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Empirical Cooling Correlation for an Experimental Afterburner With an Annular Cooling Passage

Description: Memorandum presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation relates the average combustion-chamber wall temperature at a station near the combustion-chamber outlet to the temperatures of the cooling air and combustion gas, and to the mass flows of the cooling air and combustion gas.
Date: June 26, 1952
Creator: Koffel, William K. & Kaufman, Harold R.
Partner: UNT Libraries Government Documents Department
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An investigation of the subsonic speed range of a full-span and a semispan model of a plane wing and of a cambered and twisted wing, all having 45 degrees of sweepback

Description: Report presenting a wind-tunnel investigation of two full-span and two semispan models with 45 degrees of sweepback, an aspect ratio of 5.5, and a taper ratio of 0.53. The lift and drag data obtained from tests of the semispan agreed well with data obtained on the full-span model. Results regarding a comparison of the data for the full-span and semispan models, full-span model data, and effect of surface roughness are provided.
Date: June 26, 1952
Creator: Shibata, Harry H.; Bandettini, Angelo & Cleary, Joseph
Partner: UNT Libraries Government Documents Department
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Investigation of lift and center of pressure of low-aspect-ratio, cruciform, triangular, and rectangular wings in combination with a slender fuselage at high supersonic speeds

Description: Report presenting tests to evaluate the usefulness of available theory for the calculation of lift-curve slope and center of pressure of low-aspect-ratio, triangular, and rectangular cruciform wings in combination with a long slender body. Tests were made over a range of Mach and Reynolds numbers based on model length.
Date: June 26, 1952
Creator: Canning, Thomas N. & Denardo, Billy Pat
Partner: UNT Libraries Government Documents Department
open access

Empirical cooling correlation for an experimental afterburner with an annular cooling passage

Description: Report presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation equation is useful for shortening the experimental investigation of afterburner cooling characteristics inasmuch as it provides a method for interpolating the critical wall temperatures for other combinations of operating variables.
Date: June 26, 1952
Creator: Koffel, William K. & Kaufman, Harold R.
Partner: UNT Libraries Government Documents Department
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Altitude Wind Tunnel Investigation of High-Temperature Afterburners

Description: From Introduction: "During previous investigations of afterburning conducted at the NACA Lewis laboratory (references 1 to 4, for example), the objective of obtaining high exhaust-gas temperatures and, consequently, maximum thrust augmentation was compromised to some extent in order to alleviate the problem of afterburner shell cooling. The primary objective of the investigation reported herein was therefore the attainment of maximum exhaust-gas temperature imposed by the cooling techniques pre… more
Date: June 26, 1952
Creator: Conrad, E. William & Campbell, Carl E.
Partner: UNT Libraries Government Documents Department
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[News Clip: Crowning queens]

Description: Video footage from the WBAP-TV television station in Fort Worth, Texas, to accompany a news story.
Date: June 26, 1952
Duration: 20 seconds
Creator: WBAP-TV (Television station : Fort Worth, Tex.)
Partner: UNT Libraries Special Collections
captions transcript

[News Clip: Jaycee parades]

Description: Video footage from the WBAP-TV television station in Fort Worth, Texas, to accompany a news story.
Date: June 26, 1952
Duration: 3 minutes 39 seconds
Creator: WBAP-TV (Television station : Fort Worth, Tex.)
Partner: UNT Libraries Special Collections
open access

Lift, Drag, and Pitching Moment of Low-Aspect-Ratio Wings at Subsonic and Supersonic Speeds: Plane Triangular Wing of Aspect Ratio 3 With Air-to-Air Missile Models Mounted Externally

Description: "This report presents results of an investigation of effects of externally mounted missile models on the aerodynamic characteristics of a triangular wing of aspect ratio 3 at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the wind-fuselage model fitted with the missile models are presented for Mach numbers of 0.6, 0.9, 1.2, 1.4, and 1.7 at a Reynolds number of 4.8 million. Similar data are presented for the basic wing" (p. 1).
Date: June 26, 1952
Creator: Conrard, Donald
Partner: UNT Libraries Government Documents Department
captions transcript

[News Clip: Boxing youths]

Description: Video footage from the WBAP-TV television station in Fort Worth, Texas, to accompany a news story.
Date: June 26, 1952
Duration: 1 minute 29 seconds
Creator: WBAP-TV (Television station : Fort Worth, Tex.)
Partner: UNT Libraries Special Collections
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