Aerospace Science and Technology
Sahel Alasvand; Mostafa Kazemi; Mahmood Mani
Abstract
The noise of wind turbines is mainly of aerodynamic origin and is caused by the impact of the flow on the turbine blade. Therefore, improving the behaviour of the flow around the turbine and reducing aeronoise can result in reducing its annoying noise. In the first step of this research, a suitable serration ...
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The noise of wind turbines is mainly of aerodynamic origin and is caused by the impact of the flow on the turbine blade. Therefore, improving the behaviour of the flow around the turbine and reducing aeronoise can result in reducing its annoying noise. In the first step of this research, a suitable serration is selected according to the physics of the flow, and then it is installed on the leading edge of the blade in such a way that it does not cause the power loss of the turbine. All the studies have been done experimentally in the wind tunnel and with the help of power, pressure and air velocity measurements in the wake and in the different free stream velocities. The results showed that the pressure fluctuations in the model equipped with a serrated blade have decreased by 4-9% on average in different areas compared to the simple Savonius. On the other hand, the results of the frequency analysis of the anemometer sensors also showed that in the dominant frequencies, the serration caused the range of phenomena to decrease. These results were obtained in such a way that the power measurement showed that the maximum power value of the turbine equipped with serrated blade experienced an increase of nearly 19%. On the other hand, the velocity profile in the wake also shows a greater deficit in the flow around the modified Savonius, which confirms the decrease in the output momentum from the turbine and consequently the increase in power.
Aerospace Science and Technology
Mohammad Hassan Pachenari
Abstract
Flexible ropes have wide-ranging applications in aerospace engineering, yet accurately measuring their motion state without disrupting dynamic characteristics remains a challenge. This study introduces a visual measurement method aimed at precisely assessing flexible rope motion to support the development ...
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Flexible ropes have wide-ranging applications in aerospace engineering, yet accurately measuring their motion state without disrupting dynamic characteristics remains a challenge. This study introduces a visual measurement method aimed at precisely assessing flexible rope motion to support the development and validation of an accurate cable dynamics model. Addressing non-uniform movement speeds attributed to the rope's large length-diameter ratio, a novel tether edge segmentation operator is proposed to delineate motion blur regions into exposure beginning and ending time tethers. This operator enhances accuracy over existing centerline extraction methods, particularly in asymmetric motion blur regions. The proposed approach not only resolves accuracy issues during high-speed motion but also leverages the camera's inherent image acquisition frame rate, reducing system complexity and cost. Validation of the material point tracking algorithm through mathematical and physical simulations underscores its effectiveness in monitoring any point on the tether. Furthermore, verifying the tether dynamics model through the absolute nodal coordinate method highlights the novelty and significance of this research in advancing aerospace engineering applications.
Ali Heydari; Seid H. Dr. Pourtakdoust
Volume 5, Issue 2 , June 2008, , Pages 51-56
Abstract
Conventional magnetic attitude control methodologies require several orbital periods to accomplish the required attitude maneuvers due to the existence of an uncontrollable axis, namely the local Earth’s magnetic field vector. Since in some attitude maneuver missions the elapsed time is of critical ...
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Conventional magnetic attitude control methodologies require several orbital periods to accomplish the required attitude maneuvers due to the existence of an uncontrollable axis, namely the local Earth’s magnetic field vector. Since in some attitude maneuver missions the elapsed time is of critical importance, those time-consuming controllers are not satisfactory and we need a much faster controller to achieve the maneuver in a fraction of an orbit. In this research the attitude slew maneuver using magnetic torquers is formulated as a time optimal problem and solved through the calculus of variations. The resulted controller is shown to be very fast in forcing the attitude to converge to the desired condition.
Seyed Hamid Jalali Naini
Volume 6, Issue 2 , June 2009, , Pages 55-61
S. Shokrollahi
Volume 3, Issue 2 , June 2006, , Pages 61-66
Abstract
A linear, aeroelastic analysis of a low aspect ratio swept back trapezoidal wing modeled as a cantilever plate is presented. An analytical and numerical formulation for both the aerodynamic forcing and structural response of the wing was developed. The analytical model uses a three dimensional time domain ...
