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Journal articles on the topic 'Aerodynamics. Flight. Aerospace engineering'

Author: Grafiati

Published: 4 June 2021

Last updated: 16 February 2022

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1

Bangash, Z. A., R. P. Sanchez, A. Ahmed, and M. J. Khan. "Aerodynamics of Formation Flight." Journal of Aircraft 43, no. 4 (2006): 907–12. http://dx.doi.org/10.2514/1.13872.

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2

Zhang, Jing, Wenwen Kang, and Lingyu Yang. "Aerodynamic benefits of boundary layer ingestion for distributed propulsion configuration." Aircraft Engineering and Aerospace Technology 91, no. 10 (2019): 1285–94. http://dx.doi.org/10.1108/aeat-06-2018-0174.

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Purpose Boundary layer ingestion (BLI) is one of the probable noteworthy features of distributed propulsion configuration (DPC). Because of BLI, strong coupling effects are generated between the aerodynamics and propulsion system of aircraft, leading to the specific lift and drag aerodynamic characteristics. This paper aims to propose a model-based comprehensive analysis method to investigate this unique aerodynamic. Design/methodology/approach To investigate this unique aerodynamics, a model-based comprehensive analysis method is proposed. This method uses a detailed mathematical model of the

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3

Ghommem, M., and V. M. Calo. "Flapping wings in line formation flight: a computational analysis." Aeronautical Journal 118, no. 1203 (2014): 485–501. http://dx.doi.org/10.1017/s0001924000009325.

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AbstractThe current understanding of the aerodynamics of birds in formation flights is mostly based on field observations. The interpretation of these observations is usually made using simplified aerodynamic models. Here, we investigate the aerodynamic aspects of formation flights. We use a potential flow solver based on the unsteady vortex lattice method (UVLM) to simulate the flow over flapping wings flying in grouping arrangements and in proximity of each other. UVLM has the capability to capture unsteady effects associated with the wake. We demonstrate the importance of properly capturing

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4

Stollery, J. L. "Aerodynamics, Aeronautics and Flight Mechanics." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 211, no. 1 (1997): 63–64. http://dx.doi.org/10.1177/095441009721100102.

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5

Prothin, S., C. Fernandez Escudero, N. Doué, and T. Jardin. "Aerodynamics of MAV rotors in ground and corner effect." International Journal of Micro Air Vehicles 11 (January 2019): 175682931986159. http://dx.doi.org/10.1177/1756829319861596.

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The work presented in this paper is part of a project called ARChEaN (Aerodynamic of Rotors in Confined ENvironment) whose objective is to study the interactions of a micro drone rotor with its surroundings in the case of flight in enclosed environments such as those encountered, for example, in archeological exploration of caves. To do so the influence of the environment (walls, ground, ceiling, etc) on the rotor’s aerodynamic performance as well as on the flow field between the rotor and the surroundings is studied. This paper focuses on two different configurations, flight near the ground a

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6

Gennaretti, M., and G. Bernardini. "Aeroelastic response of helicopter rotors using a 3D unsteady aerodynamic solver." Aeronautical Journal 110, no. 1114 (2006): 793–801. http://dx.doi.org/10.1017/s0001924000001664.

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The prediction of blade deflections and vibratory hub loads concerning helicopter main rotors in forward flight is the objective of this work. They are determined by using an aeroelastic model derived through the coupling between a nonlinear blade structural model and a boundary integral equation solver for three-dimensional, unsteady, potential aerodynamics. The Galerkin method is used for the spatial integration, whereas the periodic blade response is determined by a harmonic balance approach. This aeroelastic model yields a unified approach for aeroelastic response and blade pressure predic

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Kulhánek, Robert. "Identification of a degradation of aerodynamic characteristics of a paraglider due to its flexibility from flight test." Aircraft Engineering and Aerospace Technology 91, no. 6 (2019): 873–79. http://dx.doi.org/10.1108/aeat-06-2018-0162.

