means detachably securing each said curtain to its adjacent partition member along one edge thereof. 2,712,420. Vertical Take-Off Airplane and Control System Therefor. W. H. Amster, C. H. Holleman and E. V. Browne, assignors to Northrop Aircraft, Inc. These details and drawings of patents granted in the United States are taken, by permission of the Application December 1, 1951. Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies of the full specifications can be obtained, price 25 cents each, from the Commissioner of Patents, Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, Southampton Buildings, Chancery Lane, London, W.C.2. 2,709,052. Spanwise Flow Control of Fluid Swept of two axially spaced but closely adjacent rows of holes Lifting Surfaces. M. W. Berg, assignor of one-half to in one of said walls, the holes in one row being stag C. J. Fletcher. Application April 15, 1952. gered circumferentially with respect to the holes in the other row, the rows of holes being spaced from each other in the direction of gas flow through the passage far enough to provide an imperforate wall portion between the two rows, and means located on the side A vertically rising aeroplane comprising a fuselage, of said one wall opposite to the gas path and providing a wing attached to said fuselage and having a relatively a fluid connexion solely between said two rows of high dihedral angle, said wing being essentially straight in plan-form, an elongated fore-and-aft pod member holes in order, as a result of the static pressure at each wing tip, a ventral fin extending downwardly gradient which increases in a downstream direction under the rear of said fuselage, and landing strut as a result of the diffusing action, to produce an out means including a wing tip strut in the aft end of each flow from the passage through the downstream row of of said pod members and rearwardly extending fin holes and a return flow into the passage through the strut means attached near the lower extremity of said A lifting surface or body, such as an aeroplane wing, upstream row of holes thereby producing trailing adapted to be driven through fluids, such as air; said ventral fin. vortices projecting downstream from the upstream lifting body having a plan view form such that the row of holes for energizing the boundary layer. leading and trailing edges of said plan view form are 2,712,421. Folding Wing Aircraft. D. J. Naumann, swept aft with respect to a vertical plane transverse to assignor to North American Aviation, Inc. Applica 2,709,569. Impeller Member and Method of Mak the plane of symmetry or longitudinal axis of the said tion August 21, 1953. ing Same. M. S. Roush, assignor to Thompson lifting body; said lifting body having a structure within Products, Inc. Application August 28, 1948. In an aircraft having folding wings, first and second the said plan view form incorporating root, tip and wing portions relatively foldable with respect to each one or more intermediate aerofoil sections specifically other, a first movable surface pivotally mounted upon shaped wherein the radii of curvature of the leading said first wing portion, a second movable surface and trailing edges and the chordwise positions of the pivotally mounted upon said second wing portion, maximum thickness of said aerofoil sections vary means for folding one of said wing portions with spanwise from root to tip in a progressive and pro respect to the other said wing portion, and means portionate manner forming smooth surface contours including a pair of universally interconnected links of and between the said aerofoil sections; whereby the An impeller blade for a compressor comprising a separately connected respectively to each of said structure of the said root section consists of the base portion for attachment to a support member and following three features: one, a sharp leading edge an aerofoil section extending beyond said base portion, formed by an edge radius smaller than the edge radius said blade having a metallic aerofoil surface enveloped of the trailing edge of feature two following; two, a within a layer of an organosiloxane polymer firmly blunt trailing edge formed by an edge radius larger bonded to the surface by a chemical reaction with the than the edge radius of the leading edge of feature one metal surface and a metal oxide layer interposed preceding; and three, a position of maximum thick between, said polymer layer being less than 0·004 inch ness, defined in per cent of the aerofoil section chord, thick and the coated aerofoil surface being non- closest to the trailing edge; whereby the structure of wettable by water and air, being corrosion and erosion the said tip section consists of the following three resistant, and possessing improved aerodynamic features: one, a blunt leading edge formed by an edge properties. radius larger than the edge radius of the trailing edge of feature two following; two, a sharp trailing edge movable surfaces whereby the relative disposition of 2,710,731. Removable Bulkhead for Aircraft. H. E. formed by an edge radius smaller than the edge radius each said movable surface with respect to its respective Bright and B. C. Mann, assignors to The Glenn L. of the leading edge of feature one preceding; and wing portion is maintained during the folding of said Martin Company. Application June 25, 1952. three, a position of maximum thickness, defined in wing portion. per cent of the aerofoil section chord, closest to the leading edge; and whereby the structure of the said 2,715,011. Ceramic Blade for Turbine Engine. one or more intermediate aerofoil sections between C. Schörner, assignor to Maschinenfrabrik Augsburg- said root and tip sections have radii of curvature of Nurnberg A. G. Application December 29, 1949. their leading and trailing edges, and positions of maximum thickness, defined in per cent of the aerofoil In a gas turbine having a metal rotor and a plurality section chord, progressively and proportionately of composite ceramic blades mounted around the altered in a manner whereby smooth surface fairing of rim thereof, the combination which comprises a plu and between the said aerofoil sections at root and tip rality of transverse grooves in the rim of said rotor for with the said intermediate sections thereof is provided. receiving said blades, each of said grooves having a por tion disposed substantially axially of said rotor and a second portion disposed at an angle to said axial por tion, a plurality of separate ceramic blade elements 2,709,337. Boundary Layer Control for the Diffuser assembled in edge-to-edge arrangement on said rotor of a Gas Turbine. S. J. Markowski, assignor to United forming each said blade, each of said elements having Aircraft Corporation. Application March 28, 1952. In an aircraft having a cabin including a plurality a vane part and a root part which completely under of seats in orderly arrangement along opposite sides lies the entire cross section of said vane part, means for thereof, a supporting brace structure comprising an affixing the root part of one of said elements in said upper transverse member, and a pair of lower brace axial portion of said groove in said rotor, and means members depending therefrom and spaced laterally for affixing the root part of another of said elements in inwardly from the sides of said cabin, attaching means provided on said cabin and said brace structure for detachably securing said brace structure to the upper portion of said cabin at any one of a plurality of locations spaced longitudinally along said cabin, a pair of partition members supported by said brace The combination with a gas turbine, a thrust nozzle structure and disposed at opposite sides of said cabin downstream of the turbine, and outer and inner annu to form a generally rectangular doorway between the lar walls defining an annular gas passage extending sides, said partition members each comprisingan upper downstream from the turbine toward the thrust panel portion detachably secured to one of said brace nozzle, the outer wall constituting a duct connecting members, and a lower flexible portion supported at its the turbine to the thrust nozzle, the adjacent surfaces upper end by said panel portion, means detachably of said inner and outer walls being substantially said second portion of said groove, the vane parts of fastening the lower end of each said flexible portion to smooth and being spaced apart to define the passage, said assembled elements forming for each said blade a said cabin to cause the lower portion thereof to lie said inner and outer walls diverging from each other continuous curved working surface and the root parts snugly against the rear side of a pair of said seats, in a downstream direction such that the gas passage of said elements abutting at a substantial angle and a pair of curtains slidably supported by said trans is of increasing cross-sectioned area in a downstream having a substantially rectilinear transverse cross direction to produce a diffusing action in the passage, verse member to form a closure for said doorway, and section. 390 Aircraft. Engineering
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Nov 1, 1955
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