Relevant bibliographies by topics / Flight characteristics

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Flight characteristics'

Author: Grafiati
Published: 4 June 2021
Last updated: 16 February 2022

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Journal articles on the topic "Flight characteristics"

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PRISACARIU, Vasile. "ANALYSIS OF UAVs FLIGHT CHARACTERISTICS." Review of the Air Force Academy 16, no. 3 (December 19, 2018): 29–36. http://dx.doi.org/10.19062/1842-9238.2018.16.3.4.

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BRUDERER, BRUNO, and ANDREAS BOLDT. "Flight characteristics of birds:." Ibis 143, no. 2 (April 2001): 178–204. http://dx.doi.org/10.1111/j.1474-919x.2001.tb04475.x.

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Wilhelm, Frank H., and Walton T. Roth. "Clinical Characteristics of Flight Phobia." Journal of Anxiety Disorders 11, no. 3 (May 1997): 241–61. http://dx.doi.org/10.1016/s0887-6185(97)00009-1.

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Bader, Gail Byrne, Maureen Terhorst, Patricia Heilman, and Judith A. DePalma. "Characteristics of flight nursing practice." Air Medical Journal 14, no. 4 (October 1995): 214–18. http://dx.doi.org/10.1016/1067-991x(95)90005-5.

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SUZUKI, Shota, Shinichiro ITO, and Masaki HIRATUKA. "Flight characteristics of flying discs." Proceedings of the Symposium on sports and human dynamics 2020 (2020): B—5–2. http://dx.doi.org/10.1299/jsmeshd.2020.b-5-2.

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Öznalbant, Zafer, and Mehmet Ş. Kavsaoğlu. "Flight control and flight experiments of a tilt-propeller VTOL UAV." Transactions of the Institute of Measurement and Control 40, no. 8 (February 26, 2018): 2454–65. http://dx.doi.org/10.1177/0142331218754618.

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The purpose of this work is to present a study on the stability and control of an unmanned, fixed wing, vertical take-off and landing aerial vehicle. This airplane is driven by a fixed-pitch tilt-propeller system with the capability of vertical take-off and landing as well as conventional flight. The novelty of the vehicle is the use of a fixed-pitch propeller system instead of variable-pitch tilt-rotors. There are three flight modes: vertical, transitional and conventional flight modes. Each flight mode has different dynamic characteristics. Therefore, these modes each need dedicated flight control methods. In this paper, the equations of motion are generated by modelling the aerodynamic and propulsion forces and moments. After performing trim condition calculations, longitudinal stability characteristics are investigated for each flight mode. The control methods are described for vertical, transitional and conventional flight modes. Stability augmentation systems, which consist of proportional and proportional/integral controller, are applied. A number of flight tests, including vertical, transitional and conventional flights, have been successfully performed with a prototype aircraft.
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Chen, Jiu Sheng, and Xiao Yu Zhang. "Modeling of Flight Arrival Scheduling Based on Fuzzy Programming." Applied Mechanics and Materials 313-314 (March 2013): 995–98. http://dx.doi.org/10.4028/www.scientific.net/amm.313-314.995.

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The issue of flight arrival in civil airport is a typical problem of discrete event dynamic system. IN Time is a random variable. According to the characteristics of arrival flights, flight delay cost as objective function, the fuzzy model for scheduling arrival flights is established. In the case of growing air traffic, the model is a better opinion for scientific optimum ordering matter in air traffic control system. It can improve flight operation on time.
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Karmali, Faisal, and Mark Shelhamer. "The dynamics of parabolic flight: Flight characteristics and passenger percepts." Acta Astronautica 63, no. 5-6 (September 2008): 594–602. http://dx.doi.org/10.1016/j.actaastro.2008.04.009.

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Yang, Zi-Yi, and Rong-Jiun Sheu. "EFFECTS OF FLIGHT ROUTE VARIATION AND GREAT-CIRCLE APPROXIMATION ON AVIATION DOSE ASSESSMENT FOR POPULAR FLIGHTS FROM TAIWAN." Radiation Protection Dosimetry 184, no. 1 (October 31, 2018): 79–89. http://dx.doi.org/10.1093/rpd/ncy186.

