Sergiu P Iliev | Imperial College London (original) (raw)
Papers by Sergiu P Iliev
Journal of Space Weather and Space Climate, 2015
Materials Science and Engineering A-structural Materials Properties Microstructure and Processing, Aug 1, 2018
HAL (Le Centre pour la Communication Scientifique Directe), Nov 1, 2013
This paper forms part of the 'Everplane' Group Design Project and aims to present... more This paper forms part of the 'Everplane' Group Design Project and aims to present the Vehicle Definition of an autonomous high-altitude long-endurance concept aircraft, designed for flying continuously over one month in an environmentally sustainable manner. The platform has the capability of acting as an aerosattelite, providing affordable internet to remote areas. Note that this report is part of a group of 20 approaching this design challenge from different perspectives. The focus points of this particular report are: initial and final aircraft configuration design; accurate mass and centre of gravity determination; computer-aided design for technical (CFD, FEA, Drawings) and media (rendering) purposes. The results, consistent with previous studies, indicate that an optimum configuration is a conventional one, featuring a high aspect ratio wing, a cruciform tail, 4 electric engines powered by H2 fuel cells, recharged by a large solar panel array. Furthermore, the total mass for the most recent aircraft iteration was determined as 539.65kg, within the flight allowance of 559kg. Finally, the concept was determined to be technically feasible from the perspective of all teams involved.
Materials Science and Engineering: A, 2017
Journal of Space Weather and Space Climate, 2015
The experiment was performed in the Donald Campbell Wind Tunnel Laboratory on the 26 th of Februa... more The experiment was performed in the Donald Campbell Wind Tunnel Laboratory on the 26 th of February, under the supervision of Mr Ben Clapperton with the objective of determining the lift and drag coefficients of a Cessna 172 airplane at various angles of attack (AOA) and two air speeds. After the analysis of data gathered from the test, the Reynolds numbers have been determined and various plots have been created to show the evolution of lift and drag with change of AOA. The effects of induced drag have been observed visually and found numerically, also the stall speed of the real plane has been estimated. Following a comparison with the actual value of 26m/s (Lab Handout, 2012) the impact of wind tunnel blockage effects could be observed.
The experiment was performed in the Strain Measurement laboratory on the 12th of November, under ... more The experiment was performed in the Strain Measurement laboratory on the 12th of November, under the supervision of Mr Yuefeng Cui with the objective of determining the Young modulus and Poisson Ration of a sample of steel material using resistance strain gauges at room temperature. After the analysis of raw data gathered from the test, the average values of the two parameters sought have been calculated. After subjecting them to a comparison with previous experimental determinations (Luecke, et al., 2006, pp. 46-47), (Toolbox, 2012) and (Toolbox, 2012) it is reasonable to state that the values obtained are feasible and a good approximation of the real material properties.
We have designed a concept airplane in order to analyze the feasibility of passenger flight can b... more We have designed a concept airplane in order to analyze the feasibility of passenger flight can be an ecological, no-emissions, means of travelling. Using relevant facts as well as combining conventional technology with well-researched concepts we hope to achieve realistic design, as far as our knowledge in high school can reach, that can be analyzed further by specialists. The project is based on our original idea and the information provided justifies our choices.
Following the wind tunnel testing of a swept uniformly tapered half wing with straight edges at a... more Following the wind tunnel testing of a swept uniformly tapered half wing with straight edges at an average Re number of 5E+05 and at 6 angles of attack (0, 4, 6, 9, 11, 15), pressure distribution data for three sections was obtained. This paper assesses the reliability of the inviscid computational ‘panel method’ and thin aerofoil theory in predicting wing performance, though comparison with experimental data. Both the validity of the data and its interpretation were confirmed, upon comparison with similar papers. Uncertainties were accounted for. Furthermore, the report presents the advantages, limitations and importance of inviscid methods in swept-back wing design and analyses the stalling behavior of the wing.
Our team has analyzed the possible purpose of our colony ship in the future, by thinking of plaus... more Our team has analyzed the possible purpose of our colony ship in the future, by thinking of plausible futuristic scenarios. We designed our project for a relevant and clear representation of the colony and the life an inhabitant would have aboard it. By combining 3D graphics with scientific concepts we hoped to create a clear depiction of all issues that make up the station, from its creation to the social structure and they way it is sustained by life support systems. At the end of each chapter we imagined scenario in a short narration to illustrate how the proposed design affects inhabitants.
