Download or read book Investigation at Large Scale of the Pressure Distribution and Flow Phenomena Over a Wing with the Leading Edge Swept Back 47 5 Degrees Having Circular arc Airfoil Sections and Equipped with Drooped nose and Plain Flaps written by Roy H. Lange and published by . This book was released on 1949 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Studies of the Flow Field Behind a Large Scale 47 5 Degree Sweptback Wing Having Circular arc Airfoil Sections and Equipped with Drooped nose and Plain Flaps written by Roy H. Lange and published by . This book was released on 1952 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Low speed Pressure Distributions Over the Drooped nose Flap of a 42 Degree Sweptback Wing with Circular arc Airfoil Sections at a Reynolds Number of 5 3 X 10 6 written by Stanley H. Spooner and published by . This book was released on 1948 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Influence of Airfoil Geometry on Delta Wing Leading edge Vortices and Vortex induced Aerodynamics at Supersonic Speeds written by Richard M. Wood and published by . This book was released on 1992 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure distribution Measurements Over a 45 Degree Sweptback Wing at Transonic Speeds by the NACA Wing flow Method written by Edward C. B. Danforth and published by . This book was released on 1951 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of pressure were made over the chord of a swept-wing model at four stations along (2, 6, 50, and 82 percent semispan) by the NACA wing-flow method. The model tested was an untapered 45 degree sweptback wing of aspect ratio 3.5 with 2-inch-chord NACA 65-210 airfoil sections normal to the leading edge. The tests were conducted at Mach numbers from about 0.7 to 1.1 at angles of attack from -1 to 4 degrees. The Reynolds number of the tests was nominally 600,000 based on the wing chord in the stream direction. The results are presented to show the chordwise pressure distributions and the spanwise distributions of section lift, drag, and pitching moment.
Download or read book The Effect of Leading edge Droop Upon the Pressure Distribution and Aerodynamic Loading Characteristics of a 45 Degree Sweptback Wing at Transonic Speeds written by James W. Schmeer and published by . This book was released on 1955 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley 16-foot transonic tunnel to determine the effects of leading-edge droop on the pressure distribution on a 45 degree sweptback wing with an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. The leading edge of the wing was drooped 6 degrees about the 19-percent chord line from 0.15 semispan to the wing tip. Data were obtained at Mach numbers of 0.80 to 1.03 with average Reynolds numbers of 5,700,000 to 6,300,000, respectively. The results of this investigation are compared with the pressure data obtained with the undrooped or basic wing of a previous investigation.
Download or read book NACA 0015 Wing Pressure and Trailing Vortex Measurements written by Kenneth W. McAlister and published by . This book was released on 1991 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of High lift and Stall control Devices Fuselage and Horizontal Tail on a Wing Swept Back 42 Degrees at the Leading Edge and Having Symmetrical Circular arc Airfoil Sections at a Reynolds Number of 6 9 X 10 6 written by Robert L. Woods and published by . This book was released on 1949 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book High pressure Blowing Over Flap and Wing Leading Edge of a Large scale 49 Degrees Swept Wing body tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase written by Marvin P. Fink and published by . This book was released on 1957 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of Pressure Distribution Over an Extended Leading Edge Flap on a 42 Degree Sweptback Wing written by and published by . This book was released on 1947 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chordwise location of the flap center of pressure to be move forward.
Download or read book An Experimental Study of the Pressure and Heat transfer Distribution on a 70 Sweep Slab Delta Wing in Hypersonic Flow written by Mitchel H. Bertram and published by . This book was released on 1963 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Measurements on Two 60 Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0 and 45 at a Mach Number of 4 95 written by P. Calvin Stainback and published by . This book was released on 1962 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Low speed Pressure distribution and Flow Investigation for a Large Pitch and Yaw Range of Three Low aspect ratio Pointed Wings Having Leading Edge Swept Back 60 Degrees and Biconvex Sections written by Ralph W. Jr May and published by . This book was released on 1949 with total page 109 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Pressure Distributions Over Wing Tips at Mach Number 1 9 written by Harold Mirels and published by . This book was released on 1949 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.
Download or read book Surface Pressure Distributions on a Large scale 49 Degree Sweptback Wing body tail Configuration with Blowing Applied Over the Flaps and Wing Leading Edge written by H. Clyde McLemore and published by . This book was released on 1958 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of the Influence of Wing Sweep on Juncture Flow written by Mohammad Javed Khan and published by . This book was released on 1994 with total page 620 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book High pressure Blowing Over Flap and Wing Leading Edge of a Thin Large scale 49 Swept Wing body tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase written by Marvin P. Fink and published by . This book was released on 1957 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