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Abstract Galactic cosmic-ray-induced secondary particles in the atmosphere constitute an important source of radiation exposure to airline crews and passengers. In this study, a systematic dose assessment was conducted for 11 popular flights from Taiwan, with an emphasis on the effects of flight route variation and assumption. The case studies covered a broad range of commercial flights departing from Taipei, from a domestic flight of <1 h to a long-haul international flight of more than 14 h. For each route under study, information on 100 actual flight routes was retrieved from flight tracking data collected from June to September 2017, and the information was analyzed using a self-developed program called the ‘NTHU Flight Dose Calculator’. The resulting distribution of route doses provided not only the mean value and associated standard deviation but also information on the characteristics of aviation dose assessment and management. Furthermore, compared with actual flight routes, the dose differences introduced by great-circle approximation were evaluated, and the effects of solar activity on the dose assessment of these flights were reported.
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Cao, Yihua, Zhenlong Wu, Yuan Su, and Zhongda Xu. "Aircraft flight characteristics in icing conditions." Progress in Aerospace Sciences 74 (April 2015): 62–80. http://dx.doi.org/10.1016/j.paerosci.2014.12.001.

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Dissertations / Theses on the topic "Flight characteristics"

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Larsson, Roger. "System Identification of Flight Mechanical Characteristics." Licentiate thesis, Linköpings universitet, Reglerteknik, 2013. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-92823.

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With the demand for more advanced fighter aircraft, relying on relaxed stability or even unstable flight mechanical characteristics to gain flight performance, more focus has been put on model-based system engineering to help with the design work. The flight control system design is one important part that relies on this modeling. Therefore it has become more important to develop flight mechanical models that are highly accurate in the whole flight envelop. For today’s newly developed fighters, the basic aircraft characteristics change between linear and nonlinear as well as stable and unstable as an effect of the desired capability of advanced maneuvering at subsonic, transonic and supersonic speeds. This thesis combines the subject of system identification, which is the art of building mathematical models of dynamical systems based on measurements, with aeronautics in order to find methods to identify flight mechanical characteristics from flight tests. Here, a challenging aeronautical identification problem combining instability and nonlinearity is treated. Two aspects are considered. The first is identification during a flight test with the intent to ensure that enough information is available in the resulting test data. Here, a frequency domain method is used. This idea has been taken from an existing method to which some improvements have been made. One of these improvements is to use an Instrumental Variable approach to take care of disturbances coming from atmospheric turbulence. The method treats linear systems that can be both stable and unstable. The improved method shows promising results, but needs further work to become robust against outliers and missing data. The other aspect is post-flight identification. Here, five different direct identification methods, which treat unstable and nonlinear systems, have been compared. Three of the methods are variations of the prediction-error method. The fourth is a parameter and state estimation method and the fifth method is a state estimation method based on an augmented system approach. The simplest of the prediction-error methods, based on a parametrized observer approach, is least sensitive to noise and initial offsets of the model parameters for the studied cases. This approach is attractive since it does not have any parameters that the user has to tune in order to get the best performance. All methods in this thesis have been validated on simulated data where the system is known, and have also been tested on real flight test data.
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Kornienko, Andrei. "System identification approach for determining flight dynamical characteristics of an airship from flight data." [S.l. : s.n.], 2006. http://nbn-resolving.de/urn:nbn:de:bsz:93-opus-28803.

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Soinne, Erkki. "Aerodynamic and Flight Dynamic Simulations of Aileron Characteristics." Doctoral thesis, KTH, Aeronautical Engineering, 2000. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3038.

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Hazlehurst, Grant Allen. "The morphometric and flight characteristics of the pterosaurs." Thesis, University of Bristol, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.303761.

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Yin, Feijia, Volker Grewe, Christine Frömming, and Hiroshi Yamashita. "Impact on flight trajectory characteristics when avoiding the formation of persistent contrails for transatlantic flights." Elsevier, 2018. https://publish.fid-move.qucosa.de/id/qucosa%3A72194.

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This paper studies the impacts on flight trajectories, such as lateral and vertical changes, when avoiding the formation of persistent contrails for transatlantic flights. A sophisticated Earth-System Model (EMAC) coupled with a flight routing submodel (AirTraf) and a contrail submodel (CONTRAIL) is used to optimize flight trajectories concerning the flight time and the flight distance through contrail forming regions (contrail distance). All the trajectories are calculated taking into account the effects of the actual and local meteorological parameters, e.g., wind, temperature, relative humidity, etc. A full-year simulation has been conducted based on a daily flight schedule of 103 transatlantic flights. The trade-off between the flight time and contrail distance shows a large daily variability, meaning for the same increase in flight time, the reduction in contrail distance varies from 20% to 80% depending on the daily meteorological situation. The results confirm that the overall changes in flight trajectories follow a seasonal cycle corresponding to the nature of the potential contrail coverage. In non-summer seasons, the southward and upward shifts of the trajectories are favorable to avoid the contrail formation. In summer, the northward and upward shifts are preferred. A partial mitigation strategy for up to 40% reduction in contrail distance can be achieved throughout all the seasons with a negligible increase in flight time (less than 2%), which represents a reasonable trade-off between flight time increase and contrail avoidance.
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Neiusma, William J. Jr. "An investigation of two-propeller tilt wing V/STOL aircraft flight characteristics." Thesis, Monterey, California. Naval Postgraduate School, 1993. http://hdl.handle.net/10945/39820.