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Purpose Aerodynamics of paragliders is very complicated aeroelastic phenomena. The purpose of this work is to quantify the amount of aerodynamic drag related to the flexible nature of a paraglider wing. Design/methodology/approach The laboratory testing on scaled models can be very difficult because of problems in the elastic similitude of such a structure. Testing of full-scale models in a large facility with a large full-scale test section is very expensive. The degradation of aerodynamic characteristics is evaluated from flight tests of the paraglider speed polar. All aspects of the identif

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8

Escobar-Ruiz, Alan G., Omar Lopez-Botello, Luis Reyes-Osorio, Patricia Zambrano-Robledo, Luis Amezquita-Brooks, and Octavio Garcia-Salazar. "Conceptual Design of an Unmanned Fixed-Wing Aerial Vehicle Based on Alternative Energy." International Journal of Aerospace Engineering 2019 (November 14, 2019): 1–13. http://dx.doi.org/10.1155/2019/8104927.

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This paper focuses on the aerodynamics and design of an unmanned aerial vehicle (UAV) based on solar cells as a main power source. The procedure includes three phases: the conceptual design, preliminary design, and a computational fluid dynamics analysis of the vehicle. One of the main disadvantages of an electric UAV is the flight time; in this sense, the challenge is to create an aerodynamic design that can increase the endurance of the UAV. In this research, the flight mission starts with the attempt of the vehicle design to get at the maximum altitude; then, the UAV starts to glide and bat

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9

Liu, Haojie, and Yonghui Zhao. "Efficient Training Data Generation for Reduced-Order Modeling in a Transonic Flight Regime." International Journal of Aerospace Engineering 2018 (September 12, 2018): 1–12. http://dx.doi.org/10.1155/2018/4083538.

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In this study, a time-dependent surrogate approach is presented to generate the training data for identifying the reduced-order model of an unsteady aerodynamic system with the variation of mean angle of attack and Mach number in a transonic flight regime. For such a purpose, a finite set of flight samples are selected to cover the flight range of concern at first. Subsequently, the unsteady aerodynamic outputs of the system under given inputs of filtered white Gaussian noise at these flight samples are simulated via CFD technique which solves Euler equations. The unsteady aerodynamic outputs,

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10

Zyl, L. H. van. "2D and 3D low frequency aerodynamics." Aeronautical Journal 112, no. 1136 (2008): 609–12. http://dx.doi.org/10.1017/s0001924000002578.

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Abstract Unsteady aerodynamic loads on aircraft configurations are used for aeroelastic or flight dynamic analyses. The sources for deriving these loads include strip theory aerodynamics and three-dimensional panel methods. In some applications the behaviour of the unsteady air loads as the frequency approaches zero is important, and it is well known that the behaviour of strip theory aerodynamics employing the exact circulation function differs qualitatively from that of the three-dimensional panel methods such as the subsonic doublet lattice method (DLM). Theoretical results from an earlier

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11

Rhoades, M. M., and J. Val Healey. "Flight deck aerodynamics of a nonaviation ship." Journal of Aircraft 29, no. 4 (1992): 619–26. http://dx.doi.org/10.2514/3.46210.

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12

Kornev, Nikolai. "On Unsteady Effects in WIG Craft Aerodynamics." International Journal of Aerospace Engineering 2019 (May 6, 2019): 1–14. http://dx.doi.org/10.1155/2019/8351293.

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The paper presents the analysis of unsteady forces and their influence on the aerodynamics and motion of a wing-in-ground (WIG) effect craft. Two-dimensional and three-dimensional aerodynamic models based on the potential flow are coupled with time domain simulations in the longitudinal plane. A special attention is paid to the explanation of the dynamic ground effect on both the sink and pitching motions. The influence of unsteady and quasi-steady forces on the dynamic ground effects and the craft motion is analyzed for different heights of flight.

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13

Kim, H. W., A. R. Kenyon, R. E. Brown, and K. Duraisamy. "Interactional aerodynamics and acoustics of a hingeless coaxial helicopter with an auxiliary propeller in forward flight." Aeronautical Journal 113, no. 1140 (2009): 65–78. http://dx.doi.org/10.1017/s0001924000002797.