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A linear, aeroelastic analysis of a low aspect ratio swept back trapezoidal wing modeled as a cantilever plate is presented. An analytical and numerical formulation for both the aerodynamic forcing and structural response of the wing was developed. The analytical model uses a three dimensional time domain vortex lattice aerodynamic method. A Rayleigh-Ritz approach has been used to transfer equations into a modal domain in order to solve equations of motion. The theoretical results are consistent with numerical results for low aspect ratio rectangular wings and experimental data reported by other investigators for delta wings.
Mahdi Mohseni; ???? ????????
Volume 7, Issue 2 , September 2010, , Pages 69-79
Abstract
There are a number of systems in which supercritical cryogenic fluids are used as coolants or propellant fluids. In some modern military aircraft, the fuel is pressurized above its critical point and used as a coolant to remove heat from the aircraft engine. Accurate prediction of heat transfer coefficients ...
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There are a number of systems in which supercritical cryogenic fluids are used as coolants or propellant fluids. In some modern military aircraft, the fuel is pressurized above its critical point and used as a coolant to remove heat from the aircraft engine. Accurate prediction of heat transfer coefficients to turbulent flows of supercritical fluids is essential in design of such systems. One of the most challenging parts in mathematical modeling of this phenomenon is the turbulence modeling. The turbulence modeling, like other aspects of the supercritical fluid flows, seems to be highly affected by the large variations of the fluid properties. A two dimensional CFD code has been developed in this study and a number of the Low Reynolds Number (LRN) k-e turbulence models have been examined. Both flow conditions corresponding to the heat transfer enhancement and deterioration have been studied. The results appear to be quite sensitive to the choice of the turbulence model, especially in the deteriorated regime of heat transfer. The turbulence model assisting the two-dimensional numerical model of the present study to best fit the experiments has been determined for both cases of the enhanced and deteriorated heat transfer. That is while the jump in the wall temperature occurring in the deteriorated regime of heat transfer is over- predicted by the present numerical code regardless of the turbulence model used.
Iman Mohammadzaman; Hamiderza Momeni
Volume 8, Issue 2 , September 2011, , Pages 69-75
Abstract
In this paper a new nonlinear guidance law with finite time convergence is proposed. The second order integrated guidance and control loop is formulated considering a first order control loop dynamics. By transforming the state equations to the normal form, a finite time stabilizer feedback linearization ...
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In this paper a new nonlinear guidance law with finite time convergence is proposed. The second order integrated guidance and control loop is formulated considering a first order control loop dynamics. By transforming the state equations to the normal form, a finite time stabilizer feedback linearization technique is proposed to guarantee the finite time convergence of the system states to zero or a small neighborhood of zero before the final time of the guidance process. However, some feedback quantities such as high order LOS rate derivatives are not directly measurable and therefore, a finite time observer is proposed to have a finite time output feedback guidance law for more practical applications. Simulation results show the effectiveness of the proposed guidance law.
Nematollah Ghahramani; Abolqasem Naghash; Farzad Towhidkhah
Volume 5, Issue 3 , July 2008, , Pages 99-105
Abstract
In this paper, a new incremental predictive guidance method based on implicit form of velocity to be gained algorithm is proposed. In this approach, the generalized incremental predictive control (GIPC) approach is applied to the linearized model for compensating the guidance error. Instead of using ...
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In this paper, a new incremental predictive guidance method based on implicit form of velocity to be gained algorithm is proposed. In this approach, the generalized incremental predictive control (GIPC) approach is applied to the linearized model for compensating the guidance error. Instead of using the present state in popular model based predictive controller (MPC), in the new method both previous and present states are utilized. GIPC approach introduces a feedback action including the weighted difference of the process states and the summation of the control action increments. To evaluate the robustness and performance of the proposed approach, the parameter uncertainties of the guidance and control are considered and a comparison with standard GPC is performed by extensive computer simulations. The results show a significant improvement in the robustness as well as tracking performance for the perturbed initial value of velocity to be gained or the reference signal.
Seid H. Dr. Pourtakdoust
Volume 3, Issue 3 , September 2006, , Pages 113-123
R. Rashidi; A. Karami mohammadi Karami mohammadi; F. Bakhtiari nejad Bakhtiari nejad
Volume 5, Issue 4 , December 2008, , Pages 145-159
Abstract
This paper presents the effect of preload on nonlinear dynamic behavior of a rigid rotor supported by two-lobe aerodynamic noncircular journal bearing. A finite element method is employed to solve the Reynolds equation in static and dynamical states and the dynamical equations are solved using Runge-Kutta ...
