Static longitudinal and lateral stability characteristics at low speed of 45 degree sweptback-midwing models having wings with an aspect ratio of 2, 4, or 6

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Results are presented of tests conducted in the Langley stability tunnel to determine the effects of various components and combinations of components on the static longitudinal and lateral stability characteristics at low speed of a series of 45 degree sweptback-midwing-airplane configurations having wings with an aspect ratio of 2, 4, or 6. The tests were made at a dynamic pressure of 24.9 pounds per square foot which corresponds to a Mach number of 0.13 and Reynolds numbers of 1.00 x 10(exp 6), 0.71 x 10 (exp 6), and 0.58 x 10 (exp 6) based on the respective wing mean aerodynamic ... continued below

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Thomas, David F , Jr & Wolhart, Walter D September 1, 1957.

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This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and one other and was provided by UNT Libraries Government Documents Department to Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 151 times . More information about this report can be viewed below.

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  • Main Title: Static longitudinal and lateral stability characteristics at low speed of 45 degree sweptback-midwing models having wings with an aspect ratio of 2, 4, or 6
  • Series Title: NACA Technical Notes

Description

Results are presented of tests conducted in the Langley stability tunnel to determine the effects of various components and combinations of components on the static longitudinal and lateral stability characteristics at low speed of a series of 45 degree sweptback-midwing-airplane configurations having wings with an aspect ratio of 2, 4, or 6. The tests were made at a dynamic pressure of 24.9 pounds per square foot which corresponds to a Mach number of 0.13 and Reynolds numbers of 1.00 x 10(exp 6), 0.71 x 10 (exp 6), and 0.58 x 10 (exp 6) based on the respective wing mean aerodynamic chords. The angle-of-attack range covered was from -4 degrees to 32 degrees and the sideslip angles used for the lateral-derivative tests were 5 degrees and -5 degrees. An increasing loss in tail contribution to directional stability both with increasing wing aspect ratio and increasing angle of attack was found to be a principal cause of all the complete models becoming directionally unstable in the high angle-of-attack range.

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  • : 93R14367
  • URL: http://hdl.handle.net/2060/19930085077 External Link
  • Report No.: NACA-TN-4077
  • Center for AeroSpace Information Number: 19930085077
  • Archival Resource Key: ark:/67531/metadc57035

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National Advisory Committee for Aeronautics Collection

The National Advisory Committee for Aeronautics (NACA) was a U.S. federal agency founded on March 3, 1915 to undertake, promote, and institutionalize aeronautical research. On October 1, 1958 the agency was dissolved, and its assets and personnel transferred to the newly created National Aeronautics and Space Administration (NASA).

Technical Report Archive and Image Library

This selection of materials from the Technical Report Archive and Image Library (TRAIL) includes hard-to-find reports published by various government agencies. The technical publications contain reports, images, and technical descriptions of research performed for U.S. government agencies. Topics range from mining, desalination, and radiation to broader physics, biology, and chemistry studies. Some reports include maps, foldouts, blueprints, and other oversize materials.

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  • September 1, 1957

Added to The UNT Digital Library

  • Nov. 17, 2011, 10:13 p.m.

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  • Jan. 31, 2017, 2:11 p.m.

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Thomas, David F , Jr & Wolhart, Walter D. Static longitudinal and lateral stability characteristics at low speed of 45 degree sweptback-midwing models having wings with an aspect ratio of 2, 4, or 6, report, September 1, 1957; (digital.library.unt.edu/ark:/67531/metadc57035/: accessed October 19, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.