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This study was carried out in Igdir, where Turkey’s urban air pollution is at the highest level, and the population is among the smallest. Thus, the study aims to determine the effect of air transportation on air pollution in the most polluted city in Turkey.

The approach includes six stages: choosing the airport, accessing the flight information for the airport, classifying the aircraft that operated at the airport, determining the aircraft engines, calculating the emission amounts, calculating the landing and takeoff-based emissions.

Rather than devoting the resources disproportionally to the aviation sector within the scope of economic globalization, as a policy recommendation, to realize its production potential, Igdir, which has a great agricultural production capacity, considering its microclimate, fertile soil and arable land, should be urgently integrated into neighboring markets and the national market via railways.

It is inferred from the research that Turkey has to consider implementing the emissions tax policy, while the Turkish aviation sector is to realize new regulations for aircraft-engine matching to take public health and the impacts of the airports on their surroundings into consideration more seriously.

This study is an original one, as it puts the increasing pollution caused by the aircraft into a historical and political-economic perspective. Also, it is an example of an interdisciplinary work that combines environmental science and political science.

This paper aims to investigate the environmental impact of various pollutant emissions including carbon monoxide (CO), carbon dioxide (CO₂), nitrogen oxide (NO_x) and hydrocarbon (HC) from aircraft exhaust gases during the landing and take-off (LTO) cycles at Eskisehir Hasan Polatkan Airport, Turkey, between 2017 and 2018.

The methodology approach used to calculate the emissions from aircrafts is based on the ICAO databank and the actual data records taken from Presidency of The Republic of Turkey Directorate of Communications (DoC).

The maximum amount of total fuel burnt during the two years is 80.898 and 70.168 tons in 2017 and 2018, respectively, while the average fuel burnt per year from 2017 to 2018 is approximately 369.773 tons. The highest CO, CO₂, NO_x and HC emissions are found to be 248.3 kg in 2017, 261.380 tons, 1.708 tons and 22.15 kg, during the 2018 year, respectively. Average CO, HC, NO_x and CO₂ emissions amount per year are observed to be 1.392 tons, 135 kg, 6.909 tons and 1,143 tons, respectively. Considering the average of total emission amount as an environmental factor, as expected, CO₂ emissions contributed the most to the total emissions while HC emissions contributed the least to the total emissions from the airport.

The study presents the approach in determining the amounts of emissions released into the interannual atmosphere and it explicitly provides researchers and policymakers how to follow emissions from commercial aircraft activities at different airports.

The value of the study lies in the transparent computation of the amounts of pollutants by providing the data directly from the first hand-DoC.

The current research conducts a comprehensive review on FishBAC (fishbone active camber morphing wing surfaces) for researchers and scientists and sheds light on challenges and opportunities of FishBAC development.

This is a review article and this study reviews previous research on FishBAC.

The current FishBAC applications could be upgraded into more efficient designs in materials, design and mechanisms with more perspectives involved. Then, this promising branch of morphing surface design could be integrated with rotor blades, unmanned aerial vehicle wings, general aviation aircraft surfaces and so on.

This is a review article.

The contributions of the study are summarized as follows: to provide an overview of FishBAC research; to compare various approaches and trends in FishBAC designs; to address the research gap in the roadmap for FishBAC design; and to discuss the challenges and opportunities of FishBAC development.

To the best of the authors’ knowledge, this is the first review on a promising morphing method and an alternative for conventional flaps and ailerons.

This study aims to introduce exergy analysis of a three-spool turboprop engine during the complete flight.

In this study, a flight scenario of the aircraft is assumed. Operating parameters of the aircraft and its engine are modelled based on the assumed flight scenario with the aid of a genuine code. And then performance analysis of the engine is performed for each flight path point with the aid of exergy.

At the end of the study, major exergy parameters of the engine are calculated during the complete flight of a cargo aircraft three-spool turboprop engine.

Findings of the study may be beneficial for industry and practitioners to improve performance of the evaluated engine.

To the best of authors’ knowledge, this paper presented the exergy analysis of a three-spool turboprop engine during the complete flight for the first time. It was shown how the exergy destruction rate depends on the altitude and manoeuvre.

Lithium-polymer batteries have common usage in aviation industry especially unmanned aerial vehicles (UAV). Overheating is a serious problem in lithium-polymer batteries. Various cooling methods are performed to keep lithium-polymer batteries in the desired temperature range. The purpose of this paper is to examine pouch type lithium-polymer battery with plate fins by using particle image velocimetry (PIV) and computational fluid dynamics (CFD) for UAV.

Battery models were produced with a 3D printer. The upper surfaces of fabricated battery models were covered with plate fins with different fin heights and fin thicknesses. Velocities were obtained with PIV and CFD. Temperature dissipations were acquired with numerical simulations.

At the end of the study, the second battery model gave the lowest temperature values among the battery models. Temperature values of the seventh battery model were the highest temperatures. Fin cooling reduced the maximum cell temperatures noticeably. Numerical simulations agreed with PIV measurements well.

This paper takes into account two essential tools such as PIV and CFD, for fluid mechanics, which are significant in the aviation industry and engineering life.

The originality of this paper depends on investigation of both PIV and CFD for UAV and developing a cooling method that can be feasible for landing and take-off phases for UAV.

The purpose of this paper is to introduce an approach to evaluate the establishment requirements of an flight training organization (FTO) through indicators that are not included in the regulations from the viewpoint of “acquired indicators from FTO experience” (AIs-FTOE).

