PKE Sharquie MD, PDPAA Noaimi MD, DDV, FDSM Al-Ogaily MD, IOSR Journal of Dental and Medical Sciences (IOSR-JDMS), 2015

     In this paper, the class of meromorphic multivalent functions of the form by using fractional differ-integral operators is introduced. We get Coefficients estimates, radii of convexity and star likeness. Also closure theorems and distortion theorem for the class ,  is calculaed.

The important parameter used for determining the probable application of miscible displacement is the MMP (minimum miscibility pressure). In enhanced oil recovery, the injection of hydrocarbon gases can be a highly efficient method to improve the productivity of the well especially if miscibility developed through the displacement process. There are a lot of experiments for measuring the value of the miscibility pressure, but they are expensive and take a lot of time, so it's better to use the mathematical equations because of it inexpensive and fast. This study focused on calculating MMP required to inject hydrocarbon gases into two reservoirs namely Sadi and Tanomaa/ East Baghdad field. Modified Peng Robenson Equation of State was

Thi s study included the effect of chronic exposure of di fferent concentrations of Nan on the biology of fresh water zroDplonk ton species Moina 41.112' ( Cladcxe'ra The concentrations used for chronic exposure were 03, 0.75. 1 960 to investigate iI effects on the life cycle and la lables of this species after exposure period and the range of this exposure effects on the rate of expectation for further life, also the effect of salinity on reproduotive parameters was studied which included average of total number of eggs and young produced, volume clutch's (6.95. indiclutch for control group , 14.516 indi clutch for 0.596a ,3_65 ind./ clutch for (175 5(.. and 03 Ind} cruel] for 1960) and number of Clutch's (5.5 clutch/ female for control gr

The aerodynamic characteristics of general three-dimensional rectangular wings are considered using non-linear interaction between two-dimensional viscous-inviscid panel method and vortex ring method. The potential flow of a two-dimensional airfoil by the pioneering Hess & Smith method was used with viscous laminar, transition and turbulent boundary layer to solve flow about complex configuration of airfoils including stalling effect. Viterna method was used to extend the aerodynamic characteristics of the specified airfoil to high angles of attacks. A modified vortex ring method was used to find the circulation values along span wise direction of the wing and then interacted with sectional circulation obtained by Kutta-Joukowsky theorem of