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

Jacob Nagler

Article ID: 812
Vol 1, Issue 1, 2018

VIEWS - 217 (Abstract) 7 (PDF)

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

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References


1. Prandtl L (1923) Applications of modern hydrodynamics to aeronautics. NACA-TR-116, NASA

2. Falkner VM (1943) The Calculations of Aerodynamic Loading on Surfaces of any Shape. R&M, British A.R.C

3. Katz J, Plotkin A, (2001) Low-Speed Aerodynamics, 2nd Ed., Cambridge University Press, Cambridge

4. Bertin JJ, Smith ML (1998) Aerodynamics for Engineers. 3rd Ed., Prentice Hall, New Jersey

5. Anderson Jr JD (1991) Fundamentals of Aerodynamics. 2nd Ed., McGraw-Hill Inc

6. Boeing Commercial Airplanes (2013) 737 - Airplane Characteristics for Airport Planning. D6-58325-6: 1–554

7. Spurk J, Aksel N (2008) Fluid Mechanics. 2nd Ed., Springer-Verlag, Berlin

8. Küchemann D (1978) The Aerodynamic Design of Aircraft, Pergamon Press, Oxford

9. Kuethe AM, Chow CY (1998) Foundations of Aerodynamics: Bases of Aerodynamic Design. 5th, Wiley & Sons

10. Kuethe AM, Schetzer JD (1959) Foundations of aerodynamics. John Wiley & Sons, 2nd Ed., New York

11. Pope A (1951) Basic wing and airfoil theory. McGraw-Hill, New York

12. Wissinger J (1947) The lift distribution of swept back wings. NACA TM 1120


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