Download or read book Low speed Pressure distribution Measurements at a Reynolds Number of 3 5 X 10 6 on a Wing with Leading edge Sweepback Decreasing from 45 Degrees at the Root to 20 Degrees at the Tip written by Reed U. Jr Barnett and published by . This book was released on 1950 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Annual Report of the National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1957 with total page 1684 pages. Available in PDF, EPUB and Kindle. Book excerpt: Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Download or read book Maximum lift Characteristics of a Wing with the Leading edge Sweepback Decreasing from 45 Degrees at the Root to 20 Degrees at the Tip at Reynolds Numbers from 2 4 X 10 6 to 6 0 X 10 6 written by Roy H. Lange and published by . This book was released on 1950 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Maximum lift Characteristics of a Wing with the Leading edge Sweepback Decreasing from 45 Degrees at the Root to 20 Degrees at the Tip at Reynolds Numbers from 2 4 X 106 to 6 0 X 106 written by Roy H. Lange and published by . This book was released on 1951 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerospace Engineering Index written by and published by . This book was released on 1958 with total page 904 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering Index written by and published by . This book was released on 1954 with total page 1212 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 Experimental Surface Pressure Data Obtained on 65 delta Wing Across Reynolds Number and Mach Number Ranges written by Julio Chu and published by . This book was released on 1996 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Distribution and Force and Moment Measurements of an 80 Deg Swept Wing with Twist and Camber at a Mach Number of 2 98 written by and published by . This book was released on 1963 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Sweep Angle on the Boundary layer Stability Characteristics of an Untapered Wing at Low Speeds written by Frederick W. Boltz and published by . This book was released on 1960 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Flight written by and published by . This book was released on 1936 with total page 984 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Basic Pressure Measurements at a Mach Number of 1 43 on a Thin 45 Deg Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations written by and published by . This book was released on 1960 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic and cubic twist variations along the span. All the twisted wings had 0deg twist at the 10-percent-semispan station and 6deg twist at the tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4deg to 20deg. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 x 10(exp 6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 x 10(exp 6) during tests at a stagnation pressure of 0.5 atmosphere.
Download or read book Local Pressure Distribution on a Blunt Delta Wing for Angles of Attack Up to 35 Degrees at Mach Numbers of 3 4 and 4 7 written by Marvin Kussoy and published by . This book was released on 1962 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Measurements on Two 60 Degree Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0 Degree and 45 Degrees at a Mach Number of 4 95 written by P. CALVIN. STAINBACK and published by . This book was released on 1962 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to measure the pressures on two 60 degree swept delta wings with cylindrical leading edges of 0.25-inch radii and dihedral angles of 0 and 45 degrees. The tests were conducted at a Mach number of 4.95 and a stagnation temperature of 400 F. The test-section unit Reynolds number was 15.19 x 10 to the 6th power and the angle of attack was varied from 0 to 20 degrees. The results of the investigation indicated that, in general, Newtonian theory would not predict the pressure distri ution on the model in a plane normal to the leading edge for angles of attac greater than zero. A method which utilizes a linear combination of viscous and inviscid pressure terms, developed by Creager for predicting pressures on blunt-leading-e ge delta wing at angles of attac, was in good agreement with the measured pressure distributions. The stagnationline pressure level could be predicted within!9 percent by using the ideal-gas normal-shock relationship with the normal component of the free-stream Mach number. (Author).
Download or read book The Aeronautical Journal written by and published by . This book was released on 1968 with total page 924 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Reynolds Number and Leading Edge Shape on the Low speed Longitudinal Stability of a 6 Percent thick 45 Degree Sweptback Wing written by William C. Schneider and published by . This book was released on 1956 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3 a Taper Ratio of 0 2 and Naca 65a004 Airfoil Sections written by JACK F. RUNCKEL and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections was conducted in the Langley 16-foot transonic tunnel. Pressure measurements on the wing-body combi ation were obtained at angles of attack from 0 degrees to 26 degrees at Mach numbers from 0.80 to 0.98 and at angles of attack from 0 degrees to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic c ord varied from 7 times 10 to the 6th po er to 8.5 times 10 to the 6th power over the test Mach number range. Results of the investigation indicate that a highly swept shock originates at the juncture of the wing leading edge and the body at moderate angles of attack and has a large influence on the loading over the inboard wing sections. (Author).
