On Boeing 737 – 300 Wing Aerodynamics Calculations Based on VLM Theory

Jacob Nagler

Article ID: 812
Vol 1, Issue 1, 2018

VIEWS - 4703 (Abstract)

Abstract


In this paper, aerodynamics coefficients of Boeing 737 - 300 are calculated using VLM (vortex lattice method) theory. The wing was divided into panels of the size: 6X6. The wing was assumed to be planar and the panels are in the trapezoid shape. Aerodynamics lifting and moment coefficients were calculated. Also, center of pressure location was found using data from VLM and wing geometry. Comparisons between literature, finite wing theory and VLM theory were done. It was found that maximum lifting coefficient error between literature and VLM is about 4.0%. Moreover, the maximum lifting coefficient error between finite wing theory and VLM is about 2.2%. Center of pressure location error between finite wing theory and VLM is about 0.5%.


Keywords


VLM; Finite wing theory; Lifting coefficient; Moment coefficient; Center of pressure

Full Text:

PDF


References


Prandtl L (1923) Applications of modern hydrodynamics to aeronautics. NACA-TR-116, NASA Falkner VM (1943) The Calculations of Aerodynamic Loading on Surfaces of any Shape. R&M, British A.R.C Katz J, Plotkin A, (2001) Low-Speed Aerodynamics, 2nd Ed., Cambridge University Press, Cambridge Bertin JJ, Smith ML (1998) Aerodynamics for Engineers. 3rd Ed., Prentice Hall, New Jersey Anderson Jr JD (1991) Fundamentals of Aerodynamics. 2nd Ed., McGraw-Hill Inc Boeing Commercial Airplanes (2013) 737 - Airplane Characteristics for Airport Planning. D6-58325-6: 1–554 Spurk J, Aksel N (2008) Fluid Mechanics. 2nd Ed., Springer-Verlag, Berlin Küchemann D (1978) The Aerodynamic Design of Aircraft, Pergamon Press, Oxford Kuethe AM, Chow CY (1998) Foundations of Aerodynamics: Bases of Aerodynamic Design. 5th, Wiley & Sons Kuethe AM, Schetzer JD (1959) Foundations of aerodynamics. John Wiley & Sons, 2nd Ed., New York Pope A (1951) Basic wing and airfoil theory. McGraw-Hill, New York Wissinger J (1947) The lift distribution of swept back wings. NACA TM 1120

Refbacks

  • There are currently no refbacks.


Creative Commons License
This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.

Creative Commons License

This site is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.