Author: William Gracey
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
Book Description
Wind-tunnel Investigation of a Shielded Total-pressure Tube at Transonic Speeds
Author: William Gracey
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
Book Description
Wind-tunnel Investigation of a Number of Total-pressure Tubes at High Angles of Attack
Author: A. Gerald Rainey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 316
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 316
Book Description
Wind-tunnel Investigation of a Number of Total-pressure Tubes at High Angles of Attack
Author: William Gracey
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 10
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.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 10
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.
Wind-tunnel Investigation of a Shielded Total-pressure Tube at a Mach Number 1.61
Author: Walter R. Russell
Publisher:
ISBN:
Category : Aeronautical instruments
Languages : en
Pages : 9
Book Description
Publisher:
ISBN:
Category : Aeronautical instruments
Languages : en
Pages : 9
Book Description
Wind-tunnel Investigation of Six Shielded Total-pressure Tubes at High Angles of Attack
Author: Walter R. Russell
Publisher:
ISBN:
Category : Aeronautical instruments
Languages : en
Pages : 25
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.
Publisher:
ISBN:
Category : Aeronautical instruments
Languages : en
Pages : 25
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.
Wind-tunnel Investigation of a Number of Total-pressure Tubes at High Angles of Attack
Author: William Gracey
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 69
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.
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 69
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.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1056
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1056
Book Description
Index of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580
Book Description
NASA Reference Publication
Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 852
Book Description
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 852
Book Description
A Selected Listing of NASA Scientific and Technical Reports for ...
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
Book Description