| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce |
| 附註: | Prepared at the Lewis Research Center, Cleveland, Ohio. Cover title. "January 1961."--Cover. Includes bibliographical references. Collision integrals were calculated for the modified Stockmayer potential E(r) = 4 epsilon [(sigma/r)(exp 12) - (sigma/r)(exp 6) - delta(sigma/r)(exp 3)], which may be applied to polar molecules. It was assumed that the colliding molecules maintain their same relative orientation during the encounter. Calculations of the integrals were made for a large reduced temperature range and for a range of delta from 0 to 10. The results agree with other work on non-polar interactions (delta = 0). However for polar interactions the only previously published calculations have been found to be in error and do not agree with this work. Assuming that the molecules interact as alined dipoles of maximum attraction, values for sigma, epsilon, and delta were determined for various polar molecules by a least squares fit of experimental viscosity data. Satisfactory results were obtained for slightly polar molecules, but not for more highly polar molecules such as NH3 or H2O. Therefore, it appears that the assumed model of molecules interacting at all times as alined dipoles of maximum attraction is not satisfactory for estimating trans- port properties of polar molecules. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce] |
| 附註: | Cover title. "November 1961." Aerodynamics, missiles and space vehicles; Fluid mechanics; Mathematics. Includes bibliographical references. |
| 出版: | Los Alamos, N.M. : Los Alamos Scientific Laboratory of the University of California |
| 附註: | "Contract W-7405-ENG.36 with the U.S. Atomic Energy Commission." "LA-2486 ; Physics ; TID-4500, 16th ed." "Report written: December 1, 1960 ; Report distributed: April 14, 1961." Includes bibliographical references (p. 125-126). An analytical solution is presented to the steady-state heat-conduction equation for a heat-generating circular region which is cooled by a ring of equal holes spaced uniformly on a circle concentric with the boundary of the cylinder. The solution is based upon a class of harmonic functions previously defined by Howland. Numerical results are presented in the form of dimensionless curves for the particular examples of (a) uniform heat generation within the region with cooling at the holes and insulated outer boundary, and (b) the shape factor or conductance for this geometry. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce |
| 附註: | Cover title. "January 1961." Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Fluid mechanics. Includes bibliographical references. |
| 出版: | Washington, D.C. : U.S. Dept. of Agriculture, Statistical Reporting Service, Crop Reporting Board |
| 出版: | Washington, D.C. : U.S. Dept. of Commerce, Business and Defense Services Administration : For sale by the Superintendent of Documents, U.S. Government Printing Office |
| 出版: | Washington, D.C. : U.S. Dept. of Commerce, Business and Defense Services Administration |
| 出版: | Washington, D.C. : U.S. Department of Commerce, Business and Defense Services Administration : For sale by the Superintendent of Documents, U.S. Government Printing Office |
| 出版: | Argonne, Ill. : Argonne National Laboratory |
| 附註: | "December 1961" Bibliography: p. 39-40 Operated by the University of Chicago underContract no. W-31-109-eng-38 |
| 出版: | [Washington, D.C.] : U.S. Dept. of the Interior, Bureau of Mines |
| 附註: | Bibliography: p. 23 |
| 出版: | Oak Ridge, Tenn. : Oak Ridge National Laboratory |
| 附註: | "Date issued Nov 7 1961". Bibliography references included. |
| 出版: | Washington : National Aeronautics and Space Administration |
| 附註: | Prepared at Lewis Research Center. "June 1961." Cover title. Includes bibliographical references (p. 11-12). Experimental tests performed in vacuo indicated that a chemical adsorption reaction can be used to facilitate the cryopumping of H with liquidN-cooled condensers. Cryopumping is accomplished by reacting H with O to form H2O, which will readily condense on a liquid-N-cooled surface. The reaction in vacuo was performed on a solid catalyst, which consisted of a bed of Pd-coated alumina pellets. Cryopumping was observed at pressures as low as about 0.4 micron of mercury. A laboratory cryopump consisting of 5.8 lb of catalyst and a liquid-N-cooled condenser achieved a pumping speed of about 570 l/sec at 1.0 micron of Hg. A laboratory model of a cryopump which could be used in an electric rocket test facility was studied. The experimental data obtained were used to estimate the size of the catalyst bed necessary to test a 50-kw electric thermal rocket with an H propellant flow rate of 0.00063 kg/sec (a pumping speed of 580,000 l/sec at an operating pressure of 10 microns of Hg. (Author). |
| 出版: | [Washington, D.C.] : U.S. Dept. of the Interior, Bureau of Mines |
| 附註: | Bibliography: p. 11 |
| 出版: | Washington : Smithsonian Institution |
| 附註: | Bibliography: p. 226-241 |
| 出版: | Washington : |
| 附註: | Includes bibliographical references. |
| 出版: | Washington, [D.C.] : National Aeronautics and Space Administration |
| 附註: | Document ID: 19980227763 "NASA TN D-987." "Langley Research Center, Langley Air Force Base, Va." "December 1961." Cover title. Includes bibliographical references (p. 31). The variational principle, differential equations, and boundary conditions governing the cross-sectional distortions due to inertia loading of a two-dimensional model of a thin monocoque wing are shown. A theoretical analysis of this simplified model is made in order to determine the nature of the coupling between the cross-sectional modes and the spanwise deformation modes. General solutions are obtained in finite-difference form for arbitrary cross sections and an exact solution is presented for a parabolic-arc cross section of constant cover thickness. The application of these results in evaluating the coupled frequencies of the actual structure is discussed. Frequencies evaluated for a parabolic-arc monocoque beam show good agreement with experimental values. Also available via Internet from NASA Technical Reports Server. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce |
| 附註: | Cover title. "April 1961." Major NASA subject terms Includes bibliographical references. Abstract |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce |
| 附註: | Major NASA subject terms: CYLINDRICAL BODIES CAVITIES ZIRCONIUM DIFFUSION THEORY HYDROGEN CRITICAL MASS BUCKLING. Prepared at the Lewis Research Center, Cleveland, Ohio. Cover title. "October 1961."--Cover. Includes bibliographical references. The results of a multigroup, diffusion theory study of spherical gaseous-core cavity reactors are presented in this report. The reactor cavity of gaseous U235 is enclosed by a region of hydrogen gas and is separated from an external D2O moderator-reflector by a zirconium structural shell. Some cylindrical reactors are also investigated. A parametric study of spherical reactors indicates that, for the range of variables studied, critical mass increases as: (1) Fuel region is compressed within the reactor cavity, (2) moderator thickness is decreased, (3) structural shell thickness is increased, and (4) moderator temperature is increased. A buckling analogy is used to estimate the critical mass of fully reflected cylindrical reactors from spherical results without fuel compression. For a reactor cavity of a 120-centimeter radius uniformly filled with fuel, no structural shell, a moderator temperature of 70 F, and a moderator thickness of 100 centimeters, the critical mass of a spherical reactor is 3.1 kilograms while that of a cylinder with a length-to-diameter ratio of 1.0 (L/D = 1) is approximately 3.8 kilograms and, with L/D = 2, 5.9 kilograms. For the range of variables considered for U235-D2O gaseous-core cavity reactors, the systems are characterized by 95 to 99 percent thermal absorptions, with the flux reaching a maximum in the moderator about 10 to 15 centimeters from the reactor cavity. |
| 出版: | Washington : U.S. Dept. of Agriculture |
| 附註: | Literature cited: p. 23-33 |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce] |
| 附註: | Cover title. "January 1961." Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Fluid mechanics. Includes bibliographical references. |
| 出版: | Cambridge, Mass. : Massachusetts Institute of Technology, Dept. of Civil and Sanitary Engineering |
| 出版: | Garden City, N.Y. : Doubleday |
| 出版: | New York : Basic Books |
| 出版: | Tallahassee. : |
| 附註: | Conferences sponsored by the National Science Foundation and the Office of Naval Research. |
| 出版: | Washington, D.C. : U.S. Navy Hydrographic Office |
| 出版: | Washington, D.C. : U.S. Navy Hydrographic Office |
| 出版: | Washington, D.C. : U.S. Navy, Hydrographic Office |
| 出版: | Washington : U.S. Govt. Print. Off. |
| 出版: | New York : Macmillan |
| 附註: | Includes bibliographies. Part of illustrative matter in pockets. |
| 出版: | College Station, Tex. : IGY World Data Center A: Oceanography, Dept. of Oceanography and Meteorology, Agricultural and Mechanical College of Texas |
| 出版: | La Jolla : University of California, Scripps Institution of Oceanography |
| 出版: | La Jolla, Calif. : University of California, Scripps Institution of Oceanography |
| 出版: | Washington : |
| 附註: | "Original edition, 1954 [prepared by U. S. Naval Hospital Corps School, Naval Hospital, Portsmouth, Va.]" Cover title. |
| 出版: | Washington : For sale by the Superintendent of Documents., U. S. Govt. Print. Off. |
| 附註: | Cover title. |
| 出版: | Washington : Office of Naval Research, Dept. of the Navy |
| 附註: | "ONR-9." Includes bibliographical references. |
| 出版: | Washington, [D.C.] : National Aeronautics and Space Administration |
| 附註: | Report Number: L-1757 Document ID: 19980228464 "NASA TN D-983." "Langley Research Center, Langley Air Force Base, Va." "November 1961." Cover title. Includes bibliographical references (p. 4). An investigation has been made in the Langley 7- by 10-foot transonic tunnel to determine the subsonic pressure distribution of three paraglider models through an angle-of-attack range from 0° to 74°. Three rigid metal models simulated a 45° basic flat planform paraglider with leading-edge sweep angles of 61.6°, 52.5°, and 48.6°. These configurations resulted in one-half-circle, one-third-circle, and one-quarter-circle semispan trailing-edge curvature when viewed from downstream. The results of the investigation are presented as curves of chordwise pressure distributions at four spanwise locations. Also available from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 4/09/07: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19980228464_1998393854.pdf. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce |
| 附註: | Cover title. "February 1961."--Cover. Includes bibliographical references. Measurements were made to determine the effects of sting-support diameter on the base pressures of an elliptic cone with ratio of cross-section thickness to width of 1/3 and a plan-form, semi-apex angle of 15 deg. The investigation was made for model angles of attack from -2 deg to +20 deg at Mach numbers from 0.60 to 1.40, and for a constant Reynolds number of 1.4 million, based on the length of the model. The results indicated that the sting interference decreased the base axial-force coefficients by substantial amounts up to a maximum of about one-third the value of the coefficient for no sting interference. There was no practical diameter of the sting for which the effects of the sting on the base pressures would be negligible throughout the Mach number and angle-of-attack ranges of the investigation. |
| 出版: | Washington : National Aeronautics and Space Administration |
| 附註: | Prepared at Langley Research Center. "June 1961." Cover title. Includes bibliographical references (p. 6). |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration |
| 附註: | "October 1961." Cover title. Includes bibliographical references (p. 10-11). Full text also available online. Address as of 11/15/2010:http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19670022810_1967022810.pdf. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration |
| 附註: | "December 1961." Cover title. Includes bibliographical references (p. 12-13). Full text also available online. Address as of 11/15/2010:http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19670022640_1967022640.pdf. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration |
| 附註: | "July 1961." Cover title. Includes bibliographical references (p. 16-17). Full text also available online. Address as of 11/12/2010:http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19670022202_1967022202.pdf. |