Distribution of aerodynamic loading along wing span

Summarizing pressure distribution chordwise, we receive . At the analysis of influence of wing geometrical parameters in planform for distribution of aerodynamic loading spanwise it is convenient to use relative value . The function depends on , , and geometrical twist (refer to Fig. 3.5). Let's consider a flat wing. The influence of , , is shown on the following diagrams (Figs. 4.21, 4.22, 4.23).

Loading is distributed spanwise more regular with increasing of aspect ratio . At and for an elliptical wing . Refer to fig. 4.21.

The increasing of sweep angle causes growth of loading in a tip part and reduction in root cross-section for a swept-back wing (). Refer to fig. 4.22.

The influence of wing taper is similar to sweep effect: there is loading growth in wing tip cross-sections with taper increasing. Refer to fig. 4.23.

Distribution of lift along wing span:

Fig. 4.21. Depending on aspect ratio at condition of ,

Fig. 4.22. Depending on sweep at condition of ,

Fig. 4.23. Depending on taper at condition of ,

It is possible to write down for an one-profile flat high-aspect-ratio wing approximately:

; ,

Where , , the values of parameter are undertaken from the reference book or calculated.

Chord are distributed spanwise for a tapered wing with straight-line edges as follows: .

Approximately , , .

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