Takeoff-landing characteristics of regional aircraft with auxiliary retractable distributed electric power installation

DOI: 10.34759/vst-2020-1-19-29

Аuthors

Dunaevskii A. I.^*, Perchenkov E. S.^**, Chernavskikh Y. N.^***

Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia

*e-mail: dunaev_sky@mail.ru
**e-mail: e_perchenkov@rambler.ru
***e-mail: urij_ch@mail.ru

Abstract

The article regards the possibility of regional aircraft takeoff-landing characteristics improvement by employing blow-off from propellers of the auxiliary retractable multi-propeller distributed electro-power installation (DEPI). Its motors operate only during takeoff-landing modes being retracted into the wing while cruising flight. The DEPI motors small-size, commensurable with the flaps chord size, allow deflect the jets from propellers at substantial angles, ensuring herewith significant lift force increase. A large number of the DEPI motors reduces negative impact of any of these engines failure, which leads to the flight safety enhancement. Aerodynamic layout of an aircraft with DEPI as applied to the L410 class aircraft was formed, and calculations of takeoff-landing characteristics with account for the blowing effect were performed. The article demonstrates aerodynamic characteristics dependence on thrust-to-weight ratio, the wing geometric size and propeller diameter. It considers various options of cruise engines total thrust and DEPI motors relationship. It was shown that increasing in the DEPI thrust-to-weight ratio share leads to reduction of the runway length required for the takeoff. Thus, with typical total thrust-to-weight ratio being equal to 0.50, the increase in DEPS thrust from 0 to 25% results in runway length reduction from 780 m to 580 m, i.e. approximately by 25%.

An approach to compliance of Cp_{landing approach} and Cl_{landing approach} values, being realized with account for blowing, with flight-path angle at landing approach was suggested. The article demonstrates the presence of unique dependence between the flight-path angle, required Cp_{landing approach} value and re alized Cl_{landing approach} value.The possibility of realizing higher (approximately twofold) Cl_{landing approach} values due to the blow-off is shown. With typical wing load of 250 kg/m², the blow-off implementation allows required runway length reduction approximately by 20%.

Keywords:

takeoff modes, landing modes, flaps’ blow-off by jets from propellers, thrust-to-weight ratio, wing load, runway length

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