Aerodynamic Characteristics Research Articles

Applying Machine Learning in CFD to Study the Impact of Thermal Characteristics on the Aerodynamic Characteristics of an Airfoil

Applying Machine Learning in CFD to Study the Impact of Thermal Characteristics on the Aerodynamic Characteristics of an Airfoil

Comparative Assessment on Unsteady Aerodynamics of Thin and Thick Airfoils Subjected to Pitching Motion

This article presents the comparison between the unsteady flow characteristics of thick (t/c ≥ 6%) and thin (t/c ≤ 6%) airfoils performing pitching motion at Reynolds number Re = 3.6 × 10 5 . For the analysis, the considered airfoils are NACA 0012 as thick and symmetric airfoil and GOE 417A as thin and highly cambered airfoil. The analysis in this study is restricted to only two airfoils because from the preliminary investigations, similar aerodynamic characteristics with slight variation in their flow field development under same conditions were observed. The influence of reduced frequency, pitching amplitude and mean angle of attack on the airfoil’s aerodynamic performance in terms of instantaneous force coefficients is thoroughly investigated. Further, the flow surrounding the airfoils is also investigated. It is noticed that the aforementioned parameters substantially affect the instantaneous force coefficients (both qualitatively and quantitatively). Under certain conditions, the formation of reverse Karman vortex street was observed indicating airfoil’s thrust force generation. It must be noted that the conditions where the thrust force generation occurs for thick and symmetric airfoils like NACA 0012 are quite different from that of thin and cambered airfoils like GOE 417A. Additionally, a drastic change in the flow field around the airfoils is observed under similar conditions. For NACA 0012 airfoil, the formation and convection of the Leading Edge Vortex (LEV) under certain conditions has detrimental effects on its aerodynamic characteristics as it encourages early flow separation. However, the same cannot be true for thin and highly cambered airfoils like GOE 417A. Under the similar conditions with negligible variation, the LEV contributes toward providing extra suction over the GOE 417A airfoil’s suction side. This significantly improves airfoil’s aerodynamic characteristics.

Analysis of frost layer growth behavior on cryogenic surfaces in ultralow dew point environments by experimental tests and numerical simulations

Maintaining an ultralow dew point is essential for the operation of transonic cryogenic wind tunnels, as it significantly influences aerodynamic characteristics. Even in extremely dry conditions, minute quantities of frost can form on cryogenic surfaces, which compromises data quality. Conducting experiments on frost desublimation in such ultralow dew point environments poses significant challenges due to the demanding experimental conditions. Therefore, this study aimed to explore the desublimation characteristics of cryogenic surfaces in ultralow dew point environments and to address the challenges of experimental investigations under such extreme conditions. Initially, the study experimentally investigated frost formation by assessing the impact of various factors, such as temperature and water vapor content. It was observed that the type of frost formed depended on the water vapor content, and altering the surface temperature influenced the growth region of the frost crystals. The irregular growth of the frost layer on low-temperature surfaces was evident, as temperature markedly affected both the growth rate and the diffusion direction of frost formation. Moreover, the process of trace water frost formation was simulated using a dispersive multiphase model, predicting the frost layer's thickness. The numerical results suggest that the frost layer is micrometers thick, with a minimum thickness of 20 μm. A nonlinear relationship was identified between frost growth and dew point level. This research lays the groundwork for a deeper understanding of desublimation characteristics in ultralow dew point environments and for further investigation of low-temperature heat and mass transfer phenomena.

Aerodynamic Design and Performance Analysis of Mars Ascent Vehicles

The mid-lift-to-drag ratio vehicle possesses larger dimensions and enhanced aerodynamic characteristics compared to the conventional sphere-cone reentry vehicle, suggesting its suitability for crewed missions to Mars. This research employs Computational Fluid Dynamics (CFD) simulations to investigate the influence of varying geometries on the aerodynamic properties of mid-lift-to-drag ratio vehicles. The aerodynamic analysis of four distinct configurations demonstrates that a bow shock wave forms on the windward side, leading to a reduction in flow velocity and subsequent increases in pressure and temperature after the shock wave. The simulation results for the four configurations in both laminar and turbulent flow conditions, specifically using the Shear-Stress Transport (SST) model, reveal that turbulence results in higher aerodynamic heating compared to laminar flow. Moreover, the aerodynamic heating is greater at a 40° angle of attack than at 30°. In this study, the transition phenomena of four geometric configurations are examined using the k-ω-γ transition model. The findings indicate a pronounced transition to turbulence on the windward side of the Ellipsled 2.00-0.25 and Hammerhead-Nominal configurations under conditions of high Reynolds numbers, transitioning from laminar to turbulent flow. The investigation into the aerodynamic characteristics of mid-lift-to-drag ratio vehicles holds substantial importance for ensuring the safety and success of Martian reentry missions, highlighting the critical nature of aerodynamic behavior in the context of space exploration.

