![Propellant Vaporization as Criterion for Rocket-engine Design, Experimental Performance, Vaporization, and Heat-transfer Rates with Various Propellant Combinations [with List of References] PDF](https://books.google.com/books/content/images/frontcover/UzExQwAACAAJ?fife=w150-h200)
Author: Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 31
Book Description
Propellant Vaporization as Criterion for Rocket-engine Design, Experimental Performance, Vaporization, and Heat-transfer Rates with Various Propellant Combinations [with List of References]
![Propellant Vaporization as Criterion for Rocket-engine Design, Experimental Performance, Vaporization, and Heat-transfer Rates with Various Propellant Combinations [with List of References] PDF](https://books.google.com/books/content/images/frontcover/UzExQwAACAAJ?fife=w80-h100)
Author: Propellant Vaporization as a Design Criterion for Rocket-engine Combustion Chambers
Author: Richard J. PriemPublisher:
ISBN:
Category : Combustion chambers
Languages : en
Pages : 64
Book Description
Propellant Vaporization as a Criterion for Rocket-engine Design
Author: Marcus F. HeidmannTechnical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1274
Book Description
NASA Technical Note
Author: Tables of Characteristic Functions for Solving Boundary-value Problems of the Wave Equation with Application to Supersonic Interference
Author: Jack Norman NielsenPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 682
Book Description
Tables are presented containing 69,000 values of a set of characteristic functions which first arose in problems of supersonic wing-body interference. The tables are useful in problems of supersonic flow involving aerodynamic shapes which are wholly or in part quasi-cylinders of nearly circular cross section. A number of uses are described in the aerodynamics of bodies alone, body-body or shock-body interference, wing-body interference, the vortex-panel interference. Three illustrative examples are worked out in detail. First, the pressure field due to fuselage indentation is calculated and presented in a form independent of Mach number. Secondly, the tables are applied to a problem involving a previously unpublished solution to the Navier-Stokes equations; namely, the boundary-layer profiles of a circular cylinder moved impulsively with a constant axial force in a viscous incompressible fluid. In the final example, the wave drag of corrugated circular cylinders is calculated as a function of the number of corrugations and their wave length. Several nonaerodynamic applications are pointed out in the fields of acoustics and heat conduction. Generally speaking, the tables are applicable to boundary-value problems of the second kind involving the wave equation in three dimensions with approximately circular cylindrical boundaries or involving the unsteady heat-conduction equation in two space dimensions with nearly circular boundaries.
Technical Note
Author: NASA Technical Report
Author: Spatial Characteristics of Water Spray Formed by Two Impinging Jets at Several Jet Velocities in Quiescent Air
Author: Hampton H. FosterPublisher:
ISBN:
Category : Water jets
Languages : en
Pages : 38
Book Description
The spatial characteristics of a spray formed by two impinging water jets in quiescent air were studied over a range of nominal jet velocities of 30 to 74 feet per second. The total included angle between the 0.089-inch jets was 90 deg. The jet velocity, spray velocity, disappearance of the ligaments just before drop formation, mass distribution, and size and position of the largest drops were measured in a circumferential survey around the point of jet impingement. Photographic techniques were used in the evaluations. The distance from the point of jet impingement to ligament breakup into drops was about 4 inches on the spray axis and about 1.3 inches in the radial position +/-90 deg from the axis. The distance tended to increase slightly with increase in jet velocity. The spray velocity varied from about 99 to about 72 percent of the jet velocity for a change in circumferential position from the spray axis to the +/-80 deg positions. The percentages tended to increase slightly with an increase in jet velocity. Fifty percent of the mass was distributed about the spray axis in an included angle of slightly less than 40 deg. The effect of jet velocity was small. The largest observed drops (2260-micron or 0.090-in. diam.) were found on and about the spray axis. The size of the largest drops decreased for an increase in radial angular position, being about 1860 microns (0.074 in.) at the +/-90 deg positions. The largest drop sizes tended to decrease for an increase in jet velocity, although the velocity effect was small. A drop-size distribution analysis indicated a mass mean drop size equal to 54 percent of an extrapolated maximum drop size.
Effect of Impingement Angle on Drop-size Distribution Abd Spray Pattern of Two Impinging Water Jets
Author: Marcus F. HeidmannPublisher:
ISBN:
Category : Chemical engineering
Languages : en
Pages : 38
Book Description
Sprays produced by two 0.089-inch-diameter jets at impingement angles of 10 to 90 degrees and jet velocities of 30 to 74 feet per second were studied. Drop-size distributions for sprays formed in 100-foot-per-second air are presented. Distributions were bimodal in character, and the effects of test conditions on the bimodal properties are presented. Photographs of the overall spray pattern produced in quiescent air are also shown.