Wind-tunnel Investigation of a Number of Total-pressure Tubes at High Angles of Attack PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Wind-tunnel Investigation of a Number of Total-pressure Tubes at High Angles of Attack PDF full book. Access full book title Wind-tunnel Investigation of a Number of Total-pressure Tubes at High Angles of Attack by A. Gerald Rainey. Download full books in PDF and EPUB format.
Author: A. Gerald Rainey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 316
Get Book Here
Book Description
Author: A. Gerald Rainey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 316
Get Book Here
Book Description
Author: William Gracey
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 10
Get Book Here
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: William Gracey
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 69
Get Book Here
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:
Publisher:
ISBN:
Category :
Languages : en
Pages : 72
Get Book Here
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: Mark W. Kelly
Publisher:
ISBN:
Category :
Languages : en
Pages : 60
Get Book Here
Book Description
Author: Terry J. Larson
Publisher:
ISBN:
Category : Air speed
Languages : en
Pages : 104
Get Book Here
Book Description
Author: William J. Alford
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 90
Get Book Here
Book Description
Author: William J. Alford
Publisher:
ISBN:
Category : Noses (Aircraft)
Languages : en
Pages : 28
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Supersonic wind tunnels
Languages : en
Pages : 36
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Wind tunnels
Languages : en
Pages : 94
Get Book Here
Book Description
