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in subjects: "total pressure tubes"  
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Effects of Compressibility and Large Angles of Yaw on Pressure Indicated by a Total-Pressure Tube

Description: Report discusses the effects of compressibility and angle of yaw on the pressure measured by a round-nose and a flat-nose total-pressure tube. The error incurred in the pressure measurements and factors affecting the total-pressure area are described.
Date: April 1945
Creator: Humphreys, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Number of Total Pressure Tubes at High Angles of Attack: Subsonic speeds

Description: Report presenting a wind-tunnel investigation to determine the effect of inclination of the air stream on the measured pressures of 20 total-pressure tubes through a range of angles of attack and Mach numbers. Generally, the range of angle of attack over which the tubes remained insensitive to inclination was appreciably greater at supersonic speeds than at subsonic speeds.
Date: January 1951
Creator: Gracey, William; Coletti, Donald E. & Russell, Walter R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Number of Total-Pressure Tubes at High Angles of Attack: Subsonic, Transonic, and Supersonic Speeds

Description: Note presenting the effect of inclination of the airstream on the measured pressures of 54 total-pressure tubes for angles of attack up to 60 degrees and over a Mach number range from 0.26 to 1.62. The investigation was conducted in five wind tunnels. Results regarding effect of impact-opening size, effect of varying the shape of the internal chamber, effect of external shape, effect of slant profile, effect of venting of shielded tubes, effect of varying the probe position and the throat diame… more
Date: May 1956
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Number of Total-Pressure Tubes at High Angles of Attack -- Subsonic, Transonic, and Supersonic Speeds

Description: "The effect of inclination of the airstream on the measured pressures of 54 total-pressure tubes has been determined for angles of attack up to 60 degrees and over a Mach number range from 0.26 to 1.62. The investigation was conducted in five wind tunnels at the Langley Aeronautical Laboratory" (p. 495).
Date: January 17, 1956
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of six shielded total-pressure tubes at high angles of attack: Subsonic speeds

Description: Report presenting a study of the effect of inclination of the air stream on the measured pressures of six shielded total-pressure tubes for a range of angles of attack. The tests were conducted over a range of Mach numbers. Results indicated that the shape of the venturi entry has a pronounced effect on the range of angles of attack over which the tubes remain insensitive to inclination of the air stream.
Date: November 1951
Creator: Russell, Walter R.; Gracey, William; Letko, William & Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Shielded Total-Pressure Tube at Transonic Speeds

Description: Report presenting testing of a shielded total-pressure tube with a curved venturi entry in order to obtain the variation of total-pressure error with angle of attack from a range of 0 to 60 degrees and for a range of Mach numbers. The critical angle was found to vary from about 57 degrees at Mach number 0.90 to 56 degrees at Mach number 1.10.
Date: January 22, 1952
Creator: Gracey, William; Pearson, Albin O. & Russell, Walter R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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