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Book Wind Tunnel Investigation at Low Speed of a Twisted and Cambered Wing Swept Back 63 Degrees with Vortex Generators and Fences

Download or read book Wind Tunnel Investigation at Low Speed of a Twisted and Cambered Wing Swept Back 63 Degrees with Vortex Generators and Fences written by James A. Weilberg and published by . This book was released on 1952 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind Tunnel Investigation of Effect of Yaw on Lateral stability Characteristics

Download or read book Wind Tunnel Investigation of Effect of Yaw on Lateral stability Characteristics written by Isidore G. Recant and published by . This book was released on 1942 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were tested in the NACA 7- by 10-foot wind tunnel to determine the effect of wing-fuselage interference on the lateral-stability of wing-fuselage interference on the lateral-stability characteristics. The model configurations represented a high-wing, a mid-wing, and a low-wing monoplane. For each configuration, tests were made with a partial-span split flap neutral and deflected 60 degrees and with and without a vertical tail. Tests of the fuselage alone and of the fuselage with the vertical tail were also made.

Book A Low Speed Wind Tunnel Investigation of Reynolds Number Effects on a 60 Deg Swept Wing Configuration with Leading and Trailing Edge Flaps

Download or read book A Low Speed Wind Tunnel Investigation of Reynolds Number Effects on a 60 Deg Swept Wing Configuration with Leading and Trailing Edge Flaps written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-02 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: A low-speed wind tunnel test was performed to investigate Reynolds number effects on the aerodynamic characteristics of a supersonic cruise wing concept model with a 60-deg swept wing incorporating leading-edge and trailing-edge flap deflections. The Reynolds number ranged from 0.3 to 1.6 x 10 to the 6th, and corresponding Mach numbers from .05 to 0.3. The objective was to define a threshold Reynolds number above which the flap aerodynamics basically remained unchanged, and also to generate a data base useful for validating theoretical predictions for the Reynolds number effects on flap performance. This report documents the test procedures used and the basic data acquired in the investigation. Rao, Dhanvada M. and Hoffler, Keith D. Unspecified Center...

Book Force and Moment Wind Tunnel Measurements at Mach Numbers from 0 6 to 2 8 on Four Cruciform Low Aspect Ratio Wing body Combinations

Download or read book Force and Moment Wind Tunnel Measurements at Mach Numbers from 0 6 to 2 8 on Four Cruciform Low Aspect Ratio Wing body Combinations written by G.G. Brebner and published by . This book was released on 1981 with total page 91 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Force and Moment Wind Tunnel Measurements at MACH Numbers from 0 6 to 2 0 of the Control Characteristics of a Wing body Combination with Trailing Edge Control by G G Brebner W K Osborne and Doreen E Brown

Download or read book Force and Moment Wind Tunnel Measurements at MACH Numbers from 0 6 to 2 0 of the Control Characteristics of a Wing body Combination with Trailing Edge Control by G G Brebner W K Osborne and Doreen E Brown written by G.G. Brebner and published by . This book was released on 1982 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Transonic Wind tunnel Investigation of an Unswept Wing in Combination with a Systematic Series of Four Bodies

Download or read book Transonic Wind tunnel Investigation of an Unswept Wing in Combination with a Systematic Series of Four Bodies written by Bruce B. Estabrooks and published by . This book was released on 1953 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Transonic Wind Tunnel Test of a 14 Percent Thick Oblique Wing

Download or read book Transonic Wind Tunnel Test of a 14 Percent Thick Oblique Wing written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-04 with total page 436 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted at the ARC 11- by 11-Foot Transonic Wind Tunnel as part of the Oblique Wing Research Aircraft Program to study the aerodynamic performance and stability characteristics of a 0.087-scale model of an F-8 airplane fitted with an oblique wing designed by Rockwell International. The 10.3 aspect ratio, straight-tapered wing of 0.14 thickness/chord ratio was tested at two different mounting heights above the fuselage. Additional tests were conducted to assess low-speed behavior with and without flaps, aileron effectiveness at representative flight conditions, and transonic drag divergence with 0 degree wing sweep. Longitudinal stability data were obtained at sweep angles of 0, 30, 45, 60, and 65 degrees, at Mach numbers ranging from 0.25 to 1.40. Test Reynolds numbers varied from 3.2 to 6.6 x 10 exp 6/ft. and angle of attack ranged from -5 to +18 degrees. Most data were taken at zero sideslip, but a few runs were at sideslip angles of +/- 5 degrees. The raised wing position proved detrimental overall, although side force and yawing moment were reduced at some conditions. Maximum lift coefficient with the flaps deflected was found to fall short of the value predicted in the preliminary design document. The performance and trim characteristics of the present wing are generally inferior to those obtained for a previously tested wing designed at ARC. Kennelly, Robert A., Jr. and Kroo, Ilan M. and Strong, James M. and Carmichael, Ralph L. Ames Research Center NASA-TM-102230, A-89236, NAS 1.15:102230 RTOP 533-06-01...

Book Wind tunnel Investigation at Mach Numbers from 0 8 to 1 4 of Static Longitudinal and Lateral directional Characteristics of an Unswept wing Airplane Model

Download or read book Wind tunnel Investigation at Mach Numbers from 0 8 to 1 4 of Static Longitudinal and Lateral directional Characteristics of an Unswept wing Airplane Model written by James L. Summers and published by . This book was released on 1956 with total page 99 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind Tunnel Tests of an Aspect Ratio 1 24 Swept Wing with Leading Edge Blowing Parallel to the Wing Chord Plane

Download or read book Wind Tunnel Tests of an Aspect Ratio 1 24 Swept Wing with Leading Edge Blowing Parallel to the Wing Chord Plane written by Victor R. Corsiglia and published by . This book was released on 1970 with total page 198 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book A Transonic wing Investigation in the Langley 8 foot High speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1 2

Download or read book A Transonic wing Investigation in the Langley 8 foot High speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1 2 written by Maurice S. Cahn and published by . This book was released on 1951 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Some Lessons Learned with Wind Tunnels

Download or read book Some Lessons Learned with Wind Tunnels written by and published by . This book was released on 1986 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: