Engineering & Technology

Engineering & Technology

Conceptual Design Code Validation and Optimization of Aircraft for Minimum Drag and Maximum Range

Pages: 8  ,  Volume: 20  ,  Issue: 1 , January   2019
Received: 16 Jan 2019  ,  Published: 22 January 2019
Views: 113  ,  Download: 54


# Author Name
1 Banyar Thein


This paper develops conceptual design code and validate with existing results of Single Seat Aerobatic aircraft (SSA) by the user requirements.  Special consideration is given to minimize total Drag, maximum Range for optimum conceptual design based on developed design code.


  • Conceptual Design; Validation; Range; Total Drag
  • References

    [1]        Daniel P. Raymer, “Aircraft Design: A Conceptual Approach.”

    [2]        Thomas C. Corke. Design of Aircraft. Prentice Hall, Pearson Education., Inc; Upper Saddle River. New Jersey 07458. p 109.

    [3]        Nguyen, N. V. (2011). Multidisciplinary configuration design optimization for advanced very light aircraft. The Korean Society for Aeronautical and Space Sciences, 18-23.

    [4]        Boone IV, T. R., & Striz, A. G. (2010). Optimization of aircraft configuration for minimum drag. In the proceedings of the 51st AIAA/ASME/ASCE/AHS/ ASC Structures, Structural Dynamics, and Materials Conference, Orlando,FL. doi:10.2514/6.2010-3000.

    [5]        Hamza Ashraf, Afreen Abbas, “Conceptual Design and Optimization of Supersonic Business Jet,” Student Research Paper Conference Vol-1, No-3, Aug 2014.