Determination of a Two Variable Approximation Function with Application to the Fuel Combustion Charts
Journal Title: INCAS BULLETIN - Year 2017, Vol 9, Issue 3
Abstract
Following the demands of the design and performance analysis in case of liquid fuel propelled rocket engines, as well as the trajectory optimization, the development of efficient codes, which frequently need to call the Fuel Combustion Charts, became an important matter. This paper presents an efficient solution to the issue; the author has developed an original approach to determine the non-linear approximation function of two variables: the chamber pressure and the nozzle exit pressure ratio. The numerical algorithm based on this two variable approximation function is more efficient due to its simplicity, capability to providing numerical accuracy and prospects for an increased convergence rate of the optimization codes.
Authors and Affiliations
Irina-Carmen ANDREI
Keywords
Related Articles
- EP ID EP293938
- DOI 10.13111/2066-8201.2017.9.3.1
- Views 177
- Downloads 0
Influences of surface temperature on a low camber airfoil aerodynamic performances
The current note refers to the comparison between a NACA 2510 airfoil with adiabatic walls and the same airfoil with heated patches. Both suction and pressure sides were divided into two regions covering the leading edge...
Mechanical properties evaluation and model finite element analysis of cork and felt based nanofilled phenolic resin composites
The paper presents the development of numerical experiences using finite element commercial codes, based on experimental mechanical tests performed on ablative composite materials. The studied ablative materials were obt...
Boundary Vorticity Dynamics at Very Large Reynolds Numbers
During the last century, the theoretical investigations in the boundary vorticity dynamics were based on the concept of a fluid of small-constant viscosity, i.e. the Newtonian fluid, described by the non-slip condition a...
Magnetic field nanosensor based on Mn impurities
Nanosensors based on graphene nanoribbon, studied in the present work, could provide a special interest in (aero) space applications. More specifically, the paper proposes the construction of a nanosensor based on Mn (Ma...
Optimization of flapping-wing micro aircrafts based on the kinematic parameters using genetic algorithm method
In this paper the optimization of kinematics, which has great influence in performance of flapping foil propulsion, is investigated. The purpose of optimization is to design a flapping-wing micro aircraft with appropriat...