Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance Constraints

Körpe, Durmuş Sinan; Kanat, Öztürk Özdemir

doi:10.1155/2019/3050824

Cited by 7 publications

(7 citation statements)

References 27 publications

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“…CLmax) accordingly to this are support this situation. When y plus 1 (Korpe and Kanat, 2019) results is evaluated, it is seen that the decrease in the lift coefficient of the wing starts at 20° angle of attack. According to the results, as y plus increases, the stall angle of the wing decreases to 14 degrees.…”

Section: Resultsmentioning

confidence: 99%

Başlangıç y plus Değerinin Etkileri: γ-Reθ SST Türbülans Modeli Kullanılarak 3D NACA 4412 Kanadının Sayısal Analizi

Körpe¹,

Kanat²,

Oktay³

2019

European Journal of Science and Technology

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In this numerical study, the effects of the initial y plus, which is a dimensionless wall distance, on the results of aerodynamic coefficients of designed a wing using NACA 4412 airfoil are investigated. For this purpose, the wing is designed and external flow analysis is carried out according to constant altitude. ANSYS Fluent, which is a Computational Fluid Dynamics (i.e. CFD) program and solves the problems according to the Finite Volume Method (i.e. FVM), is used for external flow analysis. Pressure-based method is used for numerical studies. Thus, the differences of coefficients on the wall, which are the results of the change in the initial y plus, are calculated ideally. Because of one of the best methods to solve the problems on transition zone, γ-Reθ SST turbulence model is used for this study. Using this model for each analysis, first element heights (i.e. the distance to the nearest wall) are calculated according to 9 different y plus (i.e. 1, 5, 10, 30, 45, 60, 75, 90, 105). According to the first element heights, the inflation layers are created on the wing and the 3D control volumes are formed along the boundary region. To be more comprehensible, orthogonal quality-skewness values, expressing the quality of control volumes, are presented for each boundary. The changes in lift coefficients and drag coefficients on the same wing according to these 9 different y plus are presented numerically. In addition, obtained results are evaluated and as described in the literature, it is observed that to calculate the aerodynamic forces with the γ-Reθ SST turbulence model is directly proportional to the initial y plus. As a consequence, this paper demonstrates that there are obvious differences detection of separation and determination of reattach region of flow occurring on the wing according to the initial y plus.

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Section: Resultsmentioning

confidence: 99%

Başlangıç y plus Değerinin Etkileri: γ-Reθ SST Türbülans Modeli Kullanılarak 3D NACA 4412 Kanadının Sayısal Analizi

Körpe¹,

Kanat²,

Oktay³

2019

European Journal of Science and Technology

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“…(2) [32,33], V So is the stall speed (m/s), HP is the generated horsepower (hp), W is the maximum take-off weight of the aircraft (N), η p is the propeller efficiency, g is the gravitational constant (N), d to is the take-off distance (m), and P o is the power delivered by the propeller (W). The stall speed of the aircraft is the minimum speed at which a particular aircraft must fly at to satisfy (Lift > Take-off weight) and, therefore, stay aloft.…”

Section: Wing Design Calculationsmentioning

confidence: 99%

“…The Oswald efficiency acts as a correction factor which represents the changes in drag and lift of a three-dimensional wing aircraft, in comparison with an ideal wing having the same aspect ratio and an elliptical lift distribution [3]. Many parameters have been assumed and given in the literature to obtain the dimensional geometries of the wing [3,23,32,33,35,37], as presented in Table 4.…”

Section: Wing Design Calculationsmentioning

confidence: 99%

Design of an unmanned aircraft system for high-altitude 1 kW fuel cell power system

Reid

Albayati

2021

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A proton exchange membrane (PEM) fuel cell is particularly considered as a prime power supply for a fuel cell-powered unmanned aircraft system (UAS) as it possesses a very high-power density in comparison with other fuel cell types, hence a high potential to be used for high altitude long endurance (HALE) UAS flights. This paper will focus on examining the design requirements for the UAS-based 1 kW PEM fuel cell for high altitude operation (10–11 km), which can be correlated into a quantitative data to produce a design constraints diagram. The maximum take-off mass, endurance, and geometries for potential UAS design are estimated. Four different geometrical design profiles are developed and presented. The resulting geometries are analysed and the design parameters of the estimated 1 kW design yielded an aircraft of maximum take-off mass 34.8 kg, wingspan of 10.4 m, cruising speed 20 m/s, stall speed 11.23 m/s, and maximum endurance of 4 h. The constraint diagram deploys these assumptions as well as values generated through the design calculations to form a possible design of which the 1 kW UAS falls slightly outside of the possible design space; this is due to the minimum thrust-to-weight ratio required to achieve the desired service ceiling; however, further alterations and adjustments on the design and mission requirements are provided to place the design of the UAS within the possible design space.

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“…M ECON is calculated for each segment of the cruising phase by using SQP algorithm of the MATLAB toolbox. The main reason for the selection of this algorithm is the fact that it requires the least number of gradient evaluations and the number of iterations (Körpe and Kanat, 2019). Figure 2 depicts the flowchart of the optimization process.…”

Section: Aircraft Performance Model Accuracymentioning

confidence: 99%

Minimization of aircraft fuel consumption subjected to arrival time constraint

Gilani

Körpe

2020

AEAT

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Purpose This paper aims to minimize aircraft fuel consumption during the cruise phase when the flight is subjected to a specific time of arrival for different weights and distances. Design/methodology/approach The approach adopted herein uses sequential quadratic programming algorithm from MATLAB optimization toolbox, which includes a mathematical model of a jet airliner based on the Base of Aircraft Data as a function evaluator, to find out the impact of meet-time of arrival constraints on fuel consumption. The cruising speeds at predefined segments and the altitude are defined as the design variables. Findings The algorithm determines the optimum cruise altitudes and speeds for minimum fuel consumption in the case of no time constraints, also, for different time constraints where the flight time shall be reduced by increasing speed and lowering the altitude in most of the investigated cases. Practical implications The algorithm computes the optimum speed and the altitude according to different flight scenarios with the meet-time of arrival constraints for minimum fuel consumption which affects the direct operating cost of the flight. The algorithm might greatly help in decision-making for the meet-time of arrival operations. Originality/value Developing an algorithm to optimize the speed and the altitude of an aircraft based on weight and range for minimization of fuel consumption. It is a pioneer study in the literature that deals with the effect of meet-time constraints on fuel consumption.

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Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance Constraints

Cited by 7 publications

References 27 publications

Başlangıç y plus Değerinin Etkileri: γ-Reθ SST Türbülans Modeli Kullanılarak 3D NACA 4412 Kanadının Sayısal Analizi

Başlangıç y plus Değerinin Etkileri: γ-Reθ SST Türbülans Modeli Kullanılarak 3D NACA 4412 Kanadının Sayısal Analizi

Design of an unmanned aircraft system for high-altitude 1 kW fuel cell power system

Minimization of aircraft fuel consumption subjected to arrival time constraint

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