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Abstract The aerodynamics and acoustics of a generic coaxial helicopter with a stiff main rotor system and a tail-mounted propulsor are investigated using Brown’s Vorticity Transport Model. In particular, the model is used to capture the aerodynamic interactions that arise between the various components of the configuration. By comparing the aerodynamics of the full configuration of the helicopter to the aerodynamics of various combinations of its sub-components, the influence of these aerodynamic interactions on the behaviour of the system can be isolated. Many of the interactions follow a si

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14

Marks, Tobias, Katrin Dahlmann, Volker Grewe, et al. "Climate Impact Mitigation Potential of Formation Flight." Aerospace 8, no. 1 (2021): 14. http://dx.doi.org/10.3390/aerospace8010014.

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The aerodynamic formation flight, which is also known as aircraft wake-surfing for efficiency (AWSE), enables aircraft to harvest the energy inherent in another aircraft’s wake vortex. As the thrust of the trailing aircraft can be reduced during cruise flight, the resulting benefit can be traded for longer flight time, larger range, less fuel consumption, or cost savings accordingly. Furthermore, as the amount and location of the emissions caused by the formation are subject to change and saturation effects in the cumulated wake of the formation can occur, AWSE can favorably affect the climate

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15

Mehta, U., J. Bowles, S. Pandya, et al. "Conceptual stage separation from widebody subsonic carrier aircraft for space access." Aeronautical Journal 118, no. 1209 (2014): 1279–309. http://dx.doi.org/10.1017/s0001924000009970.

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Abstract Stage separation is a critical technical issue for developing two-stage-to-orbit (TSTO) launch systems with widebody carrier aircraft that use air-breathing propulsion and launch vehicle stages that use rocket propulsion. During conceptual design phases, this issue can be addressed with a combination of engineering methods, computational fluid dynamics simulations, and trajectory analysis of the mated system and the launch vehicle after staging. The outcome of such analyses helps to establish the credibility of the proposed TSTO system and formulate a ground-based test programme for t

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16

Zhang, Qingrui, and Hugh H. T. Liu. "Aerodynamics Modeling and Analysis of Close Formation Flight." Journal of Aircraft 54, no. 6 (2017): 2192–204. http://dx.doi.org/10.2514/1.c034271.

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17

King, Rachel M., and Ashok Gopalarathnam. "Ideal Aerodynamics of Ground Effect and Formation Flight." Journal of Aircraft 42, no. 5 (2005): 1188–99. http://dx.doi.org/10.2514/1.10942.

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18

Bramesfeld, Götz, and Mark D. Maughmer. "Effects of Wake Rollup on Formation-Flight Aerodynamics." Journal of Aircraft 45, no. 4 (2008): 1167–73. http://dx.doi.org/10.2514/1.33821.

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19

Dimitriadis, G., J. D. Gardiner, P. G. Tickle, J. Codd, and R. L. Nudds. "Experimental and numerical study of the flight of geese." Aeronautical Journal 119, no. 1217 (2015): 803–32. http://dx.doi.org/10.1017/s0001924000010939.

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AbstractThe flight of barnacle geese at airspeeds representing high-speed migrating flight is investigated using experiments and simulations. The experimental part of the work involved the filming of three barnacle geese (Branta Leucopsis) flying at different airspeeds in a wind tunnel. The video footage was analysed in order to extract the wing kinematics. Additional information, such as wing geometry and camber was obtained from a 3D scan of a dried wing. An unsteady vortex lattice method was used to simulate the aerodynamics of the measured flapping motion. The simulations were used in orde

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20

Keshmiri, Shawn S., Edward Lan, and Richard Hale. "Nonlinear aerodynamics of an unmanned aircraft in wind shear." Aircraft Engineering and Aerospace Technology 89, no. 1 (2017): 39–51. http://dx.doi.org/10.1108/aeat-11-2014-0181.

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Purpose The purpose of this paper is to evaluate the accuracy of linear and quasi-steady aerodynamic models of aircraft aerodynamic models when a small unmanned aerial system flies in the presence of strong wind and gust at a high angle of attack and a high sideslip angle. Design/methodology/approach Compatibility analysis were done to improve the quality of recorded flight test data. A robust method called fuzzy logic modeling is used to set up the aerodynamic models. The reduced frequency is used to represent the unsteadiness of the flow field according to Theodorsen’s theory. The work done

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21

Cook, M. V., and M. Spottiswoode. "Modelling the flight dynamics of the hang glider." Aeronautical Journal 110, no. 1103 (2006): 1–20. http://dx.doi.org/10.1017/s0001924000004334.

