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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 Aerospace Engineering

Download or read book Aerospace Engineering written by and published by . This book was released on 1958-05 with total page 1236 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 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 Aeronautical Engineering Review

Download or read book Aeronautical Engineering Review written by and published by . This book was released on 1957 with total page 844 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 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 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 8 on a Delta Wing of Aspect Ratio 0 31 in Monoplane and Cruciform Combination with Two Axisymmetric Bodies

Download or read book Force and Moment Wind Tunnel Measurements at Mach Numbers from 0 6 to 2 8 on a Delta Wing of Aspect Ratio 0 31 in Monoplane and Cruciform Combination with Two Axisymmetric Bodies written by G.G. Brebner and published by . This book was released on 1979 with total page 220 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind Tunnel Results of the Aerodynamic Performance of a 1 8 Scale Model of a Twin Engine Transport with Multi Element Wing

Download or read book Wind Tunnel Results of the Aerodynamic Performance of a 1 8 Scale Model of a Twin Engine Transport with Multi Element Wing written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-23 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel investigation was performed in the 14- by 22-Foot Subsonic Tunnel on a pressure instrumented 1/8-scale twin-engine subsonic transport to better understand the flow physics on a multi-element wing section. The wing consisted of a part-span, triple-slotted trailing edge flap, inboard leading-edge Krueger flap and an outboard leading-edge slat. The model was instrumented with flush pressure ports at the fuselage centerline and seven spanwise wing locations. The model was tested in cruise, take-off and landing configurations at dynamic pressures and Mach numbers from 10 lbf/ft(exp 2) to 50 lbf/ft(exp 2) and 0.08 to 0.17, respectively. This resulted in corresponding Reynolds numbers of 0.8 x 10(exp 5) to 1.8 x 10(exp 6). Pressure data were collected using electronically scanned pressure devices and force and moment data were collected with a six component strain gauge balance. Results are presented for various control surface deflections over an angle-of-attack range from -4 degrees to 16 degrees and sideslip angle range from -10 degrees to 10 degrees. Longitudinal and lateral directional aerodynamic data are presented as well as chordwise pressure distributions at the seven spanwise wing locations and the fuselage centerline. Laflin, Brenda E. Gile and Applin, Zachary T. and Jones, Kenneth M. Langley Research Center WIND TUNNEL TESTS; PRESSURE DISTRIBUTION; SUBSONIC SPEED; WINGS; REYNOLDS NUMBER; ANGLE OF ATTACK; MACH NUMBER; AERODYNAMIC CHARACTERISTICS; SIDESLIP; SCALE MODELS; TRAILING EDGE FLAPS; LEADING EDGES; STRAIN GAGE BALANCES; CONTROL SURFACES; TAKEOFF; AIRCRAFT LANDING; DYNAMIC PRESSURE; LATERAL STABILITY; LONGITUDINAL STABILITY...

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 Introduction to Aircraft Flight Mechanics

Download or read book Introduction to Aircraft Flight Mechanics written by Thomas R. Yechout and published by AIAA. This book was released on 2003 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt: Based on a 15-year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.