Aeroacoustic characteristics of a strut-braced high-lift device

The aerodynamic and aeroacoustic performance of a strut-based high-lift device were evaluated and demonstrated for six different strut models. The primary objective of the study was to investigate the impact of strut modifications on reducing noise levels. The aerodynamic characteristics are presented with the aid of surface pressure distribution on the airfoil that remained consistent across all the tested configurations. The aeroacoustic results are presented as the near-field surface pressure fluctuations and far-field noise measurements to attain a profound comprehension of the noise generation mechanism. Although the Albatros strut exhibited the greatest reduction in tonal noise, the directivity pattern and the overall sound pressure level of the radiated noise demonstrated that the medium height strut configuration can achieve noise reduction of up to 8 dB. The near-field unsteady surface pressure measurements are suggestive of harmonic oscillations. The coherence studies carried out have shown a decrease in the tonal coherence for the small height strut configuration while the velocity field measurements performed in the wake of the high-lift device show no significant variation in flow patterns between different strut configurations.

Transonic Flutter of Skin Panels Pinned at the Center

This work is a numerical and experimental study of transonic panel flutter. Two configurations were explored: clean and pinned geometry. The former is a panel clamped on all sides, while the configuration with pin also includes an additional constraint in the middle of the panel. This case study was inspired by the skin-panel design used for Skylon, a single-stage-to-orbit concept vehicle. In Skylon, a series of discrete supports are used to stiffen thinner skin panels to maximize the payload; thus, there is a need to explore the dynamic stability of this configuration also in the transonic regime. To this end, a panel clamped on all sides and with a pin in the center was tested in the transonic wind tunnel, where time-accurate displacement measurements were performed using laser sensors. From the analysis of experiments and numerical simulations, transonic flutter appeared to be a one-way type of interaction, where the aerodynamic pressure characteristic is not affected by the structure deformation. This is due to small panel displacements, typically two orders of magnitude smaller than the panel thickness. Higher natural modes, with a frequency close to the aerodynamic fluctuating pressure, are directly excited. Generally, the additional constraint in the center does not seem to add significant benefits in terms of dynamic stability in the transonic regime. A numerical parametric study showed that for external Mach numbers ranging approximately between 0.8 and 1.2, flutter oscillation amplitude is the largest for low Mach speeds.

Numerical Study on the Influence of Separation Time Sequence on the Initial Thermal Separation

The process of separating stages is crucial for multistage rockets, directly influencing the success of the launch plan. Different separation timing methods alter the flow field structure within the interlevel zone at separation, influencing the separation of the two-stage rockets. This paper employs the SST k-ω turbulence model to investigate the structure of the flow field and its aerodynamic and motion characteristics under different nozzle baffle opening and separation times, taking into account variable properties, supersonic compressibility, and the upstream–downstream interference. First, we examined the standard flow field structure, considering the engine jet, the lateral jet between stages, and the disturbance from the external supersonic inflow. Then, we discussed the displacement characteristics and axial force coefficient curves of the first and second steps of the separation process. Finally, we explored the impact of baffle opening and separation times on the flow field structure and axial force coefficients of the two stages at the onset of separation. For the flow field structure, a delay in the baffle opening and separation moment led to a gradual increase in downstream and separation regions until they stabilized after a certain range. However, the axial force coefficients displayed different behavior before and after the design point.