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AbstractThe development of the non-linear equations of motion for the hang glider from first principles is described, including the complex geometry of control by pilot ‘weight shift’. By making appropriate assumptions the linearised small perturbation equations are derived for the purposes of stability and control analysis. The mathematical development shows that control is effected not by pilot weight shift, but by centre of gravity shift and that lateral-directional control by this means is weak, and is accompanied by significant instantaneous adverse response.The development of a comprehen

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22

Marcinkiewicz, Ewa, Zdobyslaw Jan Goraj, and Marcin Figat. "Aerodynamic and flight dynamic interaction in spin." Aircraft Engineering and Aerospace Technology 91, no. 3 (2019): 437–47. http://dx.doi.org/10.1108/aeat-01-2018-0042.

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PurposeThe purpose of this paper is to describe an integrated approach to spin analysis based on 6-DOF (degrees of freedom) fully nonlinear equations of motion and a three-dimensional multigrid Euler method used to specify a flow model. Another purpose of this study is to investigate military trainer performance during a developed phase of a deliberately executed spin, and to predict an aircraft tendency while entering a spin and its response to control surface deflections needed for recovery.Design/methodology/approachTo assess spin properties, the calculations of aerodynamic characteristics

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23

Blanchard, Robert C., Kevin T. Larman, and Christina D. Moats. "Rarefied-flow shuttle aerodynamics flight model." Journal of Spacecraft and Rockets 31, no. 4 (1994): 550–56. http://dx.doi.org/10.2514/3.26477.

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24

Tang, Wei, and Bi-Feng Song. "Transitional flight equilibrium and performance study for the X-NMRL tail-sitter VTOL MAV." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 8 (2018): 3056–77. http://dx.doi.org/10.1177/0954410018794731.

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An investigation on transitional flight equilibrium, performance analysis and parameter impacts is conducted in a conversion corridor, based on the proposed X-NMRL tail-sitter Vertical Takeoff and Landing Micro Air Vehicles (VTOL MAVs). Dependent on a propulsion model, aerodynamic model and physical control model, a nonlinear mathematical transitional model of the vehicle dynamics was constructed with consideration of the velocity, angle of attack, thrust, control surface deflection and pitching angle. The momentum theory and estimation method are applied to simulated propeller slipstream effe

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25

Gingras, D. R., and J. N. Ralston. "Aerodynamics modelling for training on the edge of the flight envelope." Aeronautical Journal 116, no. 1175 (2012): 67–86. http://dx.doi.org/10.1017/s000192400000662x.

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Abstract Aircraft upset and Loss of Control (LOC) is a leading cause of accidents in commercial and general aviation aircraft operations. A number of measures have been taken in the commercial segment to improve training and awareness of this problem and several organisations offer in-flight training to enhance awareness. In relative terms, in both commercial and general aviation sectors, the use of Full Flight Simulators (FFS) and Flight Training Devices (FTD) for this purpose is minimal. A key reason for this is the limited capability and coverage of flight models used in these devices. This

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26

Goulos, I. "Modelling the aeroelastic response and flight dynamics of a hingeless rotor helicopter including the effects of rotor-fuselage aerodynamic interaction." Aeronautical Journal 119, no. 1214 (2015): 433–78. http://dx.doi.org/10.1017/s0001924000010563.

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AbstractThis paper presents a mathematical approach for the simulation of rotor-fuselage aerodynamic interaction in helicopter aeroelasticity and flight dynamics applications. A Lagrangian method is utilised for the numerical analysis of rotating blades with nonuniform structural properties. A matrix/vector-based formulation is developed for the treatment of elastic blade kinematics in the time-domain. The combined method is coupled with a finite-state induced flow model, an unsteady blade element aerodynamics model, and a dynamic wake distortion model. A three-dimensional, steady-state, poten

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27

Ro, K., J. W. Kamman, and J. B. Barlow. "Flight mechanics of a free-wing tilt-body aircraft." Aeronautical Journal 112, no. 1137 (2008): 625–40. http://dx.doi.org/10.1017/s0001924000002608.

