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  • Aerodynamics  (12)
  • Inorganic Chemistry  (5)
  • GENERAL
  • 1955-1959  (17)
  • 1945-1949  (1)
  • 1959  (17)
  • 1945  (1)
  • 1
    Electronic Resource
    Electronic Resource
    Über Benzal-Derivate des L-Idits (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2694-2700 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die von E. Fischer und G. Bertrand beschriebenen Tribenzal-L-idite erwiesen sich als identisch mit 1.3;2.4;5.6-Tribenzal-L-idit. Unter wenig abgeänderten Versuchsbedingungen entsteht neben dem Tribenzal-L-idit ein Dibenzal-Derivat, welches einen 2.3.4.5-, wahrscheinlich 2.4;3.5-Dibenzal-L-idit darstellt. Es wird auf den unterschiedlichen Verlauf der Acetalisierung des L-Idits mit Benzaldehyd, bzw. Formaldehyd hingewiesen.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19590921103
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  • 2
    Electronic Resource
    Electronic Resource
    Über Tris-trimethylendiamin-Komplexe des dreiwertigen Chroms (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 302 (1959), S. 1-9 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: A method of preparing [Cr tn3]Cl3 (tn = NH2 · CH2 · CH2 · CH2 · NH2) by direct interaction between CrCl3 and trimethylene diamine is described. From the new compound, complex salts of the type [Cr tn3]X3 with X = Br-, J-, ClO-4, and NO-3 have been obtained.The absorption spectrum of [Cr tn3]+ is given. Attempts to isolate optical antipodes are described.
    Notes: Es wird eine Methode zur Darstellung von [Cr tn3]Cl3(tn = NH2 · CH2 · CH2 ·CH2 · NH2) in direkter Reaktion aus CrCl3 und Trimethylendiamin angegeben. Aus dem Chlorid erhält man durch Umfällen mit entsprechenden Säuren und Alkalisalzen [Cr tn3]X3 mit X = Br-, J-, ClO-4 und NO-3. Das Absorptionsspektrum von [Cr tn3]3+ wird mitgeteilt. Versuche zur Trennung in die optischen Antipoden werden beschrieben.
    Additional Material: 2 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19593020102
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  • 3
    Electronic Resource
    Electronic Resource
    Über die Bildung salzartiger Verbindungen bei der Umsetzung von Antimon(V)-chlorid mit Äthylat (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 302 (1959), S. 88-102 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: On reaction of SbCl5 with NaOC2H5 salt-like compounds with cation co-ordination number 4 and anion co-ordination number 6 are formed: [SbCla(OC2H5)4-a] [SbClb(OC2H5)6-b]. In polar solvents these substances show electrolytical conductivity and their molecular weights in dilute solution prove complete dissociation into two particles. In nonpolar solvents the compounds are also dissolved but now in a molecular form SbClc(OC2H5)5-c. The latter solutions have no electrolytical conductivity. IR-spectra of the compounds in polar and nonpolar solutions are different from each other.
    Notes: Bei der Umsetzung von SbCl5 mit NaOC2H5 entstehen heteropolare Verbindungen mit 4fach koordiniertem Kation und 6fach koordiniertem Anion: [SbCla(OC2H5)4-a] [SbClb(OC2H5)6-b]. In polaren Lösungsmitteln zeigen diese Substanzen elektrolytische Leitfähigkeit und Molekulargewichte, die in verdünnter Lösung auf vollständige Dissoziation schließen lassen. In unpolaren Lösungsmitteln sind die Verbindungen in homöopolarer Form SbClc(OC2H5)5-c gelöst. Diese Lösungen zeigen nur sehr geringe Leitfähigkeit. Die Infrarotspektren der Verbindungen in polaren und unpolaren Lösungen unterscheiden sich stark voneinander.
    Additional Material: 13 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19593020109
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  • 4
    Electronic Resource
    Electronic Resource
    Complex Compounds of n-Hexyl Biguanide with metallic Elements (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 302 (1959), S. 237-240 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Es werden Chelatkomplexe des n-Hexylbiguanids mit Kupfer(II), Nickel(II), Kobalt(III) und Chrom(III) beschrieben. Es konnte ferner Dipyridino-dibiguanidino-kobalt(III)-hydroxyd dargestellt werden.
    Notes: A study of n-hexyl biguanide as a chelating ligand has been made, and its complex compounds with copper(II), nickel(II), cobalt(III) and chromium(III) have been described. A cobaltic complex containing pyridine along with the biguanide, dipyridinocobaltic bis-n-hexyl biguanidinium hydroxide, has also been isolated.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19593020312
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  • 5
    Electronic Resource
    Electronic Resource
    Über die Hydrolyse des Antimon(V)-säureäthylesters (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 301 (1959), S. 339-342 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Sb(OC2H5)5 is hydrolized on action with ½ mol of water yielding the dimeric ester (C2H5O)4Sb—O—Sb(OC2H5)4. By larger quantities of water polymeric chains and net works are formed.