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The results of a two-propeller tilt wing aircraft static stability and performance simulation utilizing a NASA-Ames computer code, Tilt Wing Application General (TWANG), are presented with comparisons to actual test flight data. The Canadair CL-84 tilt wing aircraft was used as a model for the geometric data utilized by the computer simulation. Aerodynamic data for the simulation were obtained from previous NASA Ames research related to a four-propeller model. Variables used included a wide range of parameters associated with flight conditions from hovering flight to maximum cruise speeds at several different altitudes and wing tilt configurations. Longitudinal pitch stability was the driving factor in determining aircraft static stability for the various flight conditions. Results of the simulation indicate that the TWANG computer code provides an accurate prediction of both generic and specific tilt wing aircraft static pitch performance characteristics, as well as the additional capability of providing the required mathematical parameters for incorporation into the NASA Ames Vertical Motion Simulator as software inputs.
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Neiusma, William J. "An investigation of two-propeller tilt wing V/STOL aircraft flight characteristics." Monterey, California : Naval Postgraduate School, 1993. http://handle.dtic.mil/100.2/ADA257751.

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Thesis (Aeronautical and Astronautical Engineer)--Naval Postgraduate School, June 1993.
Thesis Advisor: Newberry, Conrad F. "June, 1993." Description based on title screen as viewed on April 16, 2009. Includes bibliographical references (p. 78-79). Also available in print.
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Hrabovský, Matúš. "Posouzení letových vlastností a zatížení malého sportovního letounu po modifikaci pohonné jednotky." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2020. http://www.nusl.cz/ntk/nusl-417471.

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The thesis deals with the issue of replacement of the Rotax 912 ULS engine with the Rotax 915 iSc3 B engine and its impact on flight performance, characteristics and airframe loads of the WT 9 Dynamic. For accomplish better maneuverability tail surfaces are enlarged. Both versions of airplane with different engines and tails surfaces are quantified with respect to airframe loads and flight characteristics. The output of the diploma thesis can be used for strength design of airplane structure and stress tests of the new modification of the WT 9 Dynamic aircraft.
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Lewis, William D. "An aeroelastic model structure investigation for a manned real-time rotorcraft simulation." Diss., Georgia Institute of Technology, 1992. http://hdl.handle.net/1853/13037.

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Min, Byung-Young. "A physics based investigation of gurney flaps for enhancement of rotorcraft flight characteristics." Diss., Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/33851.

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Helicopters are versatile vehicles that can vertically take off and land, hover, and perform maneuver at very low forward speeds. These characteristics make them unique for a number of civilian and military applications. However, the radial and azimuthal variation of dynamic pressure causes rotors to experience adverse phenomena such as transonic shocks and 3-D dynamic stall. Adverse interactions such as blade vortex interaction and rotor-airframe interaction may also occur. These phenomena contribute to noise and vibrations. Finally, in the event of an engine failure, rotorcraft tends to descend at high vertical velocities causing structural damage and loss of lives. A variety of techniques have been proposed for reducing the noise and vibrations. These techniques include on-board control (OBC) devices, individual blade control (IBC), and higher harmonic control (HHC). Addition of these devices adds to the weight, cost, and complexity of the rotor system, and reduces the reliability of operations. Simpler OBC concepts will greatly alleviate these drawbacks and enhance the operating envelope of vehicles. In this study, the use of Gurney flaps is explored as an OBC concept using a physics based approach. A three dimensional Navier-Stokes solver developed by the present investigator is coupled to an existing free wake model of the wake structure. The method is further enhanced for modeling of Blade-Vortex-Interactions (BVI). Loose coupling with an existing comprehensive structural dynamics analysis solver (DYMORE) is implemented for the purpose of rotor trim and modeling of aeroelastic effects. Results are presented for Gurney flaps as an OBC concept for improvements in autorotation, rotor vibration reduction, and BVI characteristics. As a representative rotor, the HART-II model rotor is used. It is found that the Gurney flap increases propulsive force in the driving region while the drag force is increased in the driven region. It is concluded that the deployable Gurney flap may improve autorotation characteristics if deployed only over the driving region. Although the net effect of the increased propulsive and drag force results in a faster descent rate when the trim state is maintained for identical thrust, it is found that permanently deployed Gurney flaps with fixed control settings may be useful in flare operations before landing by increasing thrust and lowering the descent rate. The potential of deployable Gurney flap is demonstrated for rotor vibration reduction. The 4P harmonic of the vertical vibratory load is reduced by 80% or more, while maintaining the trim state. The 4P and 8P harmonic loads are successfully suppressed simultaneously using individually controlled multi-segmented flaps. Finally, simulations aimed at BVI avoidance using deployable Gurney flaps are also presented.
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Books on the topic "Flight characteristics"

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Rego, Ashley Titus. Simulating the response characteristics of flight instruments. [Downsview, Ont.]: Dept. of Aerospace Science and Engineering, 1985.