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This paper presents the effect of preload on nonlinear dynamic behavior of a rigid rotor supported by two-lobe aerodynamic noncircular journal bearing. A finite element method is employed to solve the Reynolds equation in static and dynamical states and the dynamical equations are solved using Runge-Kutta method. To analyze the behavior of the rotor center in the horizontal and vertical directions under different operating conditions, the dynamic trajectory, the power spectra, the Poincare maps and the bifurcation diagrams are used. From this study, results show how the complex dynamic behavior of this type of system comprising periodic, -periodic and quasi-periodic responses of the rotor center varies with changes in preload values by considering two bearing aspect ratio. The results of this study contribute to a better understanding of the nonlinear dynamics of two-lobe aerodynamic noncircular journal bearing system.
A. Abedian
Volume 3, Issue 4 , December 2006, , Pages 167-176
Abstract
Several traditional stopping criteria in Genetic Algorithms (GAs) are applied to the optimization process of a typical laminated composite plate. The results show that neither of the criteria of the type of statistical parameters, nor those of the kinds of theoretical models performs satisfactorily in ...
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Several traditional stopping criteria in Genetic Algorithms (GAs) are applied to the optimization process of a typical laminated composite plate. The results show that neither of the criteria of the type of statistical parameters, nor those of the kinds of theoretical models performs satisfactorily in determining the interruption point for the GA process. Here, considering the configuration of the history curve of the maximum objective or fitness value with generation number, a Logarithmic Performance Criterion (LPC) is introduced as a stopping criterion for optimization of composite plates. The results highlight the advantages of LPC in performing sufficiently smooth (no noise), requiring reasonable number of generations, less parameter dependency, lower need for conservative assumption, on-line controllability, wide scope applicability, and reasonably easy application in engineering decision-making problems.
Bahman Jahromi; M.R. Soltani; M. Masdari
Volume 9, Issue 1 , March 2012
Abstract
The goal of this investigation is to study the effect of wing sweep angle on the horizontal wing-body- tail configurations in subsonic flow. For this purpose, a series of wind tunnel tests were conducted on a model having a moveable horizontal tail and a wing planform with different sweep angles. Tests ...
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The goal of this investigation is to study the effect of wing sweep angle on the horizontal wing-body- tail configurations in subsonic flow. For this purpose, a series of wind tunnel tests were conducted on a model having a moveable horizontal tail and a wing planform with different sweep angles. Tests were performed at different tail deflection angles. Static surface pressure distribution over the suction side of wing was measured for both static and dynamic changes of the tail angles of attack. The strength of the vortices over different wings was compared and the effect of tail deflection on the wing flow field was investigated. It is seen that the wing sweep angle is a dominant factor for the strength of the vortices over the wing and hence the maneuverability of the vehicle.
Darwish Alshaddadi; M.H. Arvan; A.R. Vali
Volume 9, Issue 2 , September 2012
Abstract
An accurate calibration of inertial measurement unit errors is increasingly important
as the inertial navigation system requirements become more stringent.
Developing calibration methods that use as less as possible of IMU signals has
...
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An accurate calibration of inertial measurement unit errors is increasingly important
as the inertial navigation system requirements become more stringent.
Developing calibration methods that use as less as possible of IMU signals has
6-DOF gimballed IMU in space-stabilized mode is presented. It is considered
as held stationary in the test location incorporating 15 different error sources,
including accelerometers bias, scale factor error, gyros drift, initial alignment
error, and IMU case installation error. Using kinematic relations between IMU
platform, IMU body, and IMU platform centered inertial reference frame, six
differential equations of the only system-level IMU velocity and gimbal angle
are derived. Then the extracted model is validated for error-free case using Sim-
Mechanics MATLAB SIMULINK tools to evaluate the introduced mathematical
model. Simulation results for 24 hours point out the correctness of the developed
model in error-free case. The IMU error analysis methodology incorporates
! andquot;# !
gimbal angle measurements taken during one and a half hour with 9 platform attitudes
test to estimate IMU error sources. Without the need to install IMU at rotating
table, different platform attitudes are achieved using consequent rotations
of gimbals. IMU error sources estimation is accomplished off-line. This paper
describes the design and test results of a new gimballed IMU calibration method
without using a rotating table, and error model development methodology formulated
to support the design and test of EKF algorithm and two optimal smoothers:
forward-backward and RTS. Results obtained from EKF implementation indicate
that the technique is comprehensive and accurate, and requires less specialized
test equipments. Also, results show that constant states are not smooth-able. Ad-
علیرضا نکویی
Volume 10, Issue 1 , March 2013
Abstract
The main goal of this article is to implement the MSG-3 process in structure field for an SSI component of b747 aircraft. This process is expected toincrease the ease of aircraft maintenance and its safety level. MSG-3 logic took a top-down or consequence of failure approachmeaning that MSG-3 reduces ...
