Preliminary Results of Stability and Control Investigation of the Bell X-5 Research Airplane

One of 5,163 reports in the series: NACA Research Memorandums available on this site.

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Description

During the acceptance tests of the Bell X-5 airplane, measurements of the static stability and control characteristics and horizontal-tail loads were obtained by the NACA High-Speed Flight Research Station. The results of the stability and control measurements are presented in this paper. A change in sweep angle between 20 deg and 59 deg had a minor effect on the longitudinal trim, with a maximum change of about 2.5 deg in elevator deflection being required at a Mach number near 0.85; however, sweeping the wings produced a total stick-force change of about 40 pounds. At low Mach numbers there was a ... continued below

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Finch, Thomas W & Briggs, Donald W February 11, 1953.

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  • Main Title: Preliminary Results of Stability and Control Investigation of the Bell X-5 Research Airplane
  • Series Title: NACA Research Memorandums

Description

During the acceptance tests of the Bell X-5 airplane, measurements
of the static stability and control characteristics and horizontal-tail
loads were obtained by the NACA High-Speed Flight Research Station. The
results of the stability and control measurements are presented in this
paper.
A change in sweep angle between 20 deg and 59 deg had a minor effect on
the longitudinal trim, with a maximum change of about 2.5 deg in elevator
deflection being required at a Mach number near 0.85; however, sweeping
the wings produced a total stick-force change of about 40 pounds.
At low Mach numbers there was a rapid increase in stability at
high normal-force coefficients for both 20 0 and 1100 sweepback, whereas
a condition of neutral stability existed for 58 0 sweepback at high
normal-force coefficients. At Mach numbers near 0.8 there was an
instability at normal-force coefficients above 0.5 for all sweep angles
tested. In the low normal-force-coefficient range a high degree of
stability resulted in high stick forces which limited the maximum load
factors attainable in the demonstration flights to values under 5g for
all sweep angles at a Mach number near 0.8 and an altitude of 12,000 feet.
The aileron effectiveness at 200 sweepback was found to be low over
the Mach number range tested.

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  • : 93R16766
  • URL: http://hdl.handle.net/2060/19930087476 External Link
  • Report No.: NACA-RM-L52K18b
  • Center for AeroSpace Information Number: 19930087476
  • Archival Resource Key: ark:/67531/metadc59526

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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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Creation Date

  • February 11, 1953

Added to The UNT Digital Library

  • Nov. 17, 2011, 10:13 p.m.

Description Last Updated

  • Jan. 27, 2017, 12:43 p.m.

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Finch, Thomas W & Briggs, Donald W. Preliminary Results of Stability and Control Investigation of the Bell X-5 Research Airplane, report, February 11, 1953; (digital.library.unt.edu/ark:/67531/metadc59526/: accessed November 22, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.