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Christodoulidis, Theoharis. Robustness characteristics of active flight control algorithms. Salford: University of Salford, 1987.

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Development, North Atlantic Treaty Organization Advisory Group for Aerospace Research and. Space vehicle flight mechanics. Neuilly sur Seine, France: AGARD, 1990.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Space vehicle flight mechanics. Neuilly-sur-Seine: AGARD, 1990.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Space vehicle flight mechanics. Neuilly sur Seine, France: AGARD, 1990.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Advances in flying qualities. Neuilly sur Seine, France: AGARD, 1988.

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Grant, Peter Robert. Motion characteristics of the UTIAS Flight Research Simulator motion-base. [Downsview, Ont.}]: Institute for Aerospace Studies, 1986.

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Grant, Peter Robert. Motion characteristics of the UTIAS Flight Research Simulator Motion-base. [Downsview, Ont.]: Dept. of Aerospace Science and Engineering, 1985.

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Steady aircraft flight and performance. Princeton, N.J: Princeton University Press, 2011.

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Sim, Alex G. Flight characteristics of a modified Schweizer SGS 1-36 sailplane at low and very high angles of attack. Edwards, Calif: Ames Research Center, 1990.

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Book chapters on the topic "Flight characteristics"

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Kopp, Gregory A. "Flight Characteristics of Wind-Borne Debris." In Wind-Borne Debris Hazards, 39–52. Reston, VA: American Society of Civil Engineers, 2018. http://dx.doi.org/10.1061/9780784414965.ch04.

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Fang, Jian Cheng, Wen Ji Xu, Z. Y. Zhao, and L. Wang. "Influence of In-Flight Particle Characteristics on the Forming Quality." In Materials Science Forum, 2823–26. Stafa: Trans Tech Publications Ltd., 2005. http://dx.doi.org/10.4028/0-87849-960-1.2823.

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Sarwade, A. G., A. S. Narayana, S. Panneerselvam, N. Sahoo, S. Saravanan, G. Jagadeesh, and K. P. J. Reddy. "Aerodynamic characteristics of generic flight vehicle configuration from shock tunnel tests." In Shock Waves, 143–48. Berlin, Heidelberg: Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/978-3-540-27009-6_18.

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Wang, Lei, Changxu Wu, and Ruishan Sun. "Pilot Operating Characteristics Analysis of Long Landing Based on Flight QAR Data." In Lecture Notes in Computer Science, 157–66. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-39354-9_18.

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Fujiwara, Hitoshi, and Keiichi Okai. "Emission Characteristics on Combustion of HEFA Alternative-Aviation Fuel Under In-Flight Conditions." In Lecture Notes in Mechanical Engineering, 55–63. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5996-9_4.

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Chandar, Dominic D. J., and M. Damodaran. "Computation of Low Reynolds Number Aerodynamic Characteristics of a Flapping Wing in Free Flight." In Computational Fluid Dynamics 2008, 197–202. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-01273-0_23.

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Takahashi, M., K. Itoh, H. Tanno, T. Komuro, T. Sunami, K. Sato, and S. Ueda. "Study on the high speed scramjet characteristics at Mach 10 to 15 flight condition." In Shock Waves, 935–40. Berlin, Heidelberg: Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/978-3-540-27009-6_142.

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Gao, Y. Q., Jian Cheng Fang, Z. Y. Zhao, and L. Yang. "Application of RBF Network for Forecasting Characteristics of In-Flight Particles by Plasma Spraying." In Advanced Materials Research, 985–88. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-463-4.985.

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Yoon, Sugjoon, Ji-Young Kong, Kang-Su Kim, Suk-Kyung Lee, and Moon-Sang Kim. "Derivation of Flight Characteristics Data of Small Airplanes Using Design Software and Their Validation by Subjective Tests." In Lecture Notes in Computer Science, 450–57. Berlin, Heidelberg: Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/978-3-540-30585-9_50.