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The main goal of this article is to implement the MSG-3 process in structure field for an SSI component of b747 aircraft. This process is expected toincrease the ease of aircraft maintenance and its safety level. MSG-3 logic took a top-down or consequence of failure approachmeaning that MSG-3 reduces the maintenance cost and upgrades safety. Moreover, it cansignificantly help saving thetime and providing financial benefits for the design approach and the developmentof maintenance programing. In this study, in correspondence with the SLD of MSG-3,an SSI component is selected and itsfatigue crack growth analysis is investigated. The approach of this study is to use the FEM and fractography for the purpose of exploring the loading.
Farid Shahmiri
Volume 10, Issue 2 , September 2013
Abstract
Hover performance of a twin-rotor test model in terms of rotor overlap sweep, blade collective pitch, and blade tip speedwasexaminedexperimentally.The experimental setup consisted of two three-bladed rotors (tandem rotor configuration) with a diameter of1,220 mm and constant chord of 38 mm, giving a ...
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Hover performance of a twin-rotor test model in terms of rotor overlap sweep, blade collective pitch, and blade tip speedwasexaminedexperimentally.The experimental setup consisted of two three-bladed rotors (tandem rotor configuration) with a diameter of1,220 mm and constant chord of 38 mm, giving a blade aspect ratio of 16.05. The blades were of a rectangular planform with NACA 0012 cross-sections with no twist or taper. In this model, the front rotor was fixed on the fuselage and the rearrotor could move longitudinally for tests up to about40% rotor overlap sweep.To accurately examine the hover performance, thrust, power required, power loading (PL), and figure of merit (FM) responses were measured usinga central compositetest plan. Furthermore, four quadratic polynomialswere fitted to all responses, necessary for a better understanding of the main effects and interactions. The results clearlyshowed that significant interactions between variables are evident and therefore overlapping at constant collective pitch reduces thrust much more than reducingthe power required. Moreover, the results showed that, for the twin-rotor system,the maximumefficiency in hover (i.e., maximum power loadingof 14.6kg/kW) is obtainedfor no overlapped rotors at low values of disc loading and blade tip speed.Experimental measurements of thetwin-rotor hover performance based on a central composite plan andinteraction analysis were the main contributionsstated in the current work.Results for the twin-rotor test model can be generalized to actual tandem helicopters through the Reynolds number transformation technique and some modifications.
Hossein H. Shahverdi; A.S Nobari; H Bahrami Torabi
Volume 11, Issue 1 , June 2017
Abstract
The aim of this paper is to provide an aeroelastic computational tool which determines the induced wing loads during flapping flight. For this purpose, a Finite Element (FE) code based on a four-node plate bending element formulation is developed to simulate the aeroelastic behavior of flapping wings ...
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The aim of this paper is to provide an aeroelastic computational tool which determines the induced wing loads during flapping flight. For this purpose, a Finite Element (FE) code based on a four-node plate bending element formulation is developed to simulate the aeroelastic behavior of flapping wings in low incompressible flow. A quasi-steady aerodynamic model is incorporated into the aeroelastic model for predicting the aerodynamic loads. In order for the validation of the present tool, the modal and dynamic response analyses of a rotating flat plate under pure flapping motion are firstly examined and the effect of dynamic stiffness on the plate response, due to the presence of shortening terms in the equations of motion, is also investigated. Finally, the aeroelastic analysis of an insect-like wing under a specified motion is carried out and the induced loads including shear force and bending moment at the wing root are determined. The obtained results signify the contribution of wing structural elasticity to the induced loads.
Mohammad Pasandidefard Fard
Volume 2, Issue 1 , March 2005, , Pages 7-14
Volume 4, Issue 4 , December 2007, , Pages 7-17
Aerospace Science and Technology
Ali Ansari; Jafar Eskandari Jam; Ali Alizadeh; Mohsen Heydari Beni; Majid Eskandari Shahraki
Abstract
This study was designed to investigate the ballistic behavior of ceramic-reinforced aluminum composite plates numerically and experimentally and to present an optimal sample design. The parameters studied were ceramic reinforcement percentage and type of matrix alloy. This study used the matrix alloys ...
