Volume 5, Issue 2 (9-2016)
Abstract
The effect of human chorionic gonadotropin (hCG) on the immune response, biochemical parameters and serum enzymes in adult male and female goldfish during breeding season was investigated. Mature male and female received an intramuscular injection of human chorionic gonadotropin (hCG) 1/ IU hCG g/ BW and the control group was injected with saline solution. Twelve and 24 hours after hCG injection, blood samples were taken from broodstock and immune parameters (IgM, IgG, C3, C4), biochemical and enzymes (glucose, uric acid, urea, cholesterol, total protein, triglycerides, calcium, creatinine, albumin, HDL, LDL, AST and ALT) were measured. There were no significant changes in IgM levels in females between 12 and 24 hours after hCG injection compared to the control group (P>0.05). However, IgM level in male showed a gradual decrease in comparison to control fish (P<0.05). On the other hand, the concentration of IgM and C4 complement decreased by passing time after hCG injection in both male and female (P<0.05). The C3 complement dramatically increased after hCG injection in both male and female (P<0.05). Injection of human chorionic gonadotropin caused a significant change in serum biochemical and enzyme in both male and female. The results showed that the hCG hormone even in a single dose within a short time after injection, strongly stimulate the immune system and changes physiological condition of adult male and female goldfish.
Mojtaba Dehghan Menshadi, Mehdi Eilbeigi, Mehrdad Bazaz Zadeh, Mohammad Ali Vaziry,
Volume 16, Issue 5 (7-2016)
Abstract
The aerodynamic coefficients characteristics over a lambda-shaped flying wing aircraft with 55°-30° leading edge sweep angles have been investigated in a closed circuit low speed wind tunnel. The experiments were conducted at tunnel velocity of 90 m/s, the angles of attack of -6 to 17 and the side-slip angles of -8 to 8 degrees. All forces and moments were measured using an external six-component force balance located below the wind tunnel. The wall corrections were also performed for all test conditions. To improve the aircraft longitudinal stability characteristics, a new model with an increased leading edge sweep angle of 2 degrees were also tested and compared with the original model. A “pitch-up” phenomenon identified to occur at a rather low angle of attack of α=7.7 degrees, although it occurred at the higher angle of attack of α=8.7 degrees for the increased swept angle model which means an increase in useable lift of the aircraft. Moreover, off-surface pressure measurement over the wing surface was conducted to examine the onset and development of the flow separation over the wing surface. The results showed that the flow separation started at the trailing edge crank location and extended to the other parts of the wing, especially the outer wing.
