AVIA - International Journal of Aviation Science and Engineering
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An Experimental Analysis on the Effects of Stagger on the Aerodynamic Forces of Tandem Wings
Get PDFThis study is inspired by the flapping motion of natural flyers: insects. Many insects have two pairs of wings referred as tandem wings. Literature review indicates that the effects of tandem wing are influenced by parameters such as stagger (the stream-wise distance between the aerodynamic center of the front and the rear airfoil), angle-of-attack and flow velocity. As a first stage, this study focuses on the effects of stagger (St) on the aerodynamic performance of tandem wings. A recent numerical study of stagger on tandem airfoils in turbulent flow (Re = 6000000) concluded that a larger stagger resulted in a decrease in lift force, and an increase in drag force. However, for laminar flow (Re = 2000), increasing the stagger was not found to be detrimental for aerodynamic performance. Another work also revealed that the maximum lift coefficient for a tandem configuration decreased with increasing stagger. The focus of this study is to perform an experimental analysis of tandem two-dimensional (2D) NACA 0012 airfoils. The two airfoils are set at the same angle-of-attack of 0° to 15° with 5° interval and three variations of stagger: 1c, 1.5c and 2c. The experiments are conducted using an open-loop-subsonic wind tunnel at a Reynolds number of 170000. The effects of St on the aerodynamic forces (lift and drag) are analyze
The Development of a Model for Complaint Delivery on Aviation Industry in Indonesia Based on SMS Gateway to Promote Flight Safety
Get PDFThe variety of complaints appearing on Aviation Industry in Indonesia actually indicates the existence of problems on aviation system in Indonesia. The number of complaints may serve as an early detection in a system before the occurrence of an accident in a flight. Increasing numbers of flight service users in Indonesia had not been supported with an adequate complaint delivery, whether it is for internal complaints or external ones. One of available solutions is to detect whether all system components on Aviation Industry in Indonesia is good or not. In an effort to enhance system performance, a model for integrated complaint delivery is developed on Aviation Industry based on SMS Gateway in Indonesia. The model is expected to become a data bank on Aviation Industry to ease controlling, evaluating and improving condition performance on flight systems. This research used comparative and descriptive methods. It also results in applied product hence it is expected that the output can be used to complement the current product/program operated by Directorate General of Civil Aviation (DGCA). The development of a model for complaint delivery is conducted to make cellular phone numbers inputs for all stakeholders on aviation industry. This strategy activates all stakeholders to provide information regarding the current conditions for all subsystems in flight system in Indonesi
On Developing the Noise Reduction Model for Indonesian Aviation
Get PDFAircraft noise exposure is still one of many abandoned pollution problems in Indonesia. The effects on human life have been studied more thoroughly in Europe and other regions. We review how some efforts have been implemented and how others must be further developed to support an integrated solution. Following several studies on noise exposure effects in Indonesia, future research must take part in reducing these effects. Indonesian research on noise reduction should follow the track of international research to develop sustainability and protect human capital. This paper reports the developing work aims for building a noise reduction model in the field of Indonesian aviatio
Design of Single Stage Axial Turbine for Mini Turbojet Engine
Get PDFThis paper explains about aerodynamic design of a single stage gas generator turbine for a small turbojet engine. The design requirement is that the turbine must be able to deliver power output of 150 kW at 0.814 kg/s gas mass flow, with turbine inlet temperature of 1200 K, and turbine inlet pressure of 267508 Pa. The design phase consists of 4 steps, which is thermodynamic property analysis using parametric cycle analysis, determination of velocity triangle in 2D plane and 2D blade design using CASCADE software, 3D geometry modeling, and 3D flow analysis at design point using Computational Fluid Dynamics method. In parametric cycle analysis, design points are applied to get the unknown thermodynamics property. The determination of velocity triangles, two conditions are applied: zero inlet swirl and constant nozzle angle design. The design continues with the 2D approach in CASCADE to determine the airfoil type at the hub, mean, and the tip of the blade based on the inlet and outlet flow conditions. The 3D approach flow analysis is done by simulating the 3D geometry that has been made using CAD in full configuration to evaluate the overall performance of the turbine, especially the power generated by the turbine. The observed parameters are clearance, stagger angle, and cambered flat plate substitution in NGV affects the turbine’s output power. The analysis results show that all of those parameters above affect the turbine’s output power in a different way from one to each other. The bigger the clearance, the power output and the efficiency that is generated by the turbine also become bigger. Same as clearance, the stagger angle of turbine’s NGV also affects the turbine power and efficiency. The bigger the stagger angle, the bigger the power, but the efficiency drops
On Hypothesis of the Existence of Superfine Fluid that Producing Electromagnetic Field
Get PDFBased on previous work of reformulation of equation for compressible fluid flow by analogy with Maxwell equation, further effort is successfully done to show similarity between governing equations for continuum, incompressible, non-viscous fluid flow and Maxwell equation for homogeneous medium without electric charge and without magnetic pole. From mathematical analysis of both system of equations, impulse vector in fluid field is equivalent with electric field in electromagnetic field, vorticity in fluid field is equivalent with magnetic fields in electromagnetic field, and speed of sound in fluid field is equivalent with speed of light in electromagnetic field. The success of finding the similarity leads to a hypothesis about the existence of a “superfine fluid” that forming background field in universe that having a characteristic similar with fluid field which is continuum, incompressible and invisci
Flight Profile Analysis: Finding Correlations using Scatter Plot Method and Evaluation of Scatter Plot
Get PDFThis paper analyzed flight profiles where parameters of the trajectory of the airplane were found to be correlated in some way. The Scatter Plot Method was used to find these correlations but somehow the degree of correlations was mixed. We proceeded by evaluating the usage of Scatter Plot where Scatter Plot seems to have a good prospec
A Probabilistic Modeling of the Demand and Supply for Rotable Aircraft Components (Case Study: Brake Assembly of Boeing 737-800)
Get PDFSpare parts control is an important factor in every airlines company. The unavailability of the spare parts may affect the airlines operationally, thus a delay and even a cancellation may happen. A common assumption used to calculate spare part requirements is that the demand is stochastic and the supply is constant. But in real operational circumstance, both of those are stochastic. This research develops the spare parts demand and supply model, and the calculation method of service level and safety stock in the bi-variate distribution from a real data of demand and supply of a rotable component. A fit test is conducted to determine the probability density function of the distribution. An analysis is then carried out after implementing the model in a case study. Historical data of brake assembly used in Boeing 737-800 New Generation is used in the case study. The result of this research are a model to determine demand and supply of aircraft spare part components, a method to calculate service level and safety stock for probabilistic model of demand and supply, and the amount of spare parts required for a brake assembly inventory syste
Study Travel Time in the Movement of Passengers and Baggage at the Arrival Station of Sultan Hasanuddin International Airport Makassar
Get PDFAirport provides facilities for services to aircraft, passengers, and goods. One of the activities at the airport is handling your luggage. At some particular time, especially in crowded flight, a passenger still faces delays in receiving baggage at the arrival terminal. The purpose of the research is to know the travel time difference and the factors that influence the travel timedifferences in the movement of passengers and baggage at the arrival terminal of Sultan Hasanuddin International Airport of Makassar. The type of research is a correlation study, using primary data in the form of data direct field measurements as well as secondary data from the monthly reports-MATSC Support Operations Division Aeronautical Information Service in theform of fixed flight schedules and Side Air Operations Division in the form of data movement apron. Processing the data is by using SPSS version 18:00 The findings is: the smallest time difference between the passenger and baggage occurs when using the bus, followed a garbarata and the greatest difference in time when walking, so that it can be concluded that the use of buses more effective in reducing delays in receiving the baggage at the arrival terminal of International Airport Sultan Hasanuddin of Makassa
Analysis of 6-Pulse and 12-Pulse in Conversion of the 115VAC/400Hz to 270 VDC for Application on Fighter
Get PDFThe development of aircraft secondary power technology is moving from mechanical power, pneumatic power and hydraulic power to electric power. The trend toward electric power is known as More Electric Aircraft (MEA). Modern military aircraft are designed using 270VDC for electric power system. Today, some military aircraft still use 115VAC/400Hz for their electrical power system. If this type of aircraft need provides 270VDC electrical power, then they require Multi-Pulse Transformer Rectifier Unit (TRU). The development of this type TRU has not been aimed to comply with aircraft military standards. This research investigates the variation of the number of pulses (p) and firing angle (α) to the amplitude ripple voltage, output voltage, and distortion factor in order to comply with the MIL-STD-704F standards. The multi-pulse transformer rectifier unit being analyzed consists of 6-Pulse and 12-Pulse. The research shows that the amplitude ripple voltage and distortion factor of the 6-Pulse TRU do not comply MIL-STD-704F. The amplitude ripple voltage and distortion factor of 12-Pulse comply MIL-STD-704F with firing angle (α) ≤4°.Keywords: Transformer Rectifier Unit, thyristor, ripple voltage, distortion factor, firing angl
A Simple Fight Decision Support System for BVR Air Combat Using Fuzzy Logic Algorithm
Get PDFBeyond Visual Range (BVR) air combat is a future trend of war tactic. In this situation, a fighter can attack the opponent before direct encounter. Its complexity arises due to the necessity to take into account the information of target’s maneuver, the specification of the missile, and the advantage of fighter position. In this paper, a simple BVR air combat system has been developed to give a fight strategy for pilot. Some important parameters are considered, such as the distance and the azimuth position of the target’s as well as the range and the energy of missile to reach the target. The information is processed to determine the fighter supremacy and the opponent’s threat factor. The result of the processing is used as an input of fuzzy logic algorithm to determine the optimal fighting strategy. The feasibility of the model and validity of the algorithm are verified by simulation under two typical situation