---

Aims: Today, due to the advent of drug resistance in cancer cells against conventional drugs, attention has been paid to the development of anti-cancer drugs with new mechanisms. Pardaxin is an amphipathic polypeptide neurotoxin.The aim of this study was to investigate the interaction of antimicrobial peptide pardaxin with DPPC (composed of 1, 2-dipalmitoyl-sn-glycero-3-phosphocholine) bilayers by molecular dynamics simulation.
Materials & Methods: In the present study, simulations for different membrane environments were designed under neutral pH conditions. At first, the Linux system was used to install the VMD 1.8.6 (Visual Molecular Dynamics) software; then, Gromacs 4.5.5 software was used to perform all the simulations. The pdb peptide structure (1XC0) was prepared from the Protein Data Bank and DPPC lipid bilayer was used for lipid-peptide simulation.
Findings: During the 500 nanoseconds of simulation, the peptide was infiltrated into the membrane. In the DPPC system, at first, the number of hydrogen bonds between the peptide and the lipid bilayer were increased and, then, remained almost constant until the end of the simulation and decreased over time with the number of hydrogen bonds between peptides and water. Pardaxin contacted with the membrane surface and entered into the membrane. In the presence of the peptide, the thickness of the membrane and the range of each lipid decreased and the membrane penetration increased.
Conclusion: The mechanism of Pardaxin is dependent on the bilayer composition, so that the pardaxin peptide contacts with DPPC lipid membrane surface and enters into it.

---

Derivation of temperature distribution, at the different sections of nose, to select the material, component, and sensitive system installation at inside of it, implicates to specifying the induced aeroheating to the nose surface. This parameter with surface temperature and recess due to surface ablation must be corrected at next time steps of flight trajectory. The different methods, to estimate or calculation of aeroheating, were created whereas the most accurate method for this purpose is numerical solution of fully navier stocks, chemical dissociation and ionization of air, mass conservation of species, turbulence modeling, combustion modeling due to surface ablation, nose heat transfer equations with time marching finite volume algorithms simultaneously. Utilizing these solvers for flight trajectory is snail, and it’s required the high computational memory. Therefore, the finite difference method is used, and the governing equations are translated to curvature coordinate by mapping terms. By using this translation, to solve the governing equations, the space marching solvers can be used. Therefore, in this research, the more accurate estimation of temperature distribution for 3-D nose of supersonic and hypersonic vehicles was presented by using the numerical space marching solvers such as viscous shock layers and viscous boundary layer methods. Therefore, the comprehensive code was created to this purpose. The results of this code were validated by using the temperature telemetry results of flight tests. The relative error of the results was less than 10 percent.

---

The purpose of this study is to investigate the effect of the simultaneous use of fuel injection injectors in an air cross flow. Nowadays, several methods are proposed for optimizing fuel injection in internal combustion engines. These optimizations are due to the high impact of this variable on engine performance and reduction of emissions. The method proposed in this study is to use two fuel injectors instead of a single injector in the air inlet manifold. The uses of two injectors in order to impingement two fuel sprays and increase the turbulent and collision of droplets, and so break them up faster. Also, the use of two injectors can provide more control over spatial and temporal distribution. Simulations are performed numerically using the generalized Kiva code. These simulations are similar to the fuel injection conditions in the manifold of the spark ignition internal combustion engine. The results indicate that the placement of two injectors in a longitudinal distance, the installation of two injectors at a 70 ° angle with the duct, placing two injectors in 180° or 90° relative angles and a 15° conical angle reduces the average diameter of the droplets. The results of this study can be used to design an internal combustion engine fuel injection system.