Improving aircraft fuel efficiency by using the adaptive wing and winglets

Popov, Viktor; Loginov, Vasyl; Ukrainets, Yevgen; Shmyrov, Volodymyr; Steshenko, Petro; Hlushchenko, Pavlo

doi:10.15587/1729-4061.2020.200664

Cited by 3 publications

(3 citation statements)

References 26 publications

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“…Compared to known procedures [19][20][21], the methodology for determining the characteristics of flight range and duration in a typical flight of a passenger aircraft [25][26][27] is integrated with the procedure for design calculation of a propeller [28][29][30][31]. The improvement of these procedures was intended to take into account the effect of propeller operation on the aerodynamic performance of an aircraft that previously had a different type of engine.…”

Section: Discussion Of Results Of Studying the Parametric Appearance ...mentioning

confidence: 99%

Design of the parametric appearance of the power plant for modifications of the regional passenger aircraft An-158

Loginov,

Ukrainets,

Humennyi

et al. 2023

EEJET

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The object of research is the process of remotorization of a regional passenger aircraft to increase its fuel efficiency. Based on the conceptual requirements for the remotorization of the An-158 aircraft with turbojet bypass engines, a parametric appearance of three modifications of this aircraft with turboprop engines for 80, 100, and 120 passenger seats was formed. The study was carried out on the basis of the well-known modular software systems «Integration 2.1» and «Air propeller 2.2» for typical flight profiles of the An-158 aircraft. Improved procedures of weight design and determination of the takeoff characteristics of aircraft with different types of power plant engines have made it possible to identify the most advantageous flight speeds of aircraft modifications with a turboprop engine corresponding to different flight masses. The results of the study of flight performance for optimal and «non-optimal» modifications of the aircraft are reported. The parametric appearance of the propeller was formed, the shape of the propeller blade for the cruising flight mode was determined for modifying the aircraft with a maximum number of passengers – 120 people. It is shown that the propeller for this modification of the aircraft cannot have less than 8 blades since with a smaller number of blades, the maximum chord of the propeller blade increases. The inductive power costs increase significantly due to the small elongation of the blades and, as a result, the flight efficiency of the propeller decreases. It is shown that the total fuel consumption for the entire typical flight of all modifications of the aircraft with turboprop engine at all studied flight speeds is less than the total fuel consumption of the An-158 base aircraft

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Section: Discussion Of Results Of Studying the Parametric Appearance ...mentioning

confidence: 99%

Design of the parametric appearance of the power plant for modifications of the regional passenger aircraft An-158

Loginov,

Ukrainets,

Humennyi

et al. 2023

EEJET

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“…In spite of an increase in drag with an increase and S WD , due to the change in the coefficient A of the dependences C L (C D ), the 'wing -WD' layout has a greater gradient. This is explained by the fact that, at small values of the spiroid relative radius, a concentrated vortex continues to form [24] and causes a rather strong flow bevel on the main wing. Also, the WD adding its own profile resistance leads to a deterioration in the lift drag ratio of the layout.…”

Section: Discussion Of Resultsmentioning

confidence: 99%

“…8). This is due to an increase in the loading of the final sections, a change in the velocity field behind the wing [24], and the dump coefficient of the polar А.…”

Section: K C L R R B K =mentioning

confidence: 99%

Aerodynamic Characteristics of a Straight Wing with a Spiroid Wingtip Device

Kravchenko

Loginov²,

Ukrainets

et al. 2021

Transactions on Aerospace Research

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Spiroid wingtip devices (WD) offer a promising way of improving the lift drag ratio of UAVs, but may on the other hand lead to negative aerodynamic interference of the wing with the WD and deterioration of the aerodynamic characteristics as compared to a wing without the WD. Determining the influence of the geometric parameters of a spiroid WD on aerodynamic wing characteristics, however, remains an understudied field. In our study, we investigated the influence of the following geometrical parameters on wing aerodynamic characteristics with WD: area, radius, camber angle, constriction, and pitch of the spiroid. We found that the positive effect of the WD is present at a relative radius > 0.05, as well as with an increase in the lift coefficient C L as a result of an increase in the proportion of inductive resistance. For example, with the Reynolds number Re = 2.1×105 for a rectangular wing with an aspect ratio θ = 5.12 equipped with a spiroid WD with =0.15 the quality gain is almost 10% at C L = 0.5, and at C L = 0.7 is almost 20% and at C L = 0.7 – almost 20% compared to a wing without WD. Moreover, we found that a change in the camber angle WD θ provides an increase in the derivative of the lift coefficient with respect to the angle of attack in the range from θ = 0° to θ = 130°. By changing the camber angle, it is possible to increase the lift drag ratio of the layout up to 7.5% at θ = 90° compared to θ = 0° at the Reynolds number Re = 2.1×105. From the point of view of ensuring maximum lift drag ratio and minimum inductive drag, the angle θ = 90° is the most beneficial.

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