (2010)
Prandtl, L.: Applications of Modern Hydrodynamics to Aeronautics, 116. NACA Technical Report, Germany (1923)
Anderson Jr., J.D.: Fundamentals of Aerodynamics, 5th edn, pp. 351–412. McGraw-Hill Education, New York (2010)
Baldoino, W.M., Bodstein, G.C.R.: Comparative Analysis of the Extended Lifting-Line Theory to the Classical Lifting-Line Theory for Finite Wings. ENCIT (2004)
Weissinger, J.: The Lift Distribution of Swept-Back Wings. NACA-TM-1120, Washington, DC (1947)
De Young, J., Harper, C.W.: Theoretical Symmetric Span Loading at Subsonic Speeds for Wings Having Arbitrary Planforms. NACA-TR-921, Washington, DC (1948)
Blackwell Jr., J.A.: A Finite-Step Method for Calculation of Theoretical Load Distributions for Arbitrary Lifting-Surface Arrangements at Subsonic Speeds. NASA Technical Note D-5335, Washington, DC (1969)
Jenkinson, L.R., Simpkin, P., Rhodes, D.: Civil Jet Aircraft Design, pp. 163–164. Arnold, London (1999)
Rumsey, C.L., Long, M., Stuever, R.A., Wayman, T.R.: Summary of the first AIAA CFD high lift prediction workshop (invited). In: Proceeding of 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. AIAA 2011-939, Orlando (2011)
Rudnik, R., Huber, K., Melber-Wilkending, S.: EUROLIFT test case description for the 2nd high lift prediction workshop. In: Proceeding of 30th AIAA Applied Aerodynamics Conference, New Orleans (2012)
Brezillon, J., Wild, J.: Evaluation of Different Optimization Strategies for the Design of a High-lift Flap Device. Evolutionary and Deterministic Methods for Design, Optimization and Control with Applications to Industrial and Societal Problems. EUROGEN, Munich (2005)
Ciliberti, D., Della Vecchia, P., Nicolosi, F., De Marco, A.: Aircraft directional stability and vertical tail design: a review of semi-empirical methods. Prog. Aerosp. Sci. 95, 140–172 (2017). https://doi.org/10.1016/j.paerosci.2017.11.001
Nicolosi, F., Della Vecchia, P., Ciliberti, D.: Aerodynamic interference issues in aircraft directional control. ASCE’s J. Aerosp. Eng. 28(1) (2015). https://doi.org/10.1061/(ASCE)AS.1943-5525.0000379
Nicolosi, F., Paduano, G.: Development of a software for aircraft preliminary design and analysis. 3rd CEAS Air and Space Conference, 21st AIDAA Congress, Venezia (2011)
Ruocco, M., Trifari V., Cusati V.: A Java-based framework for aircraft preliminary design—wing aerodynamic analysis module, longitudinal static stability and control module. In: READ 2016 Conference, Warsaw (2016)
Trifari, V., Ruocco, M., Cusati V., Nicolosi F., De Marco A.: Java framework for parametric aircraft design ground performance. Aircr. Eng. Aerosp. Technol. 89(4) (2017). https://doi.org/10.1108/AEAT-11-2016-0209
Nicolosi, F., De Marco, A., Attanasio L., Della Vecchia, P.: Development of a Java-based framework for aircraft preliminary design and optimization. AIAA J. Aerosp. Inf. Syst. (JAIS) 13 (2016). https://doi.org/10.2514/1.I010404
Della Vecchia, P., Stingo, L., Corcione, S., Ciliberti, D., De Marco, A.: Game theory and evolutionary algorithms applied to MDO in the AGILE European project. In: 18th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, AIAA Aviation Forum (2017). https://doi.org/10.2514/6.2017-4330
Della Vecchia, P., Corcione, S., Pecora, R., Nicolosi, F., Dimino, I., Concilio, A.: Design and integration sensitivity of a morphing trailing edge on a reference airfoil: the effect on high-altitude long-endurance aircraft performance. J. Intell. Mater. Syst. Struct. 28(20), 2933–2946 (2017). https://doi.org/10.1177/1045389X17704521
Nagel, B., Ciampa, P.D.: Aircraft 3rd Generation MDO for Innovative Collaboration of Heterogeneous Teams of Experts; AGILE Proposal (2014)
Seider, D., Fischer, P., Litz, M., Schreiber, A., Gerndt, A.: Open source software framework for applications in aeronautics and space. In: Aerospace Conference IEEE (2012)
Koven, W., Graham, R.R., Wind Tunnel Investigation of High-Lift and Stall-Control Devices On a 37 Sweptback Wing of Aspect Ratio 6 at High Reynolds Numbers. NACA RM No L8D29 (1948)
Acknowledgements
The research presented in this paper has been performed in the framework of the AGILE project (Aircraft 3rd Generation MDO for Innovative Collaboration of Heterogeneous Teams of Experts) and has received funding from the European Union Horizon 2020 Program (H2020-MG-2014-2015) under Grant Agreement No. 636202. The authors are grateful to the partners of the AGILE consortium for their contribution and feedback.
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Della Vecchia, P., Nicolosi, F., Ruocco, M. et al. An improved high-lift aerodynamic prediction method for transport aircraft. CEAS Aeronaut J 10, 795–804 (2019). https://doi.org/10.1007/s13272-018-0349-5
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DOI: https://doi.org/10.1007/s13272-018-0349-5