Selecting the Mutual Arrangement of the Engine and Wing in A Transport Aircraft for Short Take-off and Landing

In order to maintain the competitive advantage of the medium short take-off and landing transport aircraft, the task must be solved of ensuring take-off and landing on the ground runways with a length of 600‒800 m when installing a turbojet engine.When the engines are installed on the pylons under the wing, this is achieved by using a «forced» turn of the jet of engines when the flaps are released at an angle of 60°. We have found the mutual location of the wing and the engine on its stagger, based on the position relative to the construction plane of the wing and the angle of installation. A reciprocal arrangement has been determined, making it possible to maximize the lift force owing to the turn of the jet stream. It has been shown that this achieves the continuous flow around the sections of the flaps when they are deflected at a 60-degree angle.We have analyzed the temperature effect of the jet stream on the mechanization and the aircraft wing at the stages of take-off and landing at different positions of engines under the wing, at different flight speeds and angles of attack. The effect of mechanization on the distribution of jet stream speeds and temperatures has been analyzed. It is shown that decreasing the distance between the engine nozzle and the lower surface of the wing leads to an increase in the angle of the jet stream deviation. We have identified those tail section zones of the flap, which require special execution to operate at temperatures above 400 °C.The impact of the jet stream on aircraft's drag in the cruising configuration has been analyzed, as well as the scheme of engine arrangement on the aircraft's electrically dependent systems. We have shown the absence of the impact of the jet stream on the aircraft's drag in the cruising configuration, the reduction of fuel consumption at cruising modes, as well as the favorable impact exerted on the electrically dependent systems due to the significant reduction of gas-dynamic losses along the power plant tract.Ways to modernize the transport aircraft type of An-70 have been proposed to ensure its superiority in its clas

Selecting the Mutual Arrangement of the Engine and Wing in A Transport Aircraft for Short Take-off and Landing

In order to maintain the competitive advantage of the medium short take-off and landing transport aircraft, the task must be solved of ensuring take-off and landing on the ground runways with a length of 600‒800 m when installing a turbojet engine.When the engines are installed on the pylons under the wing, this is achieved by using a «forced» turn of the jet of engines when the flaps are released at an angle of 60°. We have found the mutual location of the wing and the engine on its stagger, based on the position relative to the construction plane of the wing and the angle of installation. A reciprocal arrangement has been determined, making it possible to maximize the lift force owing to the turn of the jet stream. It has been shown that this achieves the continuous flow around the sections of the flaps when they are deflected at a 60-degree angle.We have analyzed the temperature effect of the jet stream on the mechanization and the aircraft wing at the stages of take-off and landing at different positions of engines under the wing, at different flight speeds and angles of attack. The effect of mechanization on the distribution of jet stream speeds and temperatures has been analyzed. It is shown that decreasing the distance between the engine nozzle and the lower surface of the wing leads to an increase in the angle of the jet stream deviation. We have identified those tail section zones of the flap, which require special execution to operate at temperatures above 400 °C.The impact of the jet stream on aircraft's drag in the cruising configuration has been analyzed, as well as the scheme of engine arrangement on the aircraft's electrically dependent systems. We have shown the absence of the impact of the jet stream on the aircraft's drag in the cruising configuration, the reduction of fuel consumption at cruising modes, as well as the favorable impact exerted on the electrically dependent systems due to the significant reduction of gas-dynamic losses along the power plant tract.Ways to modernize the transport aircraft type of An-70 have been proposed to ensure its superiority in its clas

Improving Aircraft Fuel Efficiency by Using the Adaptive Wing and Winglets

Improving the aircraft's fuel efficiency is one of the main requirements for prospective and modernized aircraft. This paper reports the assessment of change in aerodynamic quality resulting in the improved fuel efficiency of a long-range aircraft when using promising means to enhance aerodynamic quality. These means include the abandonment of the mechanization of wing edges and conventional controls through the use of an adaptive wing, the artificial laminarization of the flow around the elements of a glider, the application of winglets. The abandonment of conventional wing controls and wing mechanization is predetermined by the need to ensure a seamless surface of the glider elements to prevent the premature turbulization of the flow that consequently leads to a decrease in the profile drag of an aircraft. The use of winglets is aimed at reducing inductive drag. Determining a change in the aircraft's fuel efficiency would make it possible to estimate a change in the operating costs during its life cycle.The study employed the known modular software complex «Integration 2.1». The engineering and navigational calculation was performed for a typical flight profile of a long-range aircraft. The possibility of reducing fuel consumption by up to 20 % has been shown. The largest impact on the decrease in fuel consumption is exerted by the flow laminarization on the surface of the glider elements; the reduction in fuel consumption was 17.1 %. The abandonment of mechanization and ailerons decreases fuel consumption by 3.9 %, while the abandonment of ailerons, slats, and flaps reduces fuel consumption by 0.4, 1.5, and 0.4 %, respectively. The use of spiroid winglets made it possible to reduce fuel consumption by 1.95

The Modernization Concept of Aircraft An-26 and An-140 Based on the Use of A Hybrid Power System

This paper reports a modernization concept of aircraft An-26 and An-140 based on the use of a hybrid basic propulsion system (HBPS). The study object is the aircraft of transport and passenger categories in the weight dimension from 20 to 25 tons. The analysis of the ways of modernization has shown that under the new market conditions two directions in the development of light aircraft «Antonov» become relevant. The first is the modernization of the existing fleet of An-26, the second is the construction of an An-140T ramp transport variant based on the An-140 aircraft. One of the considered ways of such modernization is to equip the aircraft with hybrid basic propulsion systems consisting of the gas-turbine and power electric motors, which drive the rotation of the propeller.The use of HBPS makes it possible to optimize the operation of the gas-turbine engine over a narrow traction-speed range ‒ only for the cruising section of the flight. This makes it possible to design a GTE with high fuel and weight efficiency. In this case, noise and harmful emissions could be significantly lower.The analysis has been given of existing aviation hybrid propulsion systems with recommendations on the choice of the optimal scheme to modernize aircraft An-26 and An-140. It is proposed to solve the task by choosing the option of a basic propulsion system with a moderate degree of hybridization, based on the well-established engine TV3-117VMA-SBM1.That improves the flight range of An-26 and An-140 with a payload capacity of 4.5‒5 tons by 1.4‒1.7 times, respectively.The results obtained confirm the correctness of the proposed modernization concept. The analysis results demonstrate a significant improvement in the flight characteristics of the aircraft, as well as compliance with current and projected environmental standards. The results reported could be recommended for the practical modernization of aircraft An-26 and An-14