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  • Other Sources  (43)
  • Fluid Mechanics and Thermodynamics
  • 1965-1969  (19)
  • 1940-1944  (24)
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  • Other Sources  (43)
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  • 1
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    Unknown
    In:  CASI
    Publication Date: 2019-11-09
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-69018 , SNA-8-D-027-VOL-4-REV-1 , JSC-E-DAA-TN75258
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  • 2
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    In:  CASI
    Publication Date: 2019-10-02
    Description: Preliminary Apollo 14 (Mission H-3) trajectory data for the July 1970 launch window are presented in this document. A general mission profile is presented, and approximate variations of selected mission parameters are indicated. Note that the information in this document is preliminary and will be updated in the Apollo 14 (Mission H-3) operational trajectory documents.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-69432 , MSC-01293 , MSC-IN-69-FM-328 , JSC-E-DAA-TN73749
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  • 3
    Publication Date: 2019-09-05
    Description: Spontaneous ignition temperature, ignition temperature, and transition temperature for metal-oxidizing gas system models of solid propellant rocket engine combustion processes
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-CR-93541 , REPT.-816
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  • 4
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    In:  CASI
    Publication Date: 2019-08-27
    Description: NHB 7121.2 is the initial publication of the guidelines for implementation of the Phased Project Planning (PPP) concept prescribed by NPD 7121,1A. These guidelines are applicable to the planning and approval activities which lead to the implementation of major new research and development projects as defined in NPD 7121.1A as well as to major modifications or extensions of approved projects. They should, therefore, be reflected in the Project Approval Documents which serve as the basic documentation for project definition, guidance and control throughout NASA. The purpose of PPP is to provide, through defined phases, an adequate basis for management decisions on the extent to which project activities can be properly undertaken and commitments made. However, these guidelines do not prescribe detailed format and content of plans and other documents and reports used to apply the PPP concept. Similarly, the work content of phases and the information requirements described herein are not checklists. They are included to assist in understanding the intent of the PPP concept and should not be viewed as rigid or inflexible. PPP, as a concept for orderly planning and definition of new major R&D undertakings, must be adapted to the peculiarities of each individual case. However, the flexibility permitted for adaptation should not be considered as a license for major variation which would compromise the objectives that underlie the concept. Cognizant NASA officials are expected to pursue their project planning and definition activities in reasonable conformance with these guidelines and to request only those exceptions or deviations which are clearly necessary and justified. These guidelines will be modified as determined necessary on the basis of experience. Comments or suggestions for changes should be directed to the Office of Organization and Management.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NHB-7121.2
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  • 5
    Publication Date: 2019-08-26
    Description: This preliminary investigation was made to study the hydrodynamic properties and general behavior of simple hydrofoils. Six 5- by 30-inch plain, rectangular hydrofoils were tested in the NACA tank at various speeds, angles of attack and depths below the water surface. Two of the hydrofoils had sections representing the sections of commonly used airfoils, one had a section similar to one developed Guidoni for use with hydrofoil-equipped seaplane floats, and three had sections designed to have constant chordwise pressure distributions at given values of the lift coefficient for the purpose of delaying the speed at which cavitation begins. The experimental results are presented as curves of the lift and drag coefficients plotted against speed for the various angles of attack and depths for which the hydrofoils were tested. A number of derived curves are included for the purpose of better comparing the characteristics of the hydrofoils and to show the effects of depth. Several representative photographs show the development of cavitation on the the upper surface of the hydrofoils. The results indicate that properly designed hydrofoil sections will have excellent characteristics and that the speed at which cavitation occurs may be delayed to an appreciable extent by the use of suitable sections.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-SR-158
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  • 6
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    In:  CASI
    Publication Date: 2019-08-16
    Description: The Navier-Stokes stress principle is checked in the light of Maxwell's mechanism of friction and in connection herewith the possibility of another theorem is indicated. The Navier-Stokes stress principle is in general predicated upon the conception of the plastic body. Hence the process is a purely phenomenological one, which Newton himself followed with his special theorem for one-dimensional flows. It remained for Maxwell to discover the physical mechanism by which the shear inflow direction is developed: According to it, this shear is only 'fictitious' as it merely represents the substitute for a certain transport on macroscopic motion quantity, as conditioned by Brown's moiecular motion and the diffusion, respectively. It is clear that this mechanism is not bound to the special case of the one-dimensioilal flows, but holds for any flow as expression of the diffusion, by which a fluid differs sharply from a plastic body. If it is remembered, on the other hand, that the cause of the stresses on the plastic body lies in a certain cohesion of the molecules, it appears by no means self evident that this difference in the mechanism of friction between fluid and plastic body should not prevail in the stress principle as well, although it certainly is desirable in any case, at least subsequently, to establish the general theorem in the sense of Maxwell. Actually, a different theorem is suggested which, in contrast to that by Navier-Stokes, has the form of an unsymmetrical matrix. Without anticipating a final decision several reasons are advanced by way of a special flow which seem to affirm this new theorem. To make it clear that the problem involved here still awaits its final solution, is the real purpose behind the present article.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1029 , Luftfahrtforschung; 18; 9; 327-330