Multi-objective configuration and evaluation of dynamic virtual inertia from DFIG based wind farm for frequency regulation

Modern power systems are gradually evolving into low-inertia systems due to the integration of high penetration of renewable energy and power electronic equipment. For the natural inertia on the rotor, doubly-fed induction generator (DFIG) based wind farms are expected to provide inertia support for systems. The paper proposed an analytical model of DFIG with df/dt inertia control for studying frequency dynamics, and investigates the optimal design of virtual inertia from wind farms, as well as its equivalent inertia contribution to system. The inertia response differences between DFIG and synchronous generator (SG) are discussed and analyzed for the first time, and then to accurately describe the frequency response with low cost, an analytical model of DFIG with inertia control is developed considering wind turbine aerodynamic characteristics. The explicit expression of virtual inertia provided by DFIG is derived according to the kinetic energy equilibrium, and the key factors that dominate the magnitude of virtual inertia are illustrated. Based on the system frequency response model including wind farms, taking the system frequency nadir (SFN) and the time of reaching nadir (ToN) as targets, a multi-objective optimal configuration model of virtual inertia is constructed and solved through MOPSO. The time domain simulations of a generic two machine four bus system and modified IEEE 9-bus test system are both performed in MATLAB/Simulink, the accuracy and efficiency of our proposed DFIG model on system frequency dynamics research are demonstrated, the pareto frontiers of virtual inertia configuration under different working conditions are optimized and analyzed as well as the impacts of different parameters on inertia evaluation.

Physico-Mechanical Properties of Pumpkin Seeds in the Context of Drying Processes

The paper highlights the significance of the drying process in post-harvest cucurbit seed treatment technology. To improve the effectiveness of drying high-moisture seeds, a plant construction design was introduced, incorporating the concept of providing varied heat distribution to a vigorously agitated seed layer. The paper validates the necessity of refining the dimensional, frictional, and aerodynamic properties of pumpkin seeds to determine the optimal operating modes for the proposed dryer. (Research purpose) To identify the physical and mechanical properties of pumpkin seeds by defining their dimensional, frictional and aerodynamic characteristics. (Materials and methods) The study employs one-factor experimental research methods with subsequent statistical data processing. An experimental study was conducted on the physical and mechanical properties of Volzhskaya Grey pumpkin seeds possessing a standard moisture content ranging between 9.3 and 9.7 percent. Well-known laboratory apparatuses, namely the «conical tank» and the «inclined plane», were used to determine the natural repose angle and to enhance the accuracy of friction coefficients determination. For analyzing the aerodynamic properties of the seeds, the K-293 Petkus air separator was employed. (Results and discussion) Research methods were developed and experimental plants were described. It was established that with a probability confidence level of 0.95, the static friction coefficients of pumpkin seeds on a solid steel sheet, a perforated steel sieve and on rubber are 0.473, 0.418, 0.481, respectively, and the dynamic friction coefficients under the identical conditions are measured as 0.331, 0.293, 0.337. The average angle of natural repose is found to be 22 degrees, the midsection area is 97.94 square millimeters, the soaring velocity is 7.083 meters per second, the windage coefficient stands at 0.196 and the aerodynamic drag coefficient is 0.136. (Conclusions). The assumption that enhancing the drying efficiency of vegetable seeds can be achieved by implementing a diverse thermal energy supply to continuously moving mass inside the apparatus is confirmed, provided that the seeds do not stick together in layers resulting in blockage of the coolant flow. An improved design of the dryer configurations has been developed and, to validate its optimum design and technological specifications, an in-depth analysis of the seeds' dimensional, frictional, and aerodynamic attributes has been conducted.

Scale effect on wave planing performance of amphibious aircraft at constant speed

Scaled model testing is commonly recognized as a valuable approach for predicting aircraft performance in the aeronautical applications. However, challenges arise in the case of wave planing events for amphibious aircraft due to difficulties in satisfying the scaling laws of Reynolds number and Froude number simultaneously in a water tank. Therefore, it is important to evaluate the scale effect of regular wave planing process for amphibious aircraft. In this study, by fixing the Froude number, five geosim cases with different scale factors (1/1, 1/2, 1/4, 1/8 and 1/16) are carried out based on the Reynolds-Averaged Navier–Stokes equations (RANS) framework. The hydrodynamic and aerodynamic characteristics at different scales are respectively examined in detail through several physical results, including acceleration, pressure, shear force, velocity and free surface elevation. Comparative analyses among all scaled models reveal that the aerodynamic and hydrodynamic performance both monotonously change with the scale factor, yet the proportion of aerodynamic and hydrodynamic loads remains within a reasonably small range. Furthermore, the results indicate that the scale effect primarily stems from the lack of similarity in Reynolds number, thus resulting in the discrepancies of boundary layer, wave surface elevation and flow separation between the scale model and prototype.

