Info: Zenodo’s user support line is staffed on regular business days between Dec 23 and Jan 5. Response times may be slightly longer than normal.

Published December 31, 2019 | Version v1
Journal article Open

ESTIMATION OF THE AERODYNAMIC CHARACTERISTICS OF A STEPPED NACELLE FOR THE AIRCRAFT POWERPLANT

Creators

  • 1. National Aviation University
  • 2. State Aviation Research Institute

Description

The purpose of this work is to estimate the aerodynamic characteristics of the stepped nacelle of a gas turbine engine with a turbofan unit. The research was based on the method of model physical experiment. The wind tunnel applied for the study was provided with the necessary equipment, which includes various nozzles of static and dynamic pressure with coordinate devices, etc. For the experimental study, we built the models of nacelles for an aviation power plant with front location of the fan module and with the rear arrangement of a turbofan unit. We have experimentally investigated the aerodynamic characteristics of the stepped nacelle for a gas turbine engine with a turbofan unit.

The results of this study demonstrated a possibility to decrease the aerodynamic drag of the stepped nacelle for an engine with a turbofan unit compared to the nacelle of a turbojet double-pass engine with the front arrangement of the fan. In the range of angles of attack α=0...20° the value of aerodynamic drag of the stepped nacelle for a gas turbine engine with a turbofan unit decreases by 49...55 %.

The obtained results showed that the coefficient of lifting power of the stepped nacelle for a gas turbine engine with a turbofan unit increases by 24...64 %. The coefficient of aerodynamic drag is lower by 18...28 % compared with the aerodynamic drag coefficient of a cylindrical nacelle for a double-pass turbojet engine in the range of angles of attack α=2...20°. Our findings indicate the prospects of using engines with a turbofan unit. The structural feature of the stepped nacelle would reduce the loss of efficient engine thrust by decreasing aerodynamic drag almost by two times and could increase fuel efficiency of the engine

Files

Estimation of the aerodynamic characteristics of a stepped nacelle for the aircraft powerplant.pdf

Files (461.7 kB)

Additional details

References

  • Chekalova, N. I. (2015). Methods of calculation of engine gondolas and landing gears resistance. Civil Aviation High Technologies, 211, 136–137.
  • Malouin, B., Gariépy, M., Trépanier, J.-Y., Laurendeau, É. (2015). Internal Drag Evaluation for a Through-Flow Nacelle Using a Far-Field Approach. Journal of Aircraft, 52 (6), 1847–1857. doi: https://doi.org/10.2514/1.c033093
  • Zhang, Y., Chen, H., Fu, S., Zhang, M., Zhang, M. (2015). Drag prediction method of powered-on civil aircraft based on thrust drag bookkeeping. Chinese Journal of Aeronautics, 28 (4), 1023–1033. doi: https://doi.org/10.1016/j.cja.2015.06.015
  • Robinson, M., MacManus, D. G., Sheaf, C. (2018). Aspects of aero-engine nacelle drag. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 233 (5), 1667–1682. doi: https://doi.org/10.1177/0954410018765574
  • Trapp, L. G., Argentieri, H. G. (2010). Evaluation of nacelle drag using computational fluid dynamics. Journal of Aerospace Technology and Management, 2 (2), 145–153. doi: https://doi.org/10.5028/jatm.2010.02026410
  • Li, J., Gao, Z., Huang, J., Zhao, K. (2013). Aerodynamic design optimization of nacelle/pylon position on an aircraft. Chinese Journal of Aeronautics, 26 (4), 850–857. doi: https://doi.org/10.1016/j.cja.2013.04.052
  • Sasaki, D., Nakahashi, K. (2011). Aerodynamic Optimization of an Over-the-Wing-Nacelle-Mount Configuration. Modelling and Simulation in Engineering, 2011, 1–13. doi: https://doi.org/10.1155/2011/293078
  • Peters, A., Spakovszky, Z. S., Lord, W. K., Rose, B. (2014). Ultra-Short Nacelles for Low Fan Pressure Ratio Propulsors. Volume 1A: Aircraft Engine; Fans and Blowers. doi: https://doi.org/10.1115/gt2014-26369
  • Robinson, M. H., MacManus, D. G., Richards, K., Sheaf, C. (2017). Short and slim nacelle design for ultra-high BPR engines. 55th AIAA Aerospace Sciences Meeting. doi: https://doi.org/10.2514/6.2017-0707
  • Savelyev, A., Zlenko, N., Matyash, E., Mikhaylov, S., Shenkin, A. (2016). Optimal design and installation of ultra high bypass ratio turbofan nacelle. AIP Conference Proceedings, 1770. doi: https://doi.org/10.1063/1.4964065
  • Tereshchenko, Y. Y., Tereshchenko, Y. M., Doroshenko, K. V., Usenko, V. Y. (2018). Profile resistance of a gas-turbine engine nacelle with a turbofan attachment. Problems of friction and wear, 4, 64–73.
  • Yugov, O. K., Selivanov, O. D. (1980). Soglasovanie harakteristik samoleta i dvigatelya. Moscow: Mashinostroenie, 200.