Matlab Implementation of the following: Finite Order Approximation Heat equation solution Integra... more Matlab Implementation of the following: Finite Order Approximation Heat equation solution Integration Method Mid-Point Rule vs. Gauss-Legendre Rule Trapezium Rule vs. Gauss-Legendre Rule Number Storage Bisection Method Newton-Raphson Method Secant Method
Materials Science and Engineering: A
Journal of Space Weather and Space Climate, 2015
Materials Science and Engineering A-structural Materials Properties Microstructure and Processing, Aug 1, 2018
HAL (Le Centre pour la Communication Scientifique Directe), Nov 1, 2013
This paper forms part of the 'Everplane' Group Design Project and aims to present... more This paper forms part of the 'Everplane' Group Design Project and aims to present the Vehicle Definition of an autonomous high-altitude long-endurance concept aircraft, designed for flying continuously over one month in an environmentally sustainable manner. The platform has the capability of acting as an aerosattelite, providing affordable internet to remote areas. Note that this report is part of a group of 20 approaching this design challenge from different perspectives. The focus points of this particular report are: initial and final aircraft configuration design; accurate mass and centre of gravity determination; computer-aided design for technical (CFD, FEA, Drawings) and media (rendering) purposes. The results, consistent with previous studies, indicate that an optimum configuration is a conventional one, featuring a high aspect ratio wing, a cruciform tail, 4 electric engines powered by H2 fuel cells, recharged by a large solar panel array. Furthermore, the total mass for the most recent aircraft iteration was determined as 539.65kg, within the flight allowance of 559kg. Finally, the concept was determined to be technically feasible from the perspective of all teams involved.
Materials Science and Engineering: A, 2017
Journal of Space Weather and Space Climate, 2015
The experiment was performed in the Donald Campbell Wind Tunnel Laboratory on the 26 th of Februa... more The experiment was performed in the Donald Campbell Wind Tunnel Laboratory on the 26 th of February, under the supervision of Mr Ben Clapperton with the objective of determining the lift and drag coefficients of a Cessna 172 airplane at various angles of attack (AOA) and two air speeds. After the analysis of data gathered from the test, the Reynolds numbers have been determined and various plots have been created to show the evolution of lift and drag with change of AOA. The effects of induced drag have been observed visually and found numerically, also the stall speed of the real plane has been estimated. Following a comparison with the actual value of 26m/s (Lab Handout, 2012) the impact of wind tunnel blockage effects could be observed.
The experiment was performed in the Strain Measurement laboratory on the 12th of November, under ... more The experiment was performed in the Strain Measurement laboratory on the 12th of November, under the supervision of Mr Yuefeng Cui with the objective of determining the Young modulus and Poisson Ration of a sample of steel material using resistance strain gauges at room temperature. After the analysis of raw data gathered from the test, the average values of the two parameters sought have been calculated. After subjecting them to a comparison with previous experimental determinations (Luecke, et al., 2006, pp. 46-47), (Toolbox, 2012) and (Toolbox, 2012) it is reasonable to state that the values obtained are feasible and a good approximation of the real material properties.
We have designed a concept airplane in order to analyze the feasibility of passenger flight can b... more We have designed a concept airplane in order to analyze the feasibility of passenger flight can be an ecological, no-emissions, means of travelling. Using relevant facts as well as combining conventional technology with well-researched concepts we hope to achieve realistic design, as far as our knowledge in high school can reach, that can be analyzed further by specialists. The project is based on our original idea and the information provided justifies our choices.
Following the wind tunnel testing of a swept uniformly tapered half wing with straight edges at a... more Following the wind tunnel testing of a swept uniformly tapered half wing with straight edges at an average Re number of 5E+05 and at 6 angles of attack (0, 4, 6, 9, 11, 15), pressure distribution data for three sections was obtained. This paper assesses the reliability of the inviscid computational ‘panel method’ and thin aerofoil theory in predicting wing performance, though comparison with experimental data. Both the validity of the data and its interpretation were confirmed, upon comparison with similar papers. Uncertainties were accounted for. Furthermore, the report presents the advantages, limitations and importance of inviscid methods in swept-back wing design and analyses the stalling behavior of the wing.
Our team has analyzed the possible purpose of our colony ship in the future, by thinking of plaus... more Our team has analyzed the possible purpose of our colony ship in the future, by thinking of plausible futuristic scenarios. We designed our project for a relevant and clear representation of the colony and the life an inhabitant would have aboard it. By combining 3D graphics with scientific concepts we hoped to create a clear depiction of all issues that make up the station, from its creation to the social structure and they way it is sustained by life support systems. At the end of each chapter we imagined scenario in a short narration to illustrate how the proposed design affects inhabitants.
Matlab Implementation of the following: Finite Order Approximation Heat equation solution Integra... more Matlab Implementation of the following: Finite Order Approximation Heat equation solution Integration Method Mid-Point Rule vs. Gauss-Legendre Rule Trapezium Rule vs. Gauss-Legendre Rule Number Storage Bisection Method Newton-Raphson Method Secant Method
Materials Science and Engineering: A