Wing and propeller aerodynamic interaction through nonlinear lifting line theory and blade element momentum theory

Hospodář, Pavel; Klesa, Jan; Nikola, Žižkovský

doi:10.1051/matecconf/201823300027

Cited by 4 publications

(3 citation statements)

References 2 publications

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“…Lift coefficient and local chord and is computed by following terms: Then a Kutta-Joukovsky law is used to determine local circulation . This concept was verified in previous work [7].…”

Section: Lifting Line Theorysupporting

confidence: 81%

Comparison of aerodynamic characteristics provided by wing with bell shaped lift distribution and generalized wings

Hospodář

Drábek

2019

MATEC Web Conf.

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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.

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“…Lift coefficient and local chord and is computed by following terms: Then a Kutta-Joukovsky law is used to determine local circulation . This concept was verified in previous work [7].…”

Section: Lifting Line Theorysupporting

confidence: 81%

Comparison of aerodynamic characteristics provided by wing with bell shaped lift distribution and generalized wings

Hospodář

Drábek

2019

MATEC Web Conf.

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“…Combination of lifting line theory and Blade element theory is used to estimated propeller wing interaction. This methodology was designed and validated [5]. Development of slipstream propeller velocity is assumed in this method.…”

Section: Aerodynamic Of Wing With Depmentioning

confidence: 99%

“…The weight of batteries, engines, electrical controllers and fuel are assumed in the optimization procedure which is using response surface optimization. Design of propeller and their characteristics are computed by Blade element momentum theory and the propeller-wing interaction is calculated by lifting line theory in a non-linear form [5]. It offers a design of multi-propeller wing with high lift devices.…”

Section: Introductionmentioning

confidence: 99%

Design of distributed propulsion system for general aviation airplane

2019

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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.

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Multidisciplinary design of the wing for aircraft preliminary design purposes

Hospodář

Drábek

2021

IOP Conf. Ser.: Mater. Sci. Eng.

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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.

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Wing and propeller aerodynamic interaction through nonlinear lifting line theory and blade element momentum theory

Cited by 4 publications

References 2 publications

Comparison of aerodynamic characteristics provided by wing with bell shaped lift distribution and generalized wings

Comparison of aerodynamic characteristics provided by wing with bell shaped lift distribution and generalized wings

Design of distributed propulsion system for general aviation airplane

Multidisciplinary design of the wing for aircraft preliminary design purposes

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