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Calculating the Wing Lift Distribution with the Diederich Method In Microsoft Excel

Abstract

Aim of this project is to provide the Diederich Method for calculating the lift distribution of a wing in a Microsoft Excel spreadsheet based on didactic considerations. The Diederich Method is described based on primary and secondary literature. Diagrams are digitized so that the method can run automatically. To optimize the lift distribution of the wing, the elliptical and triangular lift distribution as well as Mason's lift distribution are offered for comparison. A method for calculating the maximum lift coefficient of the wing is integrated into the Diederich Method. To do this, the maximum lift coefficients of the airfoils at the wing root and at the wing tip must be entered in the program. The calculation assumes a trapezoidal wing. Both wing sweep and linear wing twist can be taken into account. The aspect ratio must not assume values that are too small. Subsonic flow and unseparated flow are assumed. Since only the wing is described, all other influences such as from the fuselage or from the engines are not taken into account. The Excel workbook was created for teaching in aircraft preliminary design. At the moment, the Diederich Method is apparently nowhere offered as a spreadsheet. With this work, this gap can be closed.

Download Project Report: PDF TextSchnoor.pdf deutsch    Size:  2.8M
 
PERSISTENT IDENTIFIER:
URN: https://nbn-resolving.org/urn:nbn:de:gbv:18302-aero2021-03-30.017 (to reach this page)
DOI:https://doi.org/10.15488/11556
ARK:https://n2t.net/ark:/13960/s2dm83bk1d4
Associated research data:https://doi.org/10.7910/DVN/UK2SIV    (Excel File and User Guide)
 
Alternatively Read in English: TORENBEEK: Synthesis of Subsonic Airplane Design (PDF, 100 MB) E-4.2 (p.473) "Spawise Lift Distribution" and E-4.4 (p. 475) "Maximum Lift". Source: "Diederich Method" (NACA). english
 
Download User Guide: PDF User_Guide_Diederich_Method.pdf english    Size:  362K
 
Download Excel File: XLS Diederich_Method.xlsm english    Size:  764K

Major results / graphical abstract


LAST MODIFIED:  14 December 2021
AUTHOR:  Prof. Dr. Scholz
IMPRESSUM (PDF)

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home  Prof. Dr. Scholz
home  Aircraft Design and Systems Group (AERO)
home  Aeronautical Engineering
home  Department of Automotive and Aeronautical Engineering
home  Faculty of Engineering and Computer Science
home  Hamburg University of Applied Sciences