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This paper exposes a simplified preliminary conceptual integrated method to design an aircraft wing in subsonic speeds up to Mach 0.85. The proposed approach is integrated, as it allows an early estimation of main aircraft aerodynamic features, namely the maximum lift-to-drag ratio and the total parasitic drag. First, the influence of the Lift and...
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Designing and selecting the material handling system is a vital factor for any production line, and as result for the whole manufacturing system. Poor design and unsuitable handling equipment may increase the risk of having bottlenecks, longer production time and as a result the higher total production cost. One of the useful and effective tools ar...
Citations
... In wing design, the taper ratio should be greater than 0.2 to avoid catastrophic failure (Badis 2017), and the structural optimization should also achieve a minimum-weight gust load at critical flight conditions. Statistical analysis of the response surface is used to determine the optimal joined-wing aircraft configurations (Davari et al. 2011;La Mantia and Dabnichki 2011;Ren et al. 2013). ...
This study investigated the impact of wing design on the performance of the Cessna 172-R aircraft, focusing on modifications to its wing geometry. The study proposes two alternate configurations: one with increasing the span length and retaining the existing chord length, and the other with increasing the chord length retaining the existing span length. Experimental and analytical studies were conducted to evaluate the performance of these two configurations. The study found that the modified wingspan configuration significantly enhanced the aircraft’s performance, with an increase in lift coefficient, range, and endurance by 13.2%, 26.15%, and 29.26%, respectively. Additionally, the drag coefficient was decreased by 8.12%, indicating the potential for reduced fuel consumption and operational costs. In contrast, the modified wing chord configuration did not improve the performance output. These findings underscore the critical role of wing design in aircraft performance and highlight the potential for modifications to wing geometry to provide significant improvements in efficiency and operational cost. The results of this study indicate the scope for further research in this area, with efforts to optimize aircraft performance and reduce environmental impact.
The commercial transport jet designed in this report captures conceptual development and engineering details. The report delves into all the parameters and aspects of a commercial airliner including weight estimation and fuselage layout. The aircraft is carefully analyzed to be efficient, safe, and environmentally friendly.
Commercial and military interest in High Altitude Platform Station (HAPS) Systems issteadily growing. This involves a proliferation of technology that could increase electronic andcyber attacks on these systems and networks based on them. Through the study of a referencearchitecture of a HAPS System, this study presents an analysis of the cybersecurity of thesesystems through the attack tree method. The findings of this paper can be used to characterizefuture cyber risks of commercial and military HAPS-based activities and raise awareness of thesecurity of these technologies.
Performance has always been an important consideration in the design of aircraft. Modifications in wing geometry of Cessna 172-R aircraft are considered for study by theoretical and experimental methods to evaluate the output performance. The modifications include changes in wingspan and wing chord with suitable considerations on aspect ratio and taper ratio by applying NACA 2412 standard for the aerofoil. The first configuration has an increase in span length with no change in chord length, while the second has an increase in chord length with no change in span length and both consider trapezoidal planforms in place of the existing rectangular planform. Values of lift and drag coefficients, range and endurance are presented for the proposed wing configurations and for the existing rectangular wing. It is found that there is an increase in lift coefficient by 13.2, range by 26.15, and endurance by 29.26 for the modified wingspan configuration, whereas the drag coefficient has decreased by 8.12% compared to the results of the existing rectangular wing.KeywordsCessna 172-R aircraftModified wing chordWind tunnel testingLift coefficientsDrag coefficientsRange and endurance