Although the establishment requirements of an FTO can be determined through regulations, it was realized that the pilot training process can be achieved in a safe, sustainable and economical manner through indicators that are not included in the regulations. These indicators were obtained through experience in the operation process of the FTOs. In this study, the indicators (obtained from the regulations and experiences) affecting the efficiency of FTOs, that were or would be operational, were determined, and the effects of the indicators on the organization were examined and presented in detail. The case study was carried out in the Department of Flight Training (ETU-P) of Eskişehir Technical University which has an FTO.

In accordance with the results, the necessity indicators were defined, and the indicators that were not included in the regulations were called as AIs-FTOE. Identified AIs-FTOEs were classified into three main headings: natural and artificial obstacles, meteorological conditions and physical and technological resources. Detailed indicator data results were presented after examinations.

When literature on FTOs was examined, it was seen that there is a need to identify and classify indicators that affect the efficiency of FTOs. To the authors’ knowledge, this study will be the first in the literature that presented information based on an active FTO in detail. Thus, the AIs-FTOEs identified in this study will serve as a roadmap for the FTOs to be established and are to be used as parameters to evaluate efficiency for the established ones.

To the best of authors’ knowledge, this paper will be the first paper in the literature describing the indicators that can be evaluated in terms of efficiency, sustainability and economy of FTOs.

This paper aims to investigate the cycle performance of a small size turbojet engine used in unmanned aerial vehicles at 0–5,000 m altitude and 0–0.8 Mach flight speeds with real component maps.

The engine performance calculations were performed for both on-design and off-design conditions through an in-house code generated for simulating the performance of turbojet engines at different flight regimes. These calculations rely on input parameters in which fuel composition are obtained through laboratory elemental analysis.

Exemplarily, according to comparative results between in-house developed performance code and commercially available software, there is 0.25% of the difference in thrust value at on-design conditions.

Once the on-design performance parameters and fluid properties were determined, the off-design operation calculations were performed based on the compressor and turbine maps and scaling methodology. This method enables predicting component maps and fitting them to real conditions.

A method to be used easily by researchers on turbojet engine performance calculations which best fits to real conditions.

This study aims to ascertain the greenest helicopters by modeling joint parameters to make sense of induced emissions effects of helicopters allocated to various categories.

Emission indexes of helicopters construct the pillars of the methodology under use. Three different parameters are derived from emission indices: the index showing grams of pollutants that an engine produces per kWh; the index comparing of pollutant mass depending on the energy content of the fuel; and the index expressing the presence of the unreacted hydrocarbon (unburned) released into the atmosphere as a result of the combustion reaction.

Various helicopters have been designated as sensitive and insensitive to the environment under various conditions and in different categories. Details are in the conclusions section.

This study includes methods that can be used to select environmentally sensitive helicopters of various categories according to specific pollutants and their combustion efficiency.

The originality of the work lies in the determination of the most sensitive and insensitive to the environment by using true flight data of helicopters operating in various categories during different flight phases. In addition, this paper with an approach to identifying green helicopters has the capability to support studies on regulations for helicopters in some countries by policymakers.

Determining the performance parameters of the propulsion systems of the aircraft, which is the key product of the aviation industry, plays a critical role in reducing adverse environmental impacts. Therefore, the purpose of this paper is to present a temperature performance template for turbojet engines at the design stage using a neural network model that defines the relationship between the performance parameters obtained from ground tests of a turbojet engine used in unmanned aerial vehicles (UAV).

The main parameters of the flow passing through the engine of the UAV propulsion system, where ground tests were performed, were obtained through the data acquisition system and injected into a neural network model created. Fifteen sensors were mounted on the engine – six temperature sensors, six pressure sensors, two flow meters and one load cell were connected to the data acquisition system to make sense of this physical environment. Subsequently, the artificial neural network (ANN) model as a complement to the approach was used. Thus, the predicted model relationship with the experimental data was created.

Fuel flow and thrust parameters were estimated using these components as inputs in the feed-forward neural network. In the network experiments to estimate fuel flow parameter, r-square and mean absolute error were calculated as 0.994 and 0.02, respectively. Similarly, for thrust parameter, these metrics were calculated as 0.994 and 1.42, respectively. In addition, the correlation between fuel flow, thrust parameters and each input parameters was examined. According to this, air compressor inlet (AC_inlet,temp) and outlet (AC_outlet,temp) temperatures and combustion chamber (CC_inlet,temp, CC_outlet,temp) temperature parameters were determined to affect the output the most. The proposed ANN model is applicable to any turbojet engines to model its behavior.

Today, deep neural networks are the driving force of artificial intelligence studies. In this study, the behavior of a UAV is modeled with neural networks. Neural networks are used here as a regressor. A neural network model has been developed that predicts fuel flow and thrust parameters using the real parameters of a UAV turbojet engine. As a result, satisfactory findings were obtained. In this regard, fuel flow and thrust values of any turbojet engine can be estimated using the neural network hyperparameters proposed in this study. Python codes of the study can be accessed from https://github.com/tekinonlayn/turbojet.

The originality of the study is that it reports the relationships between turbojet engine performance parameters obtained from ground tests using the neural network application with open source Python code. Thus, small-scale unmanned aerial propulsion system provides designers with a template showing the relationship between engine performance parameters.