Wing and propeller aerodynamic interaction through nonlinear lifting line theory and blade element momentum theory
01 Jan 2018-Vol. 233, pp 00027
TL;DR: In this article, a computational methodology of aerodynamic interaction between propeller and wing is described, and the influence of propeller model to wing is simulated as contribution of higher dynamic pressure and change of angle of attack behind the propeller.
Abstract: In this paper a computational methodology of aerodynamic interaction between propeller and wing is described. Presented work is focused on development of quick and accurate tool. Lifting line theory (LLT) with nonlinear airfoil characteristic is used to solve a finite span wing aerodynamic to predict downwash and lift distribution respectively. Blade element momentum theory (BEM) is used as a computational tool for estimating total thrust, torque, axial and tangential velocity distributions. Model of slipstream development is considered. Influence of propeller model to wing is simulated as contribution of higher dynamic pressure and change of angle of attack behind the propeller.
Citations
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01 Jan 2019
TL;DR: In this article, different types of wings are computed by low and high-fidelity methods to compare their aerodynamic characteristics and the goal of optimization is minimization of aerodynamic drag.
Abstract: In this article different wings are computed by low and high-fidelity methods to compare their aerodynamic characteristics. Thanks to the unusual properties of the wing with the bell-shaped lift distribution, several general geometrical variants of the wings were calculated and their results are presented in this work. Three general wings are assumed and their geometry is defined as rectangular, trapezoidal and elliptical. Airspeed, total lift force, shape of airfoil and root chord are defined, and bending moment is assumed as a surrogate model for wing weight. The goal of optimization is minimization of aerodynamic drag.
3 citations
01 Sep 1958
1 citations
01 Jan 2019
TL;DR: In this paper, a small airplane is redesigned by using a distributed electrical propulsion (DEP) system and the design procedure is focused on the reduction of fuel consumption in cruise regime with constrained parameters of take-off/landing.
Abstract: In this paper, a small airplane is redesigned by using a distributed electrical propulsion (DEP) system. The design procedure is focused on the reduction of fuel consumption in cruise regime with constrained parameters of take-off/landing. In this case, a one half wing area compared to an original airplane is used. Take-off distance and minimum airspeed for landing is achieved by distributed propellers mounted on the leading edge of the wing. These propellers induce velocity on the wing and thereby increase local dynamic pressure, thus the required lift force can be reached with smaller wing area. Moreover, the distributed propellers are assumed as folded in cruise regime to minimize drag when the main combustion engine provides sufficient power.
1 citations
01 Jan 2021
TL;DR: In this paper, the authors focused on the usage of distributed electric propulsion (DEP) in order to increase the aerodynamic efficiency of a ten-seater aircraft by using lifting line theory with blade element momentum theory.
Abstract: This paper is focused on the usage of distributed electric propulsion (DEP) in order to increase aerodynamic efficiency. A ten seats aircraft is used as a case study. New design uses the existing fuselage, tail and turboprop engine, only wing is completely redesigned. The cost function for the design procedure consists of two parts. The first one is aerodynamic efficiency, which has a primary impact on fuel consumption, and the second one is weight of the wing. Lifting line theory with blade element momentum theory is used to design a wing geometry with DEP. Optimal geometry is also verified by CFD simulation. The estimation of the wing weight is needed for the second part of the cost function. This was done by the design of elementary wing parts under CS-23 regulation. The wing is assumed as full-aluminium with two spars. The main goal of this optimization is to redesign the wing for a given range and save as much fuel as possible.
01 Jan 2021
TL;DR: In this paper, an aerodynamic and wing structure is investigated by low-fidelity methods using Bell-shaped lift distribution, which leads to lower aerodynamic drag than elliptical lift distribution for a given lift force and root bending moment.
Abstract: In this paper, an aerodynamic and wing structure is investigated by low-fidelity methods Bell-shaped lift distribution was rediscovered in the last decade as a perspective alternative to traditional wing design This leads to lower aerodynamic drag than elliptical lift distribution for a given lift force and root bending moment Root bending moment is used as a surrogate model of wing structure weight It is relatively raw simplification introduced by Prandtl to estimate the weight of the spar as a main part of the wing structure For a more accurate wing weight estimation, the main parts of the wing are dimensioned under CS-23 regulation in this work The design procedure starts with defining the elementary parameters of the wing shape (chord/twist distribution, wingspan) After geometry generating a non-linear lifting line is used to calculate aerodynamic characteristics for all regime, determined from the flight envelope The dimensions of a spar, ribs and skin are calculated in the next step of the procedure for given bending moment, load and torque moment distribution The structure of the wing is assumed as a two-spar, manufactured by aluminum A target of design is to find out the shape of the wing for given weight The solution is verified by CFD calculation
References
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01 Dec 1954
TL;DR: In this paper, the authors investigated the effectiveness of a wing equipped with large-chord plain flaps and auxiliary vanes in rotating the thrust vector of two large-diameter propellers through the large angles required for vertical take off and low-speed flight.
Abstract: Report presenting an investigation of the effectiveness of a wing equipped with large-chord plain flaps and auxiliary vanes in rotating the thrust vector of two large-diameter propellers through the large angles required for vertical take off and low-speed flight. The semispan model was equipped with a 60-percent-chord flap, a 30-percent-chord flap, and two large-diameter overlapping propellers. Results regarding static thrust conditions, tests with forward speed, and application of results are provided.
13 citations
"Wing and propeller aerodynamic inte..." refers background in this paper
...Wind tunnel results show higher aerodynamic efficiency when propeller is mounted in the front of the wing [10], [11]....
[...]
08 Jan 2018
TL;DR: In this paper, Kestrel simulation tools are used to investigate the mutual interference between the propeller and wing of C130J aircraft, and the influence of installed propeller flow-fields on the wing aerodynamic (pressure coefficient and local lift distribution) are investigated.
Abstract: Kestrel simulation tools are used to investigate the mutual interference between the propeller and wing of C130J aircraft. Only the wing, nacelles, and propeller geometries are considered. The propulsion system modelled is a Dowty six-bladed R391 propeller mounted at inboard or outboard wing sections in single and dual propeller configurations. The results show that installed propeller configurations have asymmetric blade loadings such that downward-moving blades produce more thrust force than those moving upward. In addition, the influence of installed propeller flow-fields on the wing aerodynamic (pressure coefficient and local lift distribution) are investigated. The installed propeller configuration data are compared with the non-installed case, and the results show that propeller effects will improve the wing’s lift distribution. The increase in lift behind the propeller is different at the left and right sides of the propeller. In addition, the propeller helps to delay the wing flow separation behind it for tested conditions of this work. Finally, the results show the capability of Kestrel simulation tools for modeling and design of propellers and investigates their effects over aircraft during conceptual design in which no experimental or flight test data are available yet. This will lead to reducing the number of tests required later.
6 citations
"Wing and propeller aerodynamic inte..." refers methods in this paper
...To solve propeller wing interaction using CFD is performed in [12]....
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01 Sep 1958
1 citations
"Wing and propeller aerodynamic inte..." refers background in this paper
...Wind tunnel results show higher aerodynamic efficiency when propeller is mounted in the front of the wing [10], [11]....
[...]