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This study was designed to investigate the ballistic behavior of ceramic-reinforced aluminum composite plates numerically and experimentally and to present an optimal sample design. The parameters studied were ceramic reinforcement percentage and type of matrix alloy. This study used the matrix alloys 6061, 7075, and 5083. The percentage of ceramics used in this study is 15, 30, and 45% by weight. The samples are in three thicknesses of 20, 25, and 30 mm. 27 simulated samples were numerically analyzed with Abaqus finite element software in this study based on existing ballistic protection criteria, one then determines the optimal numerical sample. Using the squeeze casting method, a laboratory sample has been made and experimentally tested to evaluate the numerical results. Lastly, the numerical analysis and the experimental test were compared and the optimal sample was determined.
Prapat Suntivarakorn; Kazuo Matsuuchi
Volume 1, Issue 1 , October 2004, , Pages 9-15
Abstract
To discover the nonlinear characteristics of pipe flow, we simulated the flow as a sum of many vortex rings. As a first step, we investigated the nonlinear interaction among a maximum of three vortex rings. The pipe wall was replaced by many bound vortices. A free vortex ring moves right or left according ...
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To discover the nonlinear characteristics of pipe flow, we simulated the flow as a sum of many vortex rings. As a first step, we investigated the nonlinear interaction among a maximum of three vortex rings. The pipe wall was replaced by many bound vortices. A free vortex ring moves right or left according to the radius, and that of a particular radius keeps the initial position. The energy of a free vortex ring, except when it is close to a wall, coincides with that without boundaries. Two vortex rings of equal radii always show a repeated overtaking process. In the case of three vortex rings, they show a wide variety of behavior. For certain combinations of radii and the axial spaces among them, the motion, which seems to be very complex, is limited on a curved surface in three-dimensional space whose axes correspond to the three radii. It was found that this simplicity comes from the momentum conservation law, and also that its direction depends on the energy contribution calculated from free vortex rings. Our results elucidate the nonlinear behavior among many vortices.
Abolqasem Naghash
Volume 2, Issue 3 , September 2005, , Pages 9-18
Abstract
This work is an example of application of nonlinear programming to a problem of three-dimensional trajectory optimization for multistage launch vehicles for geostationary orbit missions. The main objective is to minimize fuel consumption or equivalently to maximize the payload. The launch vehicle considered ...
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This work is an example of application of nonlinear programming to a problem of three-dimensional trajectory optimization for multistage launch vehicles for geostationary orbit missions. The main objective is to minimize fuel consumption or equivalently to maximize the payload. The launch vehicle considered here, Europa-II, consists of 5 thrust phases and 2 coast phases. Major parameters of the coast arcs such as inclination, eccentricity and true anomaly of attachment points are not prespecified and should be found in optimization problem. The fairing should be jettisoned whenever aerothermal flux falls below a certain value. An aerodynamic heating constraint for atmospheric part of the flight is also considered. The problem is solved by direct collocation method and results are compared with those in Ref. [1] where an indirect multiple shooting method with an inner loop for parameter optimization is used. Advantages of present work with respect to methods used in that reference are then discussed.
Mohammad Reza Dr. Soltani
Volume 2, Issue 4 , December 2005, , Pages 9-26
Abstract
Details of pressure distributions, on a two dimensional airfoil oscillating in pitch through stall, in a 0.8 0.8 m low-speed wind tunnel are presented. Pitching occurred about the airfoils quarter-chord axis. Pitch rate, Reynolds number, and oscillation amplitudes were varied to determine the effects ...
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Details of pressure distributions, on a two dimensional airfoil oscillating in pitch through stall, in a 0.8 0.8 m low-speed wind tunnel are presented. Pitching occurred about the airfoils quarter-chord axis. Pitch rate, Reynolds number, and oscillation amplitudes were varied to determine the effects on pressure and lift distributions. It was found that mean angle of attack and pitching amplitude had strong effects on the flow field hence pressure distribution in the immediate vicinity of the airfoil leading edge, . For pressure ports located at , the aforementioned effects were not strong and seemed that during the oscillatory motions the flow was mostly separated. This investigation shows weak unsteady effects when the maximum dynamic angle of attack was below that of the static stall; i.e. . For higher angles of attack, strong unsteady effects appear that depend on the mean angle of attack, frequency and amplitude of the oscillation. Dynamic stall and dynamic reattachment contribute to a favorable effect of unsteadiness on the surface pressure signature and hence the mean lift coefficient which increases as compared to the steady state one.
