Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1957 with total page 378 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Lateral control Investigation of Flap type Controls on a Wing with Quarter chord Line Sweptback 35 Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by Robert F. Thompson and published by . This book was released on 1950 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of an investigation to determine the control-effectiveness characteristics of 30-percent-chord flap-type control surfaces of various spans on a semispan wing-fuselage model. The wing of the mode had 35 degrees of sweepback of the quarter chord, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. Lift, rolling moments, and pitching moments were obtained for several angle of attack throughout a small range of control-surface deflections. Most of the data are presented as control-effectiveness parameters which show their variation with Mach number.

Download or read book Annual Report for the Fiscal Year written by National Library of Medicine (U.S.) and published by . This book was released on 1959 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Report National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1918 with total page 570 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Evaluation of Proposed Reference Fuel Scales for Knock Rating written by Henry C. Barnett and published by . This book was released on 1948 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results showing the antiknock performance characteristics of proposed reference fuels (triptane, n-heptane, isooctane) in current fuel knock-rating engines. The proposed reference-fuel scales are compared with the octane-number scale and the performance-number scale now in use.

Download or read book Attempts to Defoam Existing Oils by Processing written by J. W. McBain and published by . This book was released on 1949 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lubricating oil has been processed by treatment with various adsorbaents and by solvent extraction in an attempt to reduce foaming.

Download or read book Surface Properties of Oils written by J. W. McBain and published by . This book was released on 1949 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: The surface properties of oils were studied in a short series of experiments on their film viscosities and surface tensions. Information about film formation in general was obtained from the behavior of single bubbles on the surface and from the coalesence of pairs of bubbles below the surface of various pure and binary liquids.

Download or read book NASA Technical Translation written by United States. National Aeronautics and Space Administration and published by . This book was released on 1970 with total page 230 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Technical Memorandums written by United States. National Advisory Committee for Aeronautics and published by . This book was released on with total page 404 pages. Available in PDF, EPUB and Kindle. Book excerpt: Chiefly translations from foreign aeronautical journals.

Download or read book NASA Technical Note written by and published by . This book was released on 1977 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Survey of Hydrogen Combustion Properties written by Isadore L. Drell and published by . This book was released on 1957 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: This literature survey digest of hydrogen-air combustion fundamentals presents data on flame temperature, burning velocity, quenching distance, flammability limits, ignition energy, flame stability, detonation, spontaneous ignition, and explosion limits. The data are assessed, recommended values are given, and relations among various combustion properties are discussed. New material presented includes: theoretical treatment of variation in spontaneous ignition lag with temperature, pressure, and composition, based on reaction kinetics of hydrogen-air composition range for 0.01 to 100 atmospheres and initial temperatures of 0 degrees to 1400 degrees k.

Download or read book Wartime Report written by and published by . This book was released on 194? with total page 766 pages. Available in PDF, EPUB and Kindle. Book excerpt: Reproductions of reports, some declassified, of research done at Langley Memorial Aeronautical Laboratory during World War II. The order of reports does not represent when they were chronologically issued. Reference to the original version of each report is included.

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).

Download or read book A Flight Determination of the Tolerable Range of Effective Dihedral on a Conventional Fighter Airplane written by Charles J. Liddell and published by . This book was released on 1949 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: A conventional fighter airplane was equipped with a special device for varying the effective dihedral in flight. A survey of pilot's opinions was made to determine which values of effective dihedral were intolerable. The relation between the findings and the present Air Force-Navy stability and control specifications is discussed.

Download or read book Boatswain s Mate 1 and Chief written by United States. Bureau of Naval Personnel and published by . This book was released on 1958 with total page 484 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Final Report to the Congress written by United States. Commission on Organization of the Executive Branch of the Government (1953-1955) and published by . This book was released on 1955 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Langley Full scale tunnel Investigation of the Fuselage Boundary Layer on a Typical Fighter Airplane with a Single Liquid cooled Engine written by K. R. Czarnecki and published by . This book was released on 1946 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley full-scale tunnel to determine the thickness and shape of profile of the boundary layer on the fuselage of a typical monoplane fighter airplane with a single liquid-cooled engine. The results showed that, for the range of angles of attack and fuselage stations investigated, the maximum displacement thickness was nearly 1.2 inches and was at the most rearward station (81.6 percent of the fuselage length). The displacement thickness was found to be greatly affected by the pressure gradients over the windshield-canopy combination and in the wing-fuselage juncture. An average value for the shape parameter between 1.3 and 1.4 was obtained for the turbulent boundary layer.