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Abstract The free-wing tilt-body aircraft refers to a vehicle configuration in which the wing, fuselage, and empennage are in a longitudinally articulated connection. This allows the main wing to freely rotate relative to the body, while the empennage, which is in the form of a long twin boom connected to the rear of the body, changes its incidence angle relative to the body in response to external commands. The principal advantages claimed for the configuration are short takeoff and landing capability, and reduced gust sensitivity. The aerodynamics of the free-wing tilt-body configuration has

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28

Berenger, T., D. Favier, C. Maresca, and E. Berton. "Experimental and Numerical Investigation of Rotor Aerodynamics in Forward Flight." Journal of Aircraft 34, no. 3 (1997): 394–99. http://dx.doi.org/10.2514/2.2182.

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29

Beyers, Martin E. "Interpretation of experimental high-alpha aerodynamics - Implications for flight prediction." Journal of Aircraft 32, no. 2 (1995): 247–61. http://dx.doi.org/10.2514/3.46710.

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30

Taha, Haithem E., Muhammad R. Hajj, and Philip S. Beran. "State-space representation of the unsteady aerodynamics of flapping flight." Aerospace Science and Technology 34 (April 2014): 1–11. http://dx.doi.org/10.1016/j.ast.2014.01.011.

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31

Doig, G., T. J. Barber, A. J. Neely, and D. D. Myre. "Aerodynamics of an aerofoil in transonic ground effect: numerical study at full-scale Reynolds numbers." Aeronautical Journal 116, no. 1178 (2012): 407–30. http://dx.doi.org/10.1017/s0001924000005297.

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Abstract The potential positive effects of ground proximity on the aerodynamic performance of a wing or aerofoil have long been established, but at transonic speeds the formation of shock waves between the body and the ground plane would have significant consequences. A numerical study of the aerodynamics of an RAE2822 aerofoil section in ground effect flight was conducted at freestream Mach numbers from 0·5 to 0·9, at a range of ground clearances and angles of incidence. It was found that in general the aerofoil’s lifting capability was still improved with decreasing ground clearance up until

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32

Garcia, Gonzalo, and Shahriar Keshmiri. "Adaptive and Resilient Flight Control System for a Small Unmanned Aerial System." International Journal of Aerospace Engineering 2013 (2013): 1–25. http://dx.doi.org/10.1155/2013/289357.

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The main purpose of this paper is to develop an onboard adaptive and robust flight control system that improves control, stability, and survivability of a small unmanned aerial system in off-nominal or out-of-envelope conditions. The aerodynamics of aircraft associated with hazardous and adverse onboard conditions is inherently nonlinear and unsteady. The presented flight control system improves functionalities required to adapt the flight control in the presence of aircraft model uncertainties. The fault tolerant inner loop is enhanced by an adaptive real-time artificial neural network parame

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33

Cook, M. V., and M. Spottiswoode. "Modelling the flight dynamics of the hang glider." Aeronautical Journal 109, no. 1102 (2005): I—XX. http://dx.doi.org/10.1017/s0001924000001007.

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AbstractThe development of the non-linear equations of motion for the hang glider from first principles is described, including the complex geometry of control by pilot ‘weight shift’. By making appropriate assumptions the linearised small perturbation equations are derived for the purposes of stability and control analysis. The mathematical development shows that control is effected not by pilot weight shift, but by centre of gravity shift and that lateral-directional control by this means is weak, and is accompanied by significant instantaneous adverse response.The development of a comprehen

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34

Kamaruddin, Noorfazreena, Jonathan Potts, and William Crowther. "Aerodynamic performance of flying discs." Aircraft Engineering and Aerospace Technology 90, no. 2 (2018): 390–97. http://dx.doi.org/10.1108/aeat-09-2016-0143.

