scholarly journals One-Dimensional Flow Model of a Pseudo-Shock Wave in a Constant-Area Duct.

1995 ◽  
Vol 61 (592) ◽  
pp. 4359-4365 ◽  
Author(s):  
Yoshiaki Miyazato ◽  
Kazuyasu Matsuo
Keyword(s):  
Shock Wave ◽  
Flow Model ◽  
One Dimensional ◽  
Dimensional Flow ◽  
Constant Area

An Evaluation of the Average Flow Model [1] for Surface Roughness Effects in Lubrication

1980 ◽  
Vol 102 (3) ◽  
pp. 360-366 ◽  
Author(s):  
J. L. Teale ◽  
A. O. Lebeck
Keyword(s):  
Surface Roughness ◽  
Flow Model ◽  
Two Dimensional ◽  
Roughness Effects ◽  
Important Conclusion ◽  
Average Flow ◽  
One Dimensional ◽  
Dimensional Flow ◽  
Two Dimensional Flow ◽  
Average Flow Model

The average flow model presented by Patir and Cheng [1] is evaluated. First, it is shown that the choice of grid used in the average flow model influences the results. The results presented are different from those given by Patir and Cheng. Second, it is shown that the introduction of two-dimensional flow greatly reduces the effect of roughness on flow. Results based on one-dimensional flow cannot be relied upon for two-dimensional problems. Finally, some average flow factors are given for truncated rough surfaces. These can be applied to partially worn surfaces. The most important conclusion reached is that an even closer examination of the average flow concept is needed before the results can be applied with confidence to lubrication problems.

Numerical Simulation of Supersonic Combustion in Quasi One-Dimensional Flow

1991 ◽  
Author(s):  
T. Gary Yip
Keyword(s):  
Flow Model ◽  
Cone Angle ◽  
Initial Pressure ◽  
Supersonic Combustion ◽  
Propulsion Systems ◽  
One Dimensional ◽  
Hypersonic Propulsion ◽  
Dimensional Flow ◽  
Conical Shock ◽  
Shock System

Abstract Supersonic combustion induced by a two-shock system has been studied using a chemical nonequilibrium, quasi one-dimensional flow model. The combustion of stoichiometric, premixed H2-air is described by a chemistry model which consists of 11 species and 28 reactions. The freestream Mach numbers used in this calculations are 8, 10 and 12. The initial pressure is 0.01 atm and temperature 300 K. The first of the two shocks is a conical shock and the second is its reflection. Supersonic combustion has been predicted to occur at combustor pressures between 0.8 and 2.9 atmospheres, and temperatures between 1500 and 3000 K. The Mach number of the flow in the combustor is between 1.7 and 4. These combustor conditions are typical of the future hypersonic propulsion systems. The results also show the changes in the composition of the flow during the induction and heat release phases. The two-shock system is assumed to be generated by a cone. For Mach 8, 10 and 12, the minimum cone angle for generating a strong enough two-shock system to induce supersonic combustion has also been identified.

A Theory for the High-Speed Flow of Gas-Solids Mixtures under Conditions of Equilibrium and Constant Fractional Lag

1969 ◽  
Vol 184 (3) ◽  
pp. 59-66 ◽  
Author(s):  
B. N. Cole ◽  
H. M. Bowers ◽  
F. R. Mobbs
Keyword(s):  
Mach Number ◽  
Speed Of Sound ◽  
Gas Dynamics ◽  
High Speed ◽  
Solid Particles ◽  
High Speed Flow ◽  
One Dimensional ◽  
Dimensional Flow ◽  
Speed Flow ◽  
Constant Area

A theory is presented for the high-speed, one-dimensional flow of a gas-solids mixture, assuming constant fractional lags of temperature and velocity between the solid particles and the gas. A mixture speed of sound is is derived and used as the basis of a mixture Mach number. Expressions are deduced which are parallel to many well-known relationships in orthodox one-dimensional gas dynamics. The investigation covers frictionless flow in a variable area duct and flow with friction in a constant area duct. The effect of solids volume is also taken into account.

scholarly journals Predicted response of the calving glacier Svartisheibreen, Norway, and outbursts from it, to future changes in climate and lake level

1997 ◽  
Vol 24 ◽  
pp. 16-20 ◽  
Author(s):  
Michael Kennett ◽  
Tron Laumann ◽  
Bjarne Kjøllmoen
Keyword(s):  
Mass Balance ◽  
Lake Level ◽  
Flow Model ◽  
Peak Discharge ◽  
Northern Norway ◽  
One Dimensional ◽  
Dimensional Flow ◽  
Glacier Front

The Svartisheibreen glacier in northern Norway has been investigated since 1988 in connection with a proposed hydropower scheme. The scheme includes regulation of the lake into which the glacier calves. A one-dimensional flow model has been used to estimate the response of the glacier to changes in mass balance and lake level. The model predicts that a net balance, excluding calving, of 0 m a−1 will cause the glacier to retreat approximately 400 m over 50 years if lake level is maintained at 774 m a.s.l., but that the glacier front will not move significantly if lake level is lowered to 720 m a.s.l. In 1989 and 1991, lake outbursts occurred beneath the glacier. The 1991 outburst was monitored, and culminated in a peak discharge of only 3.5 m3 s−1, much less than for other reported outbursts. This outburst can be explained in a model in which the outburst tunnel passes over a subglacial threshold approximately 70 m behind the 1991 calving front. The model shows that outbursts will probably increase dramatically in size if the front retreats beyond this threshold.

scholarly journals The Effect of the Flow Distribution on the Thermal Efficiency of a Solar Collector

1986 ◽  
Vol 39 (6) ◽  
pp. 945 ◽  
Author(s):  
MJ O'Keefe ◽  
JLA Francey
Keyword(s):  
Flat Plate ◽  
Thermal Efficiency ◽  
Solar Collector ◽  
Flow Model ◽  
Flow Distribution ◽  
Isothermal Flow ◽  
One Dimensional ◽  
Dimensional Flow ◽  
Uniform Flow Distribution ◽  
Flat Plate Solar Collector

An isothermal one-dimensional flow model is used to calculate the flow distribution across the manifold of a flat plate solar collector in order to quantify the effect of a non-uniform flow distribution on the thermal efficiency for a variety of manifold geometries. The predictions of this flow model are found to compare favourably with measured isothermal flow distributions.

Optimal Supersonic Ejector Designs

1986 ◽  
Vol 108 (4) ◽  
pp. 414-420 ◽  
Author(s):  
J. C. Dutton ◽  
B. F. Carroll
Keyword(s):  
Flow Model ◽  
Optimization Problems ◽  
Pressure Ratio ◽  
Area Ratio ◽  
Stagnation Temperature ◽  
Entrainment Ratio ◽  
One Dimensional ◽  
Supersonic Ejector ◽  
Constant Area ◽  
The Common

A technique based on a one-dimensional constant area flow model has been developed for solving a large class of supersonic ejector optimization problems. In particular, the method determines the primary nozzle Mach number and ejector area ratio which optimizes either the entrainment ratio, compression ratio, or stagnation pressure ratio given values for the other two variables and the primary and secondary gas properties and stagnation temperatures. Design curves for the common case of diatomic primary and secondary gases of equal molecular weight and stagnation temperature are also presented and discussed.

Sign in / Sign up

Export Citation Format

Share Document