Wind-tunnel Investigation of a Number of Total-pressure Tubes at High Angles of Attack PDF Download
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Author: A. Gerald Rainey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 316
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Book Description
Author: A. Gerald Rainey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 316
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Book Description
Author: William Gracey
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 10
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Book Description
The effect of Mach number on both unshielded and shielded tubes was found to be considerable. For most of the unshielded tubes the usable range increased with Mach number, whereas that of the shielded tubes decreased with Mach number.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 72
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Book Description
The National Advisory Committee for Aeronautics is investigating the possibility of designing a fixed total-pressure tube which will remain insensitive to inclination of the air stream over a wide range of angle of attack throughout the subsonic and supersonic speed ranges. As the first step in this program the variation of total-pressure error with angle of attack of 39 total-pressure tubes has been determined for an angle-of-attack range of + or - 45 deg and an indicated airspeed of 195 miles per hour. The design of these tubes was varied in such a manner that the effects of external shape, internal shape, and configuration of the total- pressure entry could be determined. The external shapes tested included cylindrical-, conical-, and ogival-nose sections. The internal shapes and total-pressure entries were varied on the basis of such factors as size of impact opening, shape of internal chamber, internal bevel, leading-edge sharpness, slant profile, and shielding (combined with venting).
Author: William Gracey
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 69
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Book Description
Calibrations of 39 total-pressure tubes for an angle-of-attack range of plus or minus 45 degrees and an indicated airspeed of the various tubes differed as regards external shape, internal shape, and type of total-pressure entry. External shapes testsed included cylindrical-, conical-, and ogival-nose sections. Internal shapes and total-pressure entries were varied on the basis of such factors as size of impact opening, leading-edge sharpness, chamber shape, internal bevel, slant profile, and shielding (combined with venting). The effect of these design variables on the sensitivity of the tubes to angle of attack is discussed.
Author: Walter R. Russell
Publisher:
ISBN:
Category : Aeronautical instruments
Languages : en
Pages : 25
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Book Description
Calibartions of six shielded total-pressure tubes over an angle-of-attack range of -30 to 65 degrees at Mach numbers of 02.6, 0.50, 0,.70, 0.90, and 0.95 are presented. One of these tubes was a standard Kiel design, while the other tubes were variations of this design. The design variables which were investigated included the shape of the venturi entry (conical and curved), the position of the total-pressure probe with respect to the leading edge of the shield, the internal diameter of the shield, and the shape of the leading-edge profile. The effect of these variables on the range of angle of attack over which the tubes remained insensitve to inclination is discussed.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 20
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Book Description
Author: Alan Pope
Publisher: John Wiley & Sons
ISBN:
Category : Science
Languages : en
Pages : 496
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1056
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Book Description
Author: William J. Alford
Publisher:
ISBN:
Category : Noses (Aircraft)
Languages : en
Pages : 28
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Book Description
Author: Carl Joseph Wenzinger
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 40
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Book Description
