Shape Optimization of Blended-Wing-Body Configuration- An Experimental Approach
Nishanth P1, A Arokkiaswamy2, Anthony Alen3

1Nishnath P, Assistant Professor, Department of Aeronautical Engineering, East West College of Engineering, Bengaluru (Karnataka), India.
2Dr. Aarokkiaswamy, Professor, Department of Aeronautical Engineering, Dayananda Sagar College of Engineering, Bengaluru (Karnataka), India.
3Anthony Alen, Student, Department of Aeronautical Engineering, East West College of Engineering, Bengaluru (Karnataka), India.
Manuscript received on 23 May 2019 | Revised Manuscript received on 13 June 2019 | Manuscript Published on 27 June 2019 | PP: 241-246 | Volume-8 Issue-1C May 2019 | Retrieval Number: A10430581C19/2019©BEIESP
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Abstract: In the recent years alternative aircraft configurations, such as Blended – Wing- Body(BWB) aircraft, are being studied and researched with the intention to develop more effectual aircraft configurations, in particular for very large transport that are more efficient and environmental friendly. In addition to the removal of the tail for this specific kind of aircraft and the substantial decline in equivalent weight, drag force, and radar cross-section, the accessible space for mounting equipment inside the wing and the operational range have also been augmented. Regardless of all these stated advantages, instability is the negative outcome of removing the tail. Revising this imperfection requires designing a combination of control surfaces and reflexed wing sections and using complex computer control systems. Hence, the aerodynamic shape optimization of BWBs, along with the need to meet the design necessities, has encouraged numerous investigators to overwhelm its challenges. In this project an experimental approach was adopted to optimize the shape of a basic design of a BWB using an experimental approach. The flow simulation using wind tunnel was carried out for a basic model of BWB. Then the aerodynamic efficiency of the basic design was compared with a conventional aircraft B747 using the same experimental conditions. The three models such as the basic BWB, B747 and the 787 were compared in terms of their (CL)max, (CD)min and (L/D)max values. The results were presented with the BWB with 45% efficient shape when the above-mentioned parameters are compared.
Keywords: Blended Wing Body, Shape Optimization, Gradient-Less Optimization, Experimental Approach.
Scope of the Article: Aeronautical Engineering