Download or read book Aerodynamic Characteristics of a Spoiler slot deflector Control on a 45 Sweptback Wing at Mach Numbers of 1 61 and 2 01 written by Douglas R. Lord and published by . This book was released on 1957 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the aerodynamic characteristics of a spoiler-slot-deflector control on a 45 degree sweptback wing having an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. The model was equipped with a 15-percent-chord spoiler-slot-deflector extending from 13 o 78 percent of the wing semispan. The spoiler and deflector were hinged along the 60- and 75-percent-chord lines, respectively. Tests were made at a Reynolds number of 3,000,000 (based on the mean aerodynamic chord of the wing) and covered ranges of angles of attack from -3 to 15 degrees, spoiler projections from 0 to 8.0 percent chord, and deflector projections from 0 to 7.6 percent chord.
Download or read book Aerodynamic Characteristics of a Spoiler slot deflector Control on a 45 Sweptback wing fuselage Model at High Subsonic Speeds written by Alexander D. Hammond and published by . This book was released on 1960 with total page 80 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 Investigation at Transonic Speeds of Loading Over a 30 Deg Sweptback Wing of Aspect Ratio 3 Taper Ratio 0 2 and NACA 65A004 Airfoil Section Mounted on a Body written by Donald D. Arabian and published by . This book was released on 1960 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic load characteristics of a wing-body combination were determined experimentally at Mach numbers from 0.80 to 1.03 for angles of attack up to 26 degrees. Two wings, both with 30 degrees sweep of the quarter-chord line, taper ratio of 0.2, aspect ratio of 3, and thickness of 4 percent chord, but of different types of construction, were tested. One wing was of solid steel and the other was of plastic with an inner steel core ...
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 1956 with total page 104 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 has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.
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 Investigation of Transonic Flutter Characteristics of a Thin 10 Degree Sweptback Wing Having an Aspect Ratio of 4 and a Taper Ratio of 0 6 written by George W. Jones and published by . This book was released on 1957 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: A flutter investigation has been made in the Langley transonic blowdown tunnel at Mach numbers between 0.79 and 1.34 on a thin 10 degree sweptback wing having an aspect ratio of 4 and a taper ratio of 0.6. The data obtained have been compared with data from NACA Research Memorandum L55I13A for zero and 30 degree sweptback wings of the type investigated, the flutter boundary for the 10 degree sweptback wing falls between those for the zero degree and 30 degree sweptback wings in the low supersonic Mach number range. However, the subsonic level (around a Mach number of 0.8) of the flutter boundary for the 10 degree sweptback wing lies above those for the zero and 30 degree sweptback wings. In addition, the amount of rise in the flutter boundary from the subsonic level to the supersonic values is about the same for the wings with angles of sweepback of 10 degrees and zero degrees, but is much greater for the wing with an angle of sweepback of 30 degrees.
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 Investigation of the Aerodynamic Characteristics in Pitch and Sideslip of a 45 Swept wing Airplane Configuration with Various Vertical Locations of the Wing and Horizontal Tail written by M. Leroy Spearman and published by . This book was released on 1957 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.
Download or read book A Comparison of the Lateral Controllability with Flap and Plug Ailerons on a Sweptback wing Model Having Full span Flaps written by Powell M. Lovell and published by . This book was released on 1950 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A free-flight-tunnel investigation has been made to compare the dynamic lateral control characteristics provided by step plug ailerons on a sweptback-wing model having full-span flaps. The model had a 38 degree sweptback wing with an aspect ratio of 3 and a taper ratio of 0.05. The static stability and control characteristics of the flight-test model were determined from force tests and the time-lag characteristics of the ailerons were determined from stand tests in which there was freedom only in roll. Flight tests of the model were made over a range of lift coefficient from 1.0 through the stall.
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.