Решение задач тепло- и массообмена в технических объектах на основе компьютерного моделирования

The purpose of the work is to carry out the necessary theoretical research and practical research for the possibility of using modern methods of ventilation of premises or using these methods in various technical installations of a nuclear reactor. The study is based on the study of the aerodynamic characteristics of an object (a crowded ship room or a nuclear reactor) at reference points. The scientific novelty of the work consists in the use of patented technologies (originally proposed by the author, and then patented by the responsible executor of the topic, a hydroaerodynamic transformer) and equipment for solving these problems for use in nuclear energy. The results of scientific research may be of interest to a wide range of specialists and scientists, mainly for nuclear energy. The research methods are based on the methods of similarity theory (Reynolds similarity criterion) and differential equations. A mathematical approach to modeling the system under study and heat and mass transfer processes occurring in an industrial nuclear power plant or spatial objects of ship premises has been formed. A general methodological approach and a scheme for the research installation of a nuclear reactor have been developed, and a model based on second-order regression equations has been constructed. Based on mathematical models and confirmed theoretical results, the distribution of gas-liquid flows is empirically visualized in experimental studies. The intensification of heat and mass transfer in the fuel assembly of a nuclear reactor is considered.

Six-dimensional force/torque sensor for aerodynamic characteristic study of high-speed train with different wind angles under stationary tornado.

Researchers conducted an investigation by tornado simulator to study the impact of wind angle on the aerodynamic characteristics of a reduced (1:150) high-speed train model using six-dimensional force/torque sensor. The reduced scale model size can match the relative size relationship between high-speed train and tornado vortex core in real condition. Results show that the wind angle affects the mean value and standard deviation of the force and moment coefficient of the high-speed train at the same radial position. The variations of the mean value and standard deviation of the pitching moment coefficient of the high-speed train carriage model at 60°and 90°are different from that at other wind angles. The variations of the mean value of the pitching moment coefficient of the high-speed train head model at 0°, 15°and 30°are different from that at other wind angles. The variations of the standard deviation of the pitching moment coefficient of the high-speed train head model at 60°,75°and 90°are different from that at other wind angles. This research will help the further study of the operation safety of high-speed train in the event of a tornado impacting a high-speed train network.

Стандартизированная модель огнестрельного проникающего ранения глаза без внутриглазного инородного тела (открытая травма глаза типа В)

The purpose of the work was to creation of a standardized model of a gunshot penetrating wound of the eye without an intraocular foreign body. The wound was inflicted by a specially made projectile. The shot was fired from an air rifle with modulated pumping of a compression pump. A set of shells (specially made and standard) was used, and they were weighed with laboratory analytical scales. The velocity of the projectiles was recorded with a ballistic chronograph. The parameters of the shot were previously worked out on a bar of ballistic plasticine, then on 11 heads of cadaver rabbits (22 eyes). 4 series of experiments were performed. We studied the flight speed of projectiles, the nature of their flight and the meeting with the target (plasticine, cadaver eyes). The nature of the eye injury (type of injury) was analyzed depending on the energy (based on speed and mass) and aerodynamic characteristics of the projectile. According to preliminary results, a decision was made to modernize the standard projectile. A projectile has been upgraded to meet external ballistic characteristics to create a standardized model of a gunshot penetrating wound to the eye without an intraocular foreign body. The specified wound parameters were as follows: the distance from the muzzle of the air rifle to the target was 30 cm. Shots were fired into the sclera projection area 2–3 mm from the limb. The parameters of the shot were as follows: the mass of the upgraded projectile was 0.54‒0.55 g, two pumps of the rifle's air pump. The parameters used provided a speed range of 40–46 m/s. In an experiment on laboratory animals, pathogenetic factors characteristic of a gunshot injury to the eye were reproduced. This made it possible in 100 % of cases to reproduce an injury simila to a gunshot penetrating injury to the eye without an intraocular foreign body (an open eye injury of type B). Keywords: pneumatic installation, standardized experimental model, gunshot open globe injury

Liquid film morphology and aerodynamic performance of a high-speed train under wind-rain environments

