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Trailing edge
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<h2 id="extensions">Extensions</h2> <p>Other sharp-edged surfaces that are attached to the trailing edges of wings or control surfaces include: </p> <ul><li>On control surfaces:</li></ul> <ul><li><a href="/facts/Trim_tabs/9tKjhH9r">trim tabs</a></li> <li><a href="/facts/Servo_tab/xVUr5FSL">servo tabs</a></li> <li><a href="/facts/Servo_tab/xVUr5FSL">anti-servo tabs</a></li></ul> <ul><li>Other surfaces:</li></ul> <ul><li><a href="/facts/Flap_(aircraft)/NJEgNK66">flaps</a></li></ul> <p>Other equipment that may be attached to the trailing edges of wings include: </p