Investigation of the Effects of Propeller Operation on the Low-Speed Stability and Control Characteristics of a 1/6-Scale Model of a Revised Configuration of the Republic XF-84H Airplane

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Description

An investigation was made to determine the static longitudinal and lateral stability and control characteristics of a l/6-scale model of the revised Republic XF-84H airplane with and without the propeller operating. The model had a 40deg swept wing of aspect ratio 3.45 and was equipped with a thin, three-blade supersonic-type propeller. Modifications incorporated in the revised model included a raised horizontal tail, increased rudder size, wing fences at 65 percent semispan, and a modified wing leading edge outboard of the fences. The test results for flap-retracted and flap-deflected conditions indicated that the revised configuration should be satisfactory for most normal ... continued below

Creation Information

Sleeman, William C., Jr. September 4, 1953.

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  • Main Title: Investigation of the Effects of Propeller Operation on the Low-Speed Stability and Control Characteristics of a 1/6-Scale Model of a Revised Configuration of the Republic XF-84H Airplane
  • Series Title: NACA Research Memorandums

Description

An investigation was made to determine the static longitudinal and lateral stability and control characteristics of a l/6-scale model of the revised Republic XF-84H airplane with and without the propeller operating. The model had a 40deg swept wing of aspect ratio 3.45 and was equipped with a thin, three-blade supersonic-type propeller. Modifications incorporated in the revised model included a raised horizontal tail, increased rudder size, wing fences at 65 percent semispan, and a modified wing leading edge outboard of the fences. The test results for flap-retracted and flap-deflected conditions indicated that the revised configuration should be satisfactory for most normal flight conditions provided the angle of attack does not exceed the angle for pitch-up. An abrupt pitch-up tendency of the model was evident for the zero thrust condition above approximately 15' angle of attack. Although the effects of power were destabilizing, power-on longitudinal stability was satisfactory through the angle-of-attack range for which the model was stable with zero thrust. Above the angle of attack for pitch-up, an uncontrollable left roll-off tendency would be expected with power on and slats retracted. Projection of wing slats or use of leading-edge chord-extensions with only the left extension drooped were found beneficial in controlling the roll-off tendency with power on; however the most effective means found was projection of only the left slat.

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  • URL: http://hdl.handle.net/2060/20050028463 External Link
  • Report No.: NACA-RM-SL53I24
  • Center for AeroSpace Information Number: 20050028463
  • Archival Resource Key: ark:/67531/metadc64541

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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).

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Creation Date

  • September 4, 1953

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

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  • Jan. 27, 2017, 6:19 p.m.

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Sleeman, William C., Jr. Investigation of the Effects of Propeller Operation on the Low-Speed Stability and Control Characteristics of a 1/6-Scale Model of a Revised Configuration of the Republic XF-84H Airplane, report, September 4, 1953; (digital.library.unt.edu/ark:/67531/metadc64541/: accessed October 22, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.