The performance degradation of railway vehicles operating in wind-rain environments has attracted widespread attention in recent years. This work focuses on a numerical study of the liquid film morphology and train aerodynamic performance under wind-rain environments. The train aerodynamic model in wind-rain environments is set up using Eulerian–Lagrangian methodology, and validated with existing experimental results. The liquid film morphology of the train is discussed using the Lagrangian wall film (LWF) model. The aerodynamic characteristics such as liquid film morphology, surface pressure, shear stress, velocity contour, aerodynamic coefficient, etc., are then discussed in detail. The results show that, when the rainfall duration is constant, the liquid film becomes thicker as rainfall intensity is greater. As crosswind becomes stronger, the thickness of liquid film gathered on the train roof decreases, and the liquid film on the windward and leeward sides of the train becomes thicker. The shear stress on the train in wind-rain environments is obviously greater than that exposed to crosswind environments. For the reason of rainfall, the skin friction coefficient on the train also increases, which will have an impact on the frictional resistance. Rainfall would lead to an increase in the aerodynamic coefficient of trains operating in crosswind environments, especially for lift force coefficient and pitch moment coefficient.

Experimental study on the aerodynamic characteristics of combined angle transmission tower subject to skew wind

The transmission towers served as crucial carriers in the process of power transmission. The combined angle transmission tower of dual-angle steel with cruciform section are relatively a novel type of angle tower, which is being more widely used in transmission lines. The studies on aerodynamic characteristics of combined angle tower in skewed wind are limited. In this paper, the wind tunnel tests are conducted to investigate the aerodynamic characteristics of the combined angle tower, and the high frequency force balance (HFFB) test is introduced to obtain the transverse and longitudinal forces on the tower using the direct force measurement (DFM) method. The drag coefficients and wind load-distribution factors of the combined angle tower are obtained from the wind tunnel tests, and the effects of interference and tower leg spacing on the wind loads of the tower legs are fully explored. It can be found that the aerodynamic coefficients and drag coefficients of the combined angle steel tower leg tend to decrease with the increase of interference members and it also decreases with the decrease of the tower leg spacing. The test wind load-distribution factors of the isolated leg are generally larger than those defined by seven typical codes (e.g., US, EU, Japanese, and Chinese codes) and significantly exceed the code-specified values under partial wind angles. The observations obtained from this study may provide helpful guidance on the wind-resistant design of this relatively novel type of combined angle tower.

Thermal effect induced by viscous dissipation on characteristics of aerodynamic foil journal bearing with aero-thermo-elastic coupling

In aero–thermo–elastic analysis, aerodynamic foil bearings are one of the most representative components that involve strong coupling among microscale shear flow, aerodynamic heating, and elastic foil deformation. Researches on the role of aerodynamic heating in bearings are really inadequate. This study clarifies the effect of thermal behavior induced by viscous dissipation on the characteristic of an aerodynamic foil journal bearing (AFJB) with a rotational speed of 4 × 104–8.0 × 104r/min and an eccentricity ratio of 0.4–0.8. The results indicate that the thermal effect induced by viscous dissipation significantly affects the aerodynamics of shear flow and the dynamic response of elastic foils in the AFJB. The inherent thermal effect induced by viscous dissipation strengthens the inherent viscosity-temperature effect and weakens the pulsation of static pressure while intensifying the temperature increase of the shear flow. The dynamic response of the elastic foils in the solid domain is closely associated with the behavior of shear flow in the fluid domain. The static pressure and temperature elevation increase with the rotational speed and eccentricity ratio owing to strengthened hydrodynamic effects. The effect of thermal behavior induced by viscous dissipation on the aerodynamic and thermal characteristics of the shear flow becomes significant at high rotational speeds and eccentricity ratios. The load capacity and peak temperature elevation increase with the rotational speed and eccentricity ratio. In the solid domain, the thermal effect induced by viscous dissipation negligibly affects the deformation of the elastic foils because the variation in the temperature increase is insignificant, thus resulting in insignificant variations in the properties of the gas film. This study elucidates the impact of aerodynamic heating, especially the thermal effect induced by viscous dissipation, on the aero–thermo–elastic field in bearings and the performance of the bearings. The results of this study serve as basic design guidelines for AFJBs and can be used to optimize the operation security.