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Purpose The purpose of this paper is to examine geometrical design influence of various types of flying discs on their flight performance from the aerodynamics perspective. Design/methodology/approach The lift, drag and moment coefficients of the discs were measured experimentally using a wind tunnel. Three types of golf discs and four sets of simpler parametric discs were studied to analyze and isolate the effect of design factors on these aerodynamic characteristics. Full six degree-of-freedom simulations of the discs were performed to visualize their flight trajectories and attitudes. These

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35

Dexter, P. C. "High Angle of Attack Missile Aerodynamics." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 207, no. 1 (1993): 15–19. http://dx.doi.org/10.1243/pime_proc_1993_207_241_02.

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A major influence in the aerodynamics of missiles is the significant amount of separated flow encountered for most flight conditions. This flow may be of an ordered nature, forming vortices, or random, such as encountered in wing stall. At high angles of attack the vortices of the body leeside flow may become unpredictably asymmetric, even on geometrically symmetric configurations, and their interactions with wing and tail panels can result in possible control problems. The modelling of such flows both accurately and easily is beyond present capabilities.

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36

Tai, Tsze C. "Effect of External Components on V-22 Aircraft Forward-Flight Aerodynamics." Journal of Aircraft 37, no. 2 (2000): 201–6. http://dx.doi.org/10.2514/2.2607.

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37

Theodore, Colin, and Roberto Celi. "Helicopter Flight Dynamic Simulation with Refined Aerodynamics and Flexible Blade Modeling." Journal of Aircraft 39, no. 4 (2002): 577–86. http://dx.doi.org/10.2514/2.2995.

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38

Wu, Jianghao, He Yan, Chao Zhou, and Yanlai Zhang. "Unsteady aerodynamics of a micro flapping rotary wing in forward flight." Aerospace Science and Technology 111 (April 2021): 106530. http://dx.doi.org/10.1016/j.ast.2021.106530.

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39

Kumar, R., and A. K. Ghosh. "Parameter estimation using unsteady downwash model from real flight data of Hansa-3 aircraft." Aeronautical Journal 115, no. 1171 (2011): 577–88. http://dx.doi.org/10.1017/s0001924000006217.

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Abstract The paper presents the estimation of longitudinal aerodynamic parameters from simulated as well as real flight data using an unsteady downwash model. The task of parameter estimation was accomplished using the Maximum Likelihood (ML) method in the frequency domain for the Hansa-3 aircraft. The presented work pertains to the aircraft having a semi-sweptback wing configuration, however, the work reported earlier considered a rectangular wing configuration. A simple vortex system was used to model downwash effects in the longitudinal equations of motion. First, it was established that th

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40

Shaw, S. T., and N. Qin. "Study of the aerodynamics of in-plane motion." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 215, no. 2 (2001): 89–104. http://dx.doi.org/10.1243/0954410011531790.

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A computational analysis is performed of the unsteady aerodynamics associated with the blade sections of helicopter rotors in forward flight. The unsteady flow is studied through solutions of the two- dimensional Reynolds averaged Navier-Stokes equations together with a strongly coupled two-equation model of turbulence. Two motions are studied. The first motion is that of an aerofoil subjected to harmonic in-plane oscillations. The influence of advance ratio and reduced frequency is investigated. It is shown that, in the absence of shock waves, the flow is periodic with a reduced frequency equ

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41

Sun, Xiao-Ying, Tian-E. Li, Guo-Chang Lin, and Yue Wu. "A study on the aerodynamic characteristics of a stratospheric airship in its entire flight envelope." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 5 (2017): 902–21. http://dx.doi.org/10.1177/0954410017723358.

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Aerodynamic characteristics of a stratospheric airship in its entire flight envelope, including take-off, ascending, cruising, descending, and landing, is an important part of its research topic. In this paper, experiments of wind pressure measurement on a 1/30-scale stratospheric airship model were carried out to obtain a better assessment of the aerodynamic characteristics during the cruising process. Based on the wind pressure distribution, the effects of pitch angle, yaw angle, and combined angles (pitch angle and yaw angle acted simultaneously) on the aerodynamics of the airship were anal

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42

Cosyn, P., and J. Vierendeels. "Design of fixed wing micro air vehicles." Aeronautical Journal 111, no. 1119 (2007): 315–26. http://dx.doi.org/10.1017/s0001924000004565.

