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Design And Predictions For A High Altitude Low Reynolds Number Aerodynamic Flight Experiment
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Book Synopsis Design and Predictions for a High-altitude (low-Reynolds-number) Aerodynamic Flight Experiment by : Donald Greer
Download or read book Design and Predictions for a High-altitude (low-Reynolds-number) Aerodynamic Flight Experiment written by Donald Greer and published by . This book was released on 1999 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: A sailplane being developed at NASA Dryden Flight Research Center will support a high-altitude flight experiment. The experiment will measure the performance parameters of an airfoil at high altitudes (70,000 to 100,000 ft), low Reynolds numbers (200,000 to 700,000), and high subsonic Mach numbers (0.5 to 0.65). The airfoil section lift and drag are determined from pitot and static pressure measurements. The locations of the separation bubble, Tollmien-Schlichting boundary layer instability frequencies, and vortex shedding are measured from a hot-film strip. The details of the planned flight experiment are presented. Several predictions of the airfoil performance are also presented. Mark Drela from the Massachusetts Institute of Technology designed the APEX-16 airfoil, using the MSES code. Two-dimensional Navier-Stokes analyses were performed by Mahidhar Tatineni and Xiaolin Zhong from the University of California, Los Angeles, and by the authors at NASA Dryden.
Book Synopsis Design and Predictions for a High-altitude (low-Reynolds-number) Aerodynamic Flight Experiment by : Donald Greer
Download or read book Design and Predictions for a High-altitude (low-Reynolds-number) Aerodynamic Flight Experiment written by Donald Greer and published by . This book was released on 1999 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: A sailplane being developed at NASA Dryden Flight Research Center will support a high-altitude flight experiment. The experiment will measure the performance parameters of an airfoil at high altitudes (70,000 to 100,000 ft), low Reynolds numbers (200,000 to 700,000), and high subsonic Mach numbers (0.5 to 0.65). The airfoil section lift and drag are determined from pitot and static pressure measurements. The locations of the separation bubble, Tollmien-Schlichting boundary layer instability frequencies, and vortex shedding are measured from a hot-film strip. The details of the planned flight experiment are presented. Several predictions of the airfoil performance are also presented. Mark Drela from the Massachusetts Institute of Technology designed the APEX-16 airfoil, using the MSES code. Two-dimensional Navier-Stokes analyses were performed by Mahidhar Tatineni and Xiaolin Zhong from the University of California, Los Angeles, and by the authors at NASA Dryden.
Book Synopsis A Design for a High Altitude Flight Test System by :
Download or read book A Design for a High Altitude Flight Test System written by and published by . This book was released on 2005 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Small UAV?s and flight vehicles in other atmospheres such as Mars are characterized by low Reynolds numbers. Low Reynolds number airfoil testing has been difficult to achieve and there are few centers that can accomplish this task. This study is an effort to develop a flight test system that will enable low Reynolds number tests to be performed with a simple glider design. The concept is to develop a high altitude glider that will be transported to altitudes reaching 100,000 feet or more by a helium filled balloon. At altitude, the glider will be released and will perform flight experiments as it descends. This region of Earth?s atmosphere,?near space? has the conditions desired for low Reynolds number testing as well as similar properties to the surface of Mars. With the knowledge gained from this experiment, a better understanding of accomplishing flight on Mars may be attained.