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Hruschka, R., and D. Klatt. "In-Pipe Aerodynamic Characteristics of a Projectile in Comparison with Free Flight for Transonic Mach Numbers Between 0.5 and 1.5." In 31st International Symposium on Shock Waves 2, 815–22. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-91017-8_101.

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Conference papers on the topic "Flight characteristics"

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Nguyen, Hung D., Liu Yu, and Koichi Mori. "Aerodynamic Characteristics of Quadrotor Helicopter." In AIAA Flight Testing Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-3141.

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Kay, Jacob. "Acquiring and modeling unsteady aerodynamic characteristics." In Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-3907.

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Murphy, Kelly, Robert Nowak, Richard Thompson, Brian Hollis, and Ramadas Prabhu. "X-33 hypersonic aerodynamic characteristics." In 24th Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-4162.

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Deiler, Christoph. "Flight Characteristics of Iced Aircraft." In AIAA Scitech 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-0560.

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Bachelder, Edward, and Bimal L. Aponso. "Novel Estimation of Pilot Performance Characteristics." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-1640.

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Xiaoqing, Chen, Hou Zhongxi, and Liu Jianxia. "The Hypersonic Dynamic Characteristics of Waverider." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-7931.

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GUPTA, S. "Aerodynamic characteristics of forward sweep." In Flight Simulation Technologies Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-3041.

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SHINER, ROBERT, and BARRY SULLIVAN. "Man-Vehicle Systems Research Facility - Design and operating characteristics." In Flight Simulation Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-4177.

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GUGLIERI, G., and F. QUAGLIOTTI. "Analysis of stability characteristics of a high performance aircraft." In Flight Simulation and Technologies. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-3616.

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ERICSSON, L., and J. REDING. "Dynamic stall overshoot of static airfoil characteristics." In 12th Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1773.

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Reports on the topic "Flight characteristics"

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Silton, Sidra I., and Bradley E. Howell. Aerodynamic and Flight Dynamic Characteristics of 5.56-mm Ammunition: M855. Fort Belvoir, VA: Defense Technical Information Center, May 2010. http://dx.doi.org/10.21236/ada530895.

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Deussing, Eric C., Jr Artino, Folga Anthony R., and Richard V. In-Flight Hypoxia Events in Tactical Jet Aviation: Characteristics Compared to Normobaric Training. Fort Belvoir, VA: Defense Technical Information Center, October 2010. http://dx.doi.org/10.21236/ada530631.

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Geri, George A. Eye and Head Movement Characteristics in Free Visual Search of Flight-Simulator Imagery. Fort Belvoir, VA: Defense Technical Information Center, March 2010. http://dx.doi.org/10.21236/ada524435.

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Das, Debopam. Aerodynamics Characteristics of Butterfly Flight Through Measurement of Three-Dimensional Unsteady Velocity Field Using TR-PIV System. Fort Belvoir, VA: Defense Technical Information Center, November 2009. http://dx.doi.org/10.21236/ada511002.

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Lee, R. S., J. Colvin, A. Frank, L. Fried, and J. Reaugh. Final report: flight dynamics and impact characteristics of thin flyer plates driven by laser-and electrically-produced plasmas. Office of Scientific and Technical Information (OSTI), February 2001. http://dx.doi.org/10.2172/15006442.

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Anderton, Gary, Ernest Berney, John Newman, Travis Mann, Chad Gartrell, and Daniel Miller. Joint Rapid Airfield Construction (JRAC) Program 2004 Demonstration Project--Fort Bragg, North Carolina. Engineer Research and Development Center (U.S.), March 2021. http://dx.doi.org/10.21079/11681/40139.

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This report describes the demonstration of technologies and procedures developed during April 2002 and May 2004 under the Joint Rapid Airfield Construction (JRAC) Program. The demonstration took place at Sicily Landing Zone (LZ) at Fort Bragg, NC, in July of 2004. The objective of the exercise was to demonstrate the procedures and technologies developed under the JRAC Program by rapidly building two parking aprons capable of supporting C-130 transport aircraft taxiing and parking operations. The exercise was conducted under continuous 24-hr operations to simulate a real-world rapid construction environment. Apron 1 (north apron) was constructed using two technologies, one-half being ACE™ Matting and the other half being a cement-polymer stabilized soil surface. Apron 2 (south apron) was constructed solely of a fiber-cement-stabilized soil system. Both aprons were treated with a polymer emulsion surface application to form a sealed surface against abrasion and water infiltration. The entire construction of both aprons required 76 hr, with Apron 1 finished in 48 hr. The construction of Apron 1 was validated by operation of a C-130 aircraft approximately 31 hr after completion with success and high praises from the aircraft flight crew on the stability and surface of the apron, as well as its dust-abating characteristics.
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