Effects of boattail area contouring and simulated turbojet exhaust on the loading and fuselage-tail component drag of a twin-engine fighter-type airplane model

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

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Description

From Summary: "An investigation of a twin-engine fighter-type airplane model has been conducted in the Langley 16-foot transonic tunnel to determine the effect on drag of a fuselage volume addition incorporating streamline contouring and more extensive boattailing of the engine shrouds. The effect of hot exhausts from the turbojet engines was simulated with hydrogen peroxide gas generators using scaled nonafterburning engine nozzles. Afterbody pressure distributions, base drag coefficients, and forces on the fuselage-tail configurations are presented at Mach numbers from 0.80 to 1.05 angles of attack of 0 degree and 4 degrees for jet pressure ratios from 1 to 7."

Creation Information

Foss, Willard E., Jr.; Runckel, Jack F. & Lee, Edwin E., Jr. July 14, 1958.

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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 184 times . More information about this report can be viewed below.

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  • Main Title: Effects of boattail area contouring and simulated turbojet exhaust on the loading and fuselage-tail component drag of a twin-engine fighter-type airplane model
  • Series Title: NACA Research Memorandums

Description

From Summary: "An investigation of a twin-engine fighter-type airplane model has been conducted in the Langley 16-foot transonic tunnel to determine the effect on drag of a fuselage volume addition incorporating streamline contouring and more extensive boattailing of the engine shrouds. The effect of hot exhausts from the turbojet engines was simulated with hydrogen peroxide gas generators using scaled nonafterburning engine nozzles. Afterbody pressure distributions, base drag coefficients, and forces on the fuselage-tail configurations are presented at Mach numbers from 0.80 to 1.05 angles of attack of 0 degree and 4 degrees for jet pressure ratios from 1 to 7."

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  • Accession or Local Control No: 93R23148
  • URL: http://hdl.handle.net/2060/19930093825 External Link
  • Report No.: NACA-RM-L58C04
  • Center for AeroSpace Information Number: 19930093825
  • Archival Resource Key: ark:/67531/metadc62849

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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

  • July 14, 1958

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

Description Last Updated

  • April 13, 2018, 5:04 p.m.

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Foss, Willard E., Jr.; Runckel, Jack F. & Lee, Edwin E., Jr. Effects of boattail area contouring and simulated turbojet exhaust on the loading and fuselage-tail component drag of a twin-engine fighter-type airplane model, report, July 14, 1958; (digital.library.unt.edu/ark:/67531/metadc62849/: accessed April 27, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.