Book Synopsis Design Study of a High Altitude Morphing UAV with Analysis of Low Reynolds Number Parawing Aerodynamics by : Peter Antoine Munther
Download or read book Design Study of a High Altitude Morphing UAV with Analysis of Low Reynolds Number Parawing Aerodynamics written by Peter Antoine Munther and published by . This book was released on 2006 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The study of this thesis concerned the development of a high altitude (70,000ft to 100,000ft) UAV which utilized a parawing-type wing along with a gimbaled pusher prop that was used for thrust as well as longitudinal stability and control purposes. First, an initial design study was performed based on a chosen thrust available requirement of I2HP and a cruise velocity requirement of l2OftIs at an altitude of 100,000ft. Additionally, the study was based on the idea that the aircraft should not be lengthy in structure. This led to the determination of a wing area of 1 8,000ft2 given that (L/D)max was 5.5 along with a CL of 0.6, as found from historical parawing analyses. This wing area was found to have met the desired dimensions of an equal length fuselage and wing leading edge of about 5Oft. These parameters dictated a low Reynolds number of 6.6X105 for the cruise condition at 100,000ft. For the found geometry it was necessary to maintain a leading edge sweep, A, of 270. However, historical parawing tests did not provide data concerning a A below 350. This motivated low leading edge sweep parawing wind tunnel tests. A model was built and tested matching the cruising Re of 6.6X105 at leading edge sweeps of 450, 300, 150, and 00 along with flat-planform leading edge sweeps, [Lamda]0, of 380, 230, 80, and -70 respectively to allow for billow. Wind tunnel tests showed that for the case where [Lamda] was 00 (with a [Lamda]0 of -70) provided the maximum values for (L/D)max and (L312/D)max at a 4.6 and 3.9 respectively. However, results for the other cases of leading edge sweep were relatively close in value. The magnitude of the values for CMa.c. were large, ranging from -0.104 to -0.323. Additionally, the a.c. locations were found to be in-front of the leading edge of the wings for all cases, moving further out as [Lamda] decreased. Data trends were created from the wind tunnel test data along with historical data in order to study the flight capabilities of the aircraft for a range of [Lamda] from 00 to 800. It was found that the THPA was sufficient to allow for flight at both extremes of altitudes at the desired cruise velocity without consideration to longitudinal stability and control. In studying the longitudinal stability and control aspects or the aircraft, it was found that the locations of the a.c. were not favorable as a large moment about the c.g. of the aircraft was produced. This proved to be a formidable challenge for static longitudinal control purposes, where it was found that the aircraft could only reach a maximum altitude of 74,000ft, requiring a vectored thrust angle, [delta][lamda], of 600. This occurred for a [Lamda] of 120 at a velocity of 54ft/s. However, by theoretically moving the a.c. closer to the c.g. it was found that flight at the extreme case of 100,000ft at the desired cruise velocity was able to be reached while maintaining static longitudinal stability with a [delta][lamda] 90. This occurred ata [Lamda] of 410. A full-state feedback dynamic longitudinal stability analysis was performed for the case of flight at 70,000ft demonstrating that the aircraft was naturally unstable but controllable utilizing the designed control system. The state responses to a disturbance in flight angle, [theta], of 50 are shown as an example. This analysis provided the equations for the control stability derivates, which were applicable to all flight cases. Overall, the study of aircraft proved to be beneficial. The results from the wind tunnel testing proved that a parawing could operate at very low leading edge sweeps. However, because of the large aerodynamic moments due to the forward position of the a.c., the longitudinal stability and control system performed poorly. Either the a.c. would need to be changed or a new longitudinal stability and control system would need to be developed to produce a successful UAV.
Book Synopsis Summary of Low Speed Airfoil Data by : Michael S. Selig
Download or read book Summary of Low Speed Airfoil Data written by Michael S. Selig and published by Soartech. This book was released on 1995 with total page 320 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low Reynolds Number by : Mustafa Serdar Genç
Download or read book Low Reynolds Number written by Mustafa Serdar Genç and published by BoD – Books on Demand. This book was released on 2012-04-04 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book reports the latest development and trends in the low Re number aerodynamics, transition from laminar to turbulence, unsteady low Reynolds number flows, experimental studies, numerical transition modelling, control of low Re number flows, and MAV wing aerodynamics. The contributors to each chapter are fluid mechanics and aerodynamics scientists and engineers with strong expertise in their respective fields. As a whole, the studies presented here reveal important new directions toward the realization of applications of MAV and wind turbine blades.