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Abstract The paper describes the methodology and computational design strategies used to develop a series of fixed wing micro air vehicles (MAVs) at the Ghent University. The emphasis of the research is to find an optimal MAV-platform that is bound to geometrical constraints but superior in its performance. This requires a multidisciplinary design optimisation but the challenges are mainly of aerodynamic nature. Key areas are endurance, stability, controllability, manoeuvrability and component integration. The highly three-dimensional low Reynolds number flow, the lack of experimental database

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43

Qu, Zhengyu, Cuichun Li, Yong Hao, Feng Yan, and Yanchu Yang. "Project of high altitude balloon launched micro glider: Aircraft design, control and flight test." International Journal of Micro Air Vehicles 12 (January 2020): 175682932097995. http://dx.doi.org/10.1177/1756829320979955.

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This paper presents the design details and flight tests validation of printed circuit board fabricated micro gliders. The purpose of the micro glider is to be launched from a super pressure balloon at high altitude, glide to the target position to collect data and upload data to the staying balloon. The mission demand requires the micro glider to finish precise landing with small size and low fabrication cost. To complete this concept, we designed a PCB fabricated aircraft with limited sensors including GPS and IMU. The first part of the article describes the aerodynamic design methods. The se

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Pomin, Hubert, and Siegfried Wagner. "Navier-Stokes Analysis of Helicopter Rotor Aerodynamics in Hover and Forward Flight." Journal of Aircraft 39, no. 5 (2002): 813–21. http://dx.doi.org/10.2514/2.3001.

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Tai, Tsze C. "Effect of Midwing Vortex Generators on V-22 Aircraft Forward-Flight Aerodynamics." Journal of Aircraft 40, no. 4 (2003): 623–30. http://dx.doi.org/10.2514/2.3165.

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46

Mor, Marat, and Eli Livne. "Minimum-State Unsteady Aerodynamics for Aeroservoelastic Configuration Shape Optimization of Flight Vehicles." AIAA Journal 43, no. 11 (2005): 2299–308. http://dx.doi.org/10.2514/1.10005.

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Lamont, Peter J., and Andrew Kennaugh. "Total incidence plane aerodynamics - The key to understanding high incidence flight dynamics?" Journal of Aircraft 28, no. 7 (1991): 431–35. http://dx.doi.org/10.2514/3.46045.

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Le Bouar, G., M. Costes, A. Leroy-Chesneau, and P. Devinant. "Numerical simulations of unsteady aerodynamics of helicopter rotor in manoeuvring flight conditions." Aerospace Science and Technology 8, no. 1 (2004): 11–25. http://dx.doi.org/10.1016/j.ast.2003.08.004.

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Gal-Or, Benjamin. "Expanded R&D by Jet-engine-steering Revolution." International Journal of Turbo & Jet-Engines 34, no. 4 (2017): 305–11. http://dx.doi.org/10.1515/tjj-2017-5001.

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Abstract Since 1987 [1, 2, 3, 4, 5] the global jet engine community is facing the historical fact that jet engine steering is gradually replacing canards and the common, often dangerous and obsolete, aerodynamic-only flight control – a fact that (i) has already affected the defense-industrial complex in the US, Russia, China, Japan, S-Korea and India, (ii) has integrated the traditional jet-engine components R&D with advanced aero-electro-physics, stealth technology, thrust vectoring aerodynamics and material science. Moreover, this military revolution is historically due to expand into th

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Tucker, Paul G. "Introduction. Computational aerodynamics." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 365, no. 1859 (2007): 2379–88. http://dx.doi.org/10.1098/rsta.2007.2014.

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The wide range of uses of computational fluid dynamics (CFD) for aircraft design is discussed along with its role in dealing with the environmental impact of flight. Enabling technologies, such as grid generation and turbulence models, are also considered along with flow/turbulence control. The large eddy simulation, Reynolds-averaged Navier–Stokes and hybrid turbulence modelling approaches are contrasted. The CFD prediction of numerous jet configurations occurring in aerospace are discussed along with aeroelasticity for aeroengine and external aerodynamics, design optimization, unsteady flow

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