    Notes: Durch Hydrolyse von Sb(OC2H5)5 mit einem halben Mol Wasser entsteht die kondensierte Verbindung (C2H5O)4SbOSb(OC2H5)4. Größere Mengen an Wasser führen zu ketten förmigen und vernetzten Produkten.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19593010518
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  • 6
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    Ground Measurements of the Shock-Wave Noise from Airplanes in Level Flight at Mach Numbers to 1.4 and at Altitudes to 45000 Feet (1959)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Time histories of noise pressures near ground level were measured during flight tests of fighter-type airplanes over fairly flat, partly wooded terrain in the e Mach number range between 1.13 and 1.4 and at altitudes from 25,000 to 45,000 feet. Atmospheric soundings and radar tracking studies were made for correlation with the measured noise data. The measured and calculated values of the pressure rise across the shock wave were generally in good agreement. There is a tendency for the theory to overestimate the pressure at locations remote from the track and to underestimate the pressures for conditions of high tailwind at altitude. The measured values of ground-reflection factor averaged about 1.8 f or the surface tested as compared to a theoretical value of 2.0. P o booms were measured in all cases. The observers also generally reported two booms; although, in some cases, only one boom was reported. The shock-wave noise associated with some of the flight tests was judged to be objectionable by ground observers, and in one case the cracking of a plate-glass store window was correlated in time with the passage of the airplane at an altitude of 25,000 feet.
    Keywords: Aerodynamics
    Type: NASA-TN-D-48
    Format: application/pdf
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  • 7
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    Determination of the Stability and Control Characteristics of a Tailless All-Wing Airplane Model with Sweepback in the Langley Free-Flight Tunnel (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Force and flight tests were performance on an all-wing model with windmilling propellers. Tests were conducted with deflected and retracted flaps, with and without auxiliary vertical tail surfaces, and with different centers of gravity and trim coefficients. Results indicate serious reduction of stick-fixed longitudinal stability because of wing-tip stalling at high lift coefficient. Directional stability without vertical tail is undesirably low. Low effective dihedral should be maintained. Elevator and rudder control system is satisfactory.
    Keywords: Aerodynamics
    Type: NACA-WR-L-50 , NACA-ACR-L5A13
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  • 8
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    Performance Characteristics of Flush and Shielded Auxiliary Exits at Mach Numbers of 1.5 to 2.0 (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The performance characteristics of several flush and shielded auxiliary exits were investigated at Mach numbers of 1.5 to 2.0, and jet pressure ratios from jet off to 10. The results indicate that the shielded configurations produced better overall performance than the corresponding flush exits over the Mach-number and pressure-ratio ranges investigated. Furthermore, the full-length shielded exit was highest in performance of all the configurations. The flat-exit nozzle block provided considerably improved performance compared with the curved-exit nozzle block.
    Keywords: Aerodynamics
    Type: NASA-MEMO-5-18-59E , E-139
    Format: application/pdf
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  • 9
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    The Effects of Streamwise-Deflected Wing Tips on the Aerodynamic Characteristics of an Aspect Ratio-2 Triangular Wing, Body, and Tail Combination (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation has been conducted on a triangular wing and body combination to determine the effects on the aerodynamic characteristics resulting from deflecting portions of the wing near the tips 900 to the wing surface about streamwise hinge lines. Experimental data were obtained for Mach numbers of 0.70, 1.30, 1.70, and 2.22 and for angles of attack ranging from -5 deg to +18 deg at sideslip angles of 0 deg and 5 deg. The results showed that the aerodynamic center shift experienced by the triangular wing and body combination as the Mach number was increased from subsonic to supersonic could be reduced by about 40 percent by deflecting the outboard 4 percent of the total area of each wing panel. Deflection about the same hinge line of additional inboard surfaces consisting of 2 percent of the total area of each wing panel resulted in a further reduction of the aerodynamic center travel of 10 percent. The resulting reductions in the stability were accompanied by increases in the drag due to lift and, for the case of the configuration with all surfaces deflected, in the minimum drag. The combined effects of reduced stability and increased drag of the untrimmed configuration on the trimmed lift-drag ratios were estimated from an analysis of the cases in which the wing-body combination with or without tips deflected was assumed to be controlled by a canard. The configurations with deflected surfaces had higher trimmed lift-drag ratios than the model with undeflected surfaces at Mach numbers up to about 1.70. Deflecting either the outboard surfaces or all of the surfaces caused the directional stability to be increased by increments that were approximately constant with increasing angle of attack at each Mach number. The effective dihedral was decreased at all angles of attack and Mach numbers when the surfaces were deflected.
    Keywords: Aerodynamics
    Type: NASA-MEMO-5-18-59A
    Format: application/pdf
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  • 10
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    Low-Speed Wind-Tunnel Investigation of Blowing Boundary-Layer Control on Leading- and Trailing-Edge Flaps of a Large-Scale, Low-Aspect-Ratio, 45 Swept-wing Airplane Configuration (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Blowing boundary-layer control was applied to the leading- and trailing-edge flaps of a 45 deg sweptback-wing complete model in a full-scale low-speed wind-tunnel study. The principal purpose of the study was to determine the effects of leading-edge flap deflection and boundary-layer control on maximum lift and longitudinal stability. Leading-edge flap deflection alone was sufficient to maintain static longitudinal stability without trailing-edge flaps. However, leading-edge flap blowing was required to maintain longitudinal stability by delaying leading-edge flow separation when trailing-edge flaps were deflected either with or without blowing. Partial-span leading-edge flaps deflected 60 deg with moderate blowing gave the major increase in maximum lift, although higher deflection and additional blowing gave some further increase. Inboard of 0.4 semispan leading-edge flap deflection could be reduced to 40 deg and/or blowing could be omitted with only small loss in maximum lift. Trailing-edge flap lift increments were increased by boundary-layer control for deflections greater than 45 deg. Maximum lift was not increased with deflected trailing-edge flaps with blowing.
    Keywords: Aerodynamics
    Type: NASA-MEMO-1-23-59A
    Format: application/pdf
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