Book Synopsis Laminar Flow Aircraft Certification by :
Download or read book Laminar Flow Aircraft Certification written by and published by . This book was released on 1986 with total page 340 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Computational Fluid Dynamics 2010 by : Alexander Kuzmin
Download or read book Computational Fluid Dynamics 2010 written by Alexander Kuzmin and published by Springer Science & Business Media. This book was released on 2011-05-03 with total page 902 pages. Available in PDF, EPUB and Kindle. Book excerpt: The International Conference on Computational Fluid Dynamics is held every two years and brings together physicists, mathematicians and engineers to review and share recent advances in mathematical and computational techniques for modeling fluid flow. The proceedings of the 2010 conference (ICCFD6) held in St Petersburg, Russia, contain a selection of refereed contributions and are meant to serve as a source of reference for all those interested in the state of the art in computational fluid dynamics.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781720385196 Total Pages :36 pages Book Rating :4.3/5 (851 download)
Book Synopsis Apex 3D Propeller Test Preliminary Design by : National Aeronautics and Space Administration (NASA)
Download or read book Apex 3D Propeller Test Preliminary Design written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-20 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A low Reynolds number, high subsonic mach number flight regime is fairly uncommon in aeronautics. Most flight vehicles do not fly under these aerodynamic conditions. However, recently there have been a number of proposed aircraft applications (such as high altitude observation platforms and Mars aircraft) that require flight within this regime. One of the main obstacles to flight under these conditions is the ability to reliably generate sufficient thrust for the aircraft. For a conventional propulsion system, the operation and design of the propeller is the key aspect to its operation. Due to the difficulty in experimentally modeling the flight conditions in ground-based facilities, it has been proposed to conduct propeller experiments from a high altitude gliding platform (APEX). A preliminary design of a propeller experiment under the low Reynolds number, high mach number flight conditions has been devised. The details of the design are described as well as the potential data that will be collected.Colozza, Anthony J.Glenn Research CenterTHREE DIMENSIONAL MODELS; LOW REYNOLDS NUMBER; PROPELLERS; SUBSONIC SPEED; PERFORMANCE TESTS; EXPERIMENT DESIGN; FLIGHT CONDITIONS; GLIDING; HIGH ALTITUDE; MACH NUMBER; OBSERVATION AIRCRAFT; PROPULSION
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781723015083 Total Pages :132 pages Book Rating :4.0/5 (15 download)
Book Synopsis Design and Performance Calculations of a Propeller for Very High Altitude Flight. Degree Awarded by Case Western Univ. by : National Aeronautics and Space Administration (NASA)
Download or read book Design and Performance Calculations of a Propeller for Very High Altitude Flight. Degree Awarded by Case Western Univ. written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt: Reported here is a design study of a propeller for a vehicle capable of subsonic flight in Earth's stratosphere. All propellers presented were required to absorb 63.4 kW (85 hp) at 25.9 km (85,000 ft) while aircraft cruise velocity was maintained at Mach 0.40. To produce the final design, classic momentum and blade-element theories were combined with two and three-dimensional results from the Advanced Ducted Propfan Analysis Code (ADPAC), a numerical Navier-Stokes analysis code. The Eppler 387 airfoil was used for each of the constant section propeller designs compared. Experimental data from the Langley Low-Turbulence Pressure Tunnel was used in the strip theory design and analysis programs written. The experimental data was also used to validate ADPAC at a Reynolds numbers of 60,000 and a Mach number of 0.20. Experimental and calculated surface pressure coefficients are compared for a range of angles of attack. Since low Reynolds number transonic experimental data was unavailable, ADPAC was used to generate two-dimensional section performance predictions for Reynolds numbers of 60,000 and 100,000 and Mach numbers ranging from 0.45 to 0.75. Surface pressure coefficients are presented for selected angles of attack. in addition to the variation of lift and drag coefficients at each flow condition. A three-dimensional model of the final design was made which ADPAC used to calculated propeller performance. ADPAC performance predictions were compared with strip-theory calculations at design point. Propeller efficiency predicted by ADPAC was within 1.5% of that calculated by strip theory methods, although ADPAC predictions of thrust, power, and torque coefficients were approximately 5% lower than the strip theory results. Simplifying assumptions made in the strip theory account for the differences seen. Koch, L. Danielle Glenn Research Center PROPELLERS; PROPELLER EFFICIENCY; PERFORMANCE PREDICTION; LOW REYNOLDS NUMBER; AERODYNAMIC COEFFICIENTS; NAVIER-STOKES EQUATION; N...
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Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 892 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 2023 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2023) Proceedings by : Song Fu
Download or read book 2023 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2023) Proceedings written by Song Fu and published by Springer Nature. This book was released on with total page 1975 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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Book Synopsis Monthly Catalog of United States Government Publications by :
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Book Synopsis Monthly Catalogue, United States Public Documents by :
Download or read book Monthly Catalogue, United States Public Documents written by and published by . This book was released on 1981 with total page 876 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis U.S. Government Research & Development Reports by :
Download or read book U.S. Government Research & Development Reports written by and published by . This book was released on 1969-10 with total page 784 pages. Available in PDF, EPUB and Kindle. Book excerpt:
