http://dspace.mist.ac.bd:8080/xmlui/handle/123456789/161 Volume 2, Number 1, (2013) Mon, 04 May 2026 12:14:06 GMT 2026-05-04T12:14:06Z http://localhost:8080/xmlui/bitstream/id/d1a6ebee-6fa0-4780-91fc-1d67f026fd47/ http://dspace.mist.ac.bd:8080/xmlui/handle/123456789/161 http://dspace.mist.ac.bd:8080/xmlui/handle/123456789/226 Hydrodynamic And Economical Analysis For The Performance Of Inland Ships In Bangladesh RASHIDUL HASAN, S. M. Shallow water affects the performance of the ship and decrease the efficiency from economic and hydrodynamic point of view. Operations in shallow water is different from open and deep water, sometimes very dangerous if the affects are not understood properly by the Naval Architects at design stage and Mariners during operation. In this paper an effort was made to analyze the effect of shallow water on Bangladeshi inland ship performance in the light of speed loss and increased fuel cost. As this increased fuel cost has the direct impact on the freight rate, effect was also analyzed and measured economically. Some suggestions are also made for the Naval Architects to overcome these losses at the initial design stage. Fri, 01 Feb 2013 00:00:00 GMT http://dspace.mist.ac.bd:8080/xmlui/handle/123456789/226 2013-02-01T00:00:00Z http://dspace.mist.ac.bd:8080/xmlui/handle/123456789/225 Design And Fabrication Of A Bench Mounted Closed Loop Wind Tunnel AbdusSalam, Gp. Capt.; Taher Ali, Dr. M. A.; AnwarulAziz, S. M.; Iqbal, Asif; MijanurRahman, Md.; Rahman, Istaqur A Bench-mountedclosed loop wind tunnel has been designed and fabricated to study the air flow characteristics and its effects on different models at different flow conditions. Thefabricated wind tunnel is sub-sonic nature with operating velocity from 0 to 18 m/s. The wind tunnel could be used to carry out research on different model for laminar and turbulent flow conditions .The wind tunnel is powered by two similar co-rotating axial flow fans and the air velocity could be varied by varying the fan speed. The wind tunnel consists of a test section, bell mouth nozzle, bends, guide vanes and fan section. An ATMega16 microcontroller based Data Acquisition Card (DAQ)has been incorporatedhere to measurepressure through pressure sensors. Steady state flow condition could be attained from the wind tunnel within short period of time to easily explain the flow parameterswhile carrying out the experiments. Fri, 01 Feb 2013 00:00:00 GMT http://dspace.mist.ac.bd:8080/xmlui/handle/123456789/225 2013-02-01T00:00:00Z http://dspace.mist.ac.bd:8080/xmlui/handle/123456789/224 Role Of Chevrons In Engine Noise Control Abdus Salam, Gp.Capt. (BAF); NC Chattopadhyay, Gp.Capt. (IAF); Tasnim, Nazifa; Bin Hossain, Asif Aircraft noise has been an issue of enormous environmental, financial, and technological impact. FAA statistics has forecast that aviation is likely to grow over the next 20 years at an average rate of 3.8% per year [1] for which the use of jet engines as the prime power plant is inescapable. Most commercial aircrafts are equipped with turbofan engines due to their capability of providing higher performance and lower noise when compared with turbojet engines. Dominant noise sources of turbofan engines are from the fan (including the stator) and the exhaust (also referred to as the jet).The noise produced in these two areas during takeoff and landing has a profound impact on the communities surrounding the airports. As a result, aircraft noise has been the target of strict FAA regulations, making turbofan engine noise suppression became the subject of intensive research and development. One of the significant sources of aircraft noise in modern jet aircraft is the turbulence generated in the shear layers around the engine’s exhaust. A number of flow control approaches have been applied to modify the flow structures in the shear layer and the radiated sound. One of the simplest and widely accepted approaches is the application of chevrons to the trailing edge of the nozzles. The purpose of this paper is to focus on the development, features & techniques of sound suppression of chevrons nozzles. Fri, 01 Feb 2013 00:00:00 GMT http://dspace.mist.ac.bd:8080/xmlui/handle/123456789/224 2013-02-01T00:00:00Z http://dspace.mist.ac.bd:8080/xmlui/handle/123456789/223 A Review On Wing Morphing NC Chattopadyay, Gp Capt.(IAF); Jony, Bodiuzzaman; Acharya, Anup Since the inception of the first flight by Wright brothers, the aerodynamicist had been focusing on improvement of aircraft performance through suitable alteration of design parameters. Most promising geometrical parameter of the aircraft was to be the wing itself. Designers and researchers conducted large number of experiments with different varieties of aspect ratio and concluded that changing the shape of the wing during actual flight can tremendously improve aircraft performance. This technique is analogous to shape change of wings of natural flyers. This had been the genesis of shape forming or conveniently “shape morphing”. Hence, shape morphing, in general, involves the change of shape of wings during flight to adapt a particular type of mission. Thus, an aircraft with a morphed wing is capable to undertake multiple missions and multiple maneuvers with combat agility, improved fuel efficiency and reduced drag. Since the wing defines the primary shape of the aircraft, an aircraft with morphed wings is conveniently renamed as a smart structure. While, the dynamic loads are fully accounted, careful considerations of the power requirement for wing planform variation will enable the smart technology as a future aviation for high performance aerial vehicles. The present paper focuses on various aspects of shape morphing and scope of future developments. Fri, 01 Feb 2013 00:00:00 GMT http://dspace.mist.ac.bd:8080/xmlui/handle/123456789/223 2013-02-01T00:00:00Z