M. R. Khoshravan; A. Hamidi
Volume 4, Issue 1 , March 2007, , Pages 9-16
Abstract
The fracture and crack growth of mechanical structures is a usual phenomenon which is due to the application of tensile, cyclic loading or thermal stresses on the structure. So introducing of methods to prevent the crack growth is useful. Afterward, one of the repairing methods of crack growth, consisting ...
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The fracture and crack growth of mechanical structures is a usual phenomenon which is due to the application of tensile, cyclic loading or thermal stresses on the structure. So introducing of methods to prevent the crack growth is useful. Afterward, one of the repairing methods of crack growth, consisting to make a hole in the crack tip to elimi-nate the sharp corners, was explained. This method is frequently used in air and space industry. The drilling can be done in various locations. Three locations in the crack tip for the hole were considered. In the first, the hole was situated in the left of the crack tip (Location A). In the second one, it sited in the center of the crack tip (Location B) and in the last one; it sited in the right site of the crack tip (Location C). The study of resistance against crack growth was based on the comparison of these three systems. We have analyzed the influence of theses stopping holes, their diameters and their lo-cations on the fracture toughness. The specimens were made of Al 7075-T6 alloy and they had the shape of the Compact Tension specimen. The solicitation was a mono-tonic tensile loading in the Mode I of fracture. The stress intensity factor and the criti-cal load versus to the crack length of the test bars were computed. Numerical method was carried out by finite element method using Ansys software. Following this nu-merical analysis, fracture experimentation was carried out on the tensile machine to evaluate the influence of the stopping hole on the critical load of initiation of the crack growth. In result the best location of the hole increased 54% the critical load and the location which gived the weakest result showed 11% of increasing of the load. Thus in result of this research the best location of the stopping hole and its diameter were ob-tained to increase the life of the mechanical pieces.
S. Rowghani; Masoud Mirzaei; Reza Kamali
Volume 7, Issue 1 , March 2010, , Pages 9-17
Abstract
The method of lattice boltzmann equation(LBE) is a kinetic-based approach for fluid flow computations. In the last decade, minimal kinetic models, and primarily the LBE, have met with significant success in the simulation of complex hydrodynamic phenomena, ranging from slow flows in grossly irregular ...
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The method of lattice boltzmann equation(LBE) is a kinetic-based approach for fluid flow computations. In the last decade, minimal kinetic models, and primarily the LBE, have met with significant success in the simulation of complex hydrodynamic phenomena, ranging from slow flows in grossly irregular geometries to fully developed turbulence, to flow with dynamic phase transitions. In the present work, a computer code, based on the LBM has been developed to show the capability of the method for simulating fluid flows. The confined flow around a cylinder with square cross-section mounted inside a plane channel (blockage ratio B=1/8) was investigated in detail with LBM method. The largest Reynolds number chosen was Re=300 based on the maximum inflow velocity and the chord length of the square cylinder. The LBE was built up on the D2Q9 model and the single relaxation time method called the lattice-BGK method. Both velocity profiles and integral parameters such as drag coefficient and Strouhal number were investigated.
A. Hossein Gholami; Mohammad Haeri; Ali Reza Doodman Tipi
Abstract
With the advancement of science and technology, ultra-light drones with electric propulsion hold many applications. In these drones, the electric motor is the primary consumer of energy. Thus, having an accurate model of power consumption of the motor, propeller, and battery set can play an essential ...
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With the advancement of science and technology, ultra-light drones with electric propulsion hold many applications. In these drones, the electric motor is the primary consumer of energy. Thus, having an accurate model of power consumption of the motor, propeller, and battery set can play an essential role in determining the drone's flight duration. This paper aims to model the behavior of two sets of motor and propeller in the wind tunnel. One motor set has a low speed, and the other has a medium speed. Also, after the above modeling, the models of speed-power, thrust-power, and speed-efficiency are extracted. Then, a lithium polymer battery with a minimal voltage drop for the drone is used. In the operating speed, the flight time of the desired drone is obtained. The power consumption, speed, and thrust models are obtained using interpolation. Finally, the motor that consumes less power and has a longer flight time is selected.