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  • 7
    Publication Date: 2019-08-15
    Description: The differential equation of Chaplygin's jet problem is utilized to give a systematic development of particular solutions of the hodograph flow equations, which extends the treatment of Chaplygin into the supersonic range and completes the set of particular solutions. The particular solutions serve to place on a reasonable basis the use of velocity correction formulas for the comparison of incompressible and compressible flows. It is shown that the geometric-mean type of velocity correction formula introduced in part I has significance as an over-all type of approximation in the subsonic range. A brief review of general conditions limiting the potential flow of an adiabatic compressible fluid is given and application is made to the particular solutions, yielding conditions for the existence of singular loci in the supersonic range. The combining of particular solutions in accordance with prescribed boundary flow conditions is not treated in the present paper.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA/TR-790
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  • 8
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    In:  CASI
    Publication Date: 2019-08-15
    Description: A brief summary of the contents of this paper is presented here. In part I the differential equations of the problem of a gas flow in two dimensions is derived and the particular integrals by which the problem on jets is solved are given. Use is made of the same independent variables as Molenbroek used, but it is found to be more suitable to consider other functions. The stream function and velocity potential corresponding to the problem are given in the form of series. The investigation on the convergence of these series in connection with certain properties of the functions entering them forms the subject of part II. In part III the problem of the outflow of a gas from an infinite vessel with plane walls is solved. In part IV the impact of a gas jet on a plate is considered and the limiting case where the jet expands to infinity changing into a gas flow is taken up in more detail. This also solved the equivalent problem of the resistance of a gaseous medium to the motion of a plate. Finally, in part V, an approximate method is presented that permits a simpler solution of the problem of jet flows in the case where the velocities of the gas (velocities of the particles in the gas) are not very large.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1063 , Scientific Memoirs; 1-121
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  • 9
    Publication Date: 2019-08-15
    Description: For the tunnel corrections of compressible flows those profiles are of interest for which at least the second approximation of the Janzen-Rayleigh method can be applied in closed form. One such case is presented by certain elliptical symmetrical cylinders located in the center of a tunnel with fixed walls and whose maximum velocity, incompressible, is twice the velocity of flow. In the numerical solution the maximum velocity at the profile and the tunnel wall as well as the entry of sonic velocity is computed. The velocity distribution past the contour and in the minimum cross section at various Mach numbers is illustrated on a worked out-example.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1030 , Luftfahrtforschung; 18; 9; 311-316
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  • 10
    Publication Date: 2019-08-15
    Description: The flutter characteristics of several wings with an aspect-ratio of 4.0, a taper ratio of 0.2, and a quarter-chord sweepback of 45 deg. have been investigated analytically for Mach numbers up to 2.0. The calculations were based on the modified-strip-analysis method, the subsonic-kernel-function method, piston theory, and quasi-steady second-order theory. Results of t h e analysis and comparisons with experiment indicated that: (1) Flutter speeds were accurately predicted by the modified strip analysis, although accuracy at t h e highest Mach numbers required the use of nonlinear aerodynamic theory (which accounts for effects of wing thickness) for the calculation of the aerodynamic parameters. (2) An abrupt increase of flutter-speed coefficient with increasing Mach number, observed experimentally in the transonic range, was also indicated by the modified strip analysis. (3) In the low supersonic range for some densities, a discontinuous variation of flutter frequency with Mach number was indicated by the modified strip analysis. An abrupt change of frequency appeared experimentally in the transonic range. (4) Differences in flutter-speed-coefficient levels obtained from tests at low supersonic Mach numbers in two wind tunnels were also predicted by the modified strip analysis and were shown to be caused primarily by differences in mass ratio. (5) Flutter speeds calculated by the subsonic-kernel-function method were in good agreement with experiment and with the results of the modified strip analysis. (6) Flutter speed obtained from piston theory and from quasi-steady second-order theory were higher than experimental values by at least 38 percent.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-4230
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