Determination of aerodynamic characteristics of the X-wing–fuselage layout for an interceptor UAV
DOI:
https://doi.org/10.54858/dndia.2025-21-8Keywords:
aerodynamic characteristics, aerodynamic quality, unmanned aerial vehicle, X-wing, aerodynamic layout, interferenceAbstract
Based on parametric analysis, the aerodynamic characteristics of the isolated X-wing, fuselage, and X-wing–fuselage configuration were determined depending on the V-shape angle Q and the taper h. The study was conducted by numerical modeling in the Ansys software package.
During the modeling, the interference of the wing and fuselage was estimated. For this purpose, the aerodynamic characteristics of the isolated wing, fuselage, and their combination were determined.
The flow of viscous compressible gas was described by the system of Navier–Stokes equations, supplemented by the continuity and energy equations. To solve the system of Navier–Stokes equations, the control volume method based on the integral form of the conservation laws was implemented in the Ansys CFX software package. The implementation of the method is a division of the computational domain into elementary volumes. At the same time, the integral form of the conservation laws does not impose strict restrictions on the shape of the cells (volumes), which allows calculations to be performed on both structured and unstructured grids. An unstructured computational grid requires a larger number of cells than a structured one, but has a clear advantage in the automated construction and approximation of complex geometry.
The studies were conducted for a flight speed of 100 m/s under standard atmospheric conditions at the Earth's surface.
As a result of the study, it was determined that the greatest aerodynamic quality is the X-wing-fuselage layout with a V-shaped angle Q = 30 °, narrowing h = 1. At the same time, the gain in aerodynamic quality can be up to 40% depending on the angle of attack compared to the wing with parameters Q = 10 °, h = 1. And when compared with the layout with an X-wing with Q = 45 °, h = 1, the increase in aerodynamic quality is up to 11% depending on the angle of attack. The layout with geometric parameters of the wing Q = 45 °, h = 1 is recommended for attack UAVs used to destroy ground targets. For an interceptor UAV, it is recommended to use an X-wing with Q = 45 °, h = 1, despite the lower aerodynamic quality. The article presents the dependences of the KL coefficient, which characterizes the mutual interference effect of the wing and fuselage.
References
John R. Spreiter. Aerodynamic properties of cruciform-wing and body combinations at subsonic, transonic and supersonic speeds / Spreiter John // Technical note – Washington.: Ames Aerànautical Laboratory Moffett Field. – №1897, 1949. – Р. 1-34.
John R. Spreiter. A theoretical study of the aerodynamics of slender cruciform-wing arrangements and their wakes / Spreiter John, Sacks Alvin // Technical report – Washington.: Ames Aerànautical Laboratory Moffett Field. – №1296, 1957. – Р. 1-35.
Leroy Spearman. Aerodynamic characteristics in pitch of a series of cruciform-wing missiles with canard controls at a mach number of 2.01 / Spearman Leroy // Technical note – Washington.: Ames Aerànautical Laboratory Moffett Field. –
№ D-839, 1961. – Р. 1-41.
А. В. Розин. Пространственное обтекание оперенного тела сверхзвуковым потоком идеального газа /
Розин А.В. // Изв. АН СССР. МЖГ. – М.: – 1983, № 1. С. 185-187.
Бураго Н.Г. Метод расчёта аэродинамических коэффициентов летательных аппаратов с крыльями в схеме X, имеющими малый размер / С.Г. Бураго // Труды МАИ. – М. : МАИ. – Вып. №72, 2014. – С. 1-16.
M. Miller, J. Burkhalter. Wing-wing interference effects for cruciform missiles / Miller M., Burkhalter J. // 4th Applied Aerodynamics Conference 09 June 1986 - 11 June 1986 San Diego,CA,U.S.A. https://doi.org/10.2514/6.1986-1772/
Tuling, S., Dala, L., Toomer, C. "Lee-side flow structures of very low aspect ratio cruciform wing–body configurations" / Tuling S., Dala L., Toomer C. // Journal of Spacecraft and Rockets – American Institute of Aeronautics and Astronautics, 2013. – Vol. 50, No. 6 – С. 1134 – 1149.
S. Deng, T. Xiao. Numerical Simulation of a Flexible X-Wing Flapping-Wing Micro Air Vehicle / Deng S., Xiao T // AIAA JOURNAL – Vol. 55, No. 7, July 2017.С. 2295 – 2306.
The Investigation on Aerodynamic Performance of the X-Wing Tail-Sitter VTOL MAV. Wei Tang, Bifeng Song, Yu Cao та інш. // AIAA AVIATION Forum 35th AIAA Applied Aerodynamics Conference 5-9 June 2017, Denver, Colorado. DOI: 10.2514/6.2017-3750.
Ansys CFX-Solver Theory Guide. Release 2025 R2. Canonsburg, PA: ANSYS, Inc., 2025. 392 p.
