The lift distribution and the lift curve slope for wing/body combinations

Blair, Brian M (1962) The lift distribution and the lift curve slope for wing/body combinations. MSc(R) thesis, University of Glasgow.

Abstract

An examination is made in this paper of a number of methods for calculating the spanwise load distribution on wing/body combinations. From the load distribution, values are then obtained for the lift curve slope. The most versatile method for solving this problem appears to be that proposed by Multhopp, and it is here described in detail, together with various extensions suggested by Weber, Kirby, and Kettle. This method is not very accurate for wings of aspect ratio of 2 or less, but it is very satisfactory for higher values of aspect ratio. A DEUCE programme has been written to calculate the load distribution over the span using this method, and the calculation has been carried out for a large number of wings and wing/body combinations in which the aspect ratio, taper ratio, angle of sweep-back, and body size are the variables. From the load distributions so obtained, values of the lift curve slope were calculated and are shown in graphical form. To show the actual effect of the body, the ratio was calculated for each case and these values are also shown in graphs. An attempt is then made to give some physical reasons for this body effect. A short series of experimental tests was also carried out in a low speed wind tunnel on a number of rectangular wing/alone and wing/body models, and the lift curve slope was obtained for each case. These results, when given in the form are found to be in good agreement with the predicted values.

• Item Type: Thesis (MSc(R))
• Qualification Level: Masters
• Keywords: Aerospace engineering
• Date of Award: 1962
• Depositing User: Enlighten Team
• Unique ID: glathesis:1962-73312
• Copyright: Copyright of this thesis is held by the author.
• Date Deposited: 14 Jun 2019 08:56
• Last Modified: 14 Jun 2019 08:56
• URI: https://theses.gla.ac.uk/id/eprint/73312