Numerical simulation of windsurfing sail aerodynamics: Insights into forces and flow characteristics

In windsurfing, the sail is the primary source of propulsive force. Due to the unique shape and structure, the aerodynamic performance of a windsurfing sail is not well understood. This study aims to investigate the aerodynamic performance of a windsurfing sail under various angles of attack and sail heights using steady Reynolds-averaged Navier–Stokes simulations. The simulations were validated with wind tunnel measurements. The study finds that the local maximum lift coefficient and stall angle are different at different sections along the sail height. Further investigations on the pressure distributions and sectional flow fields indicate that the different sectional lift coefficients and stall are significantly influenced by the geometric profiles and orientations of the luff pocket. The sectional geometric profile consists of a reduced camber near the sail tip, which is prone to flow separation. Thus, flow separation first occurred at the sail tip with increasing angle of attack, then extended towards the sail foot. During flow separation, a recirculation region was found on the suction side of the sail, leading to a reduction in lift and increase in drag. The findings of this study provide insights into the aerodynamic forces and flow characteristics of windsurfing sails, which can be applied to improve sail design and performance.

Design, Modeling, and Control of a Composite Tilt-Rotor Unmanned Aerial Vehicle

Tilt-rotor unmanned aerial vehicles combine the advantages of multirotor and fixed-wing aircraft, offering features like rapid takeoff and landing, extended endurance, and wide flight conditions. This article provides a summary of the design, modeling, and control of a composite tilt-rotor. During modeling process, aerodynamic modeling was performed on the tilting and non-tilting parts based on the subcomponent modeling method, and CFD simulation analysis was conducted on the entire unmanned aerial vehicle to obtain its accurate aerodynamic characteristics. In the process of modeling the motor propeller, the reduction of motor thrust and torque due to forward flow and tilt angle velocity is thoroughly examined, which is usually ignored in most tilt UAV propeller models. In the controller design, this paper proposes a fusion ADRC control strategy suitable for vertical takeoff and landing of this type of tiltrotor. The control system framework is built using Simulink, and the control algorithm’s efficiency has been verified through simulation testing. Through the proposed control scheme, it is possible for the composite tiltrotor unmanned aerial vehicle to smoothly transition between multirotor and fixed-wing flight modes.

The Effect of Laser-Resistant Endotracheal Tube Design on Airflow Dynamics: A Benchtop and Clinical Study.

Compare ventilation pressures of 2 endotracheal tube designs used in laser airway surgery in clinical practice and with a benchtop model to elucidate differences and understand the design elements that impact airflow dynamics. Ventilatory and aerodynamic characteristics of the laser resistant stainless-steel endotracheal tube (LRSS-ET) design and the laser resistant aluminum-wrapped silicone endotracheal tube (LRAS-ET) design were compared. Ventilatory parameters were collected for 32 patients undergoing laser-assisted airway surgery through retrospective chart review. An in vitro benchtop simulation measured average resistance and centerline turbulence intensity of both designs at various diameters and physiological frequencies. Baseline patient characteristics did not differ between the 2 groups. Clinically, the median LRAS-ET peak inspiratory pressure (PIP; 21.00 cm H2O) was significantly decreased compared to LRSS-ET PIP (34.67 cm H2O). In benchtop simulation, the average PIP of the LRAS-ET was significantly lower at all sizes and frequencies. The LRSS-ET consistently demonstrated an increased resistance, although no patterns were observed in turbulence intensity data between both designs. The benchtop model demonstrated increased resistance in the LRSS-ET compared to the LRAS-ET at all comparable sizes. This finding is supported by retrospective ventilatory pressures during laser airway surgery, which show significantly increased PIPs when comparing identically sized inner diameters. Given the equivocal turbulence intensity data, these differences in resistance and pressures are likely caused by wall roughness and intraluminal presence of tubing, not inlet or outlet geometries. The decreased PIPs of the LRAS-ET should assist in following lung protective ventilator management strategies and reduce risk of pulmonary injury and hemodynamic instability to the patient.

Learning-based modeling and control design for a coaxial helicopter with aerodynamic coupling

In this paper, a mathematical model of a coaxial helicopter with a new configuration is successfully constructed using the learning-based method. This nonlinear model can reflect the aerodynamic coupling characteristics between the two rotors of the coaxial helicopter. Compared with the traditional polynomial fitting method, this method significantly improves the integrity and robustness of the mathematical model. After multiple tune of the aircraft, we successfully completed the stable flight experiment using the designed attitude controller. By analyzing the real-time flight log, we verify the high accuracy of the coupled model trained on neural networks. The results of this research have brought important enlightenment to the field of aircraft design and control and proved the great potential of neural network in improving the accuracy of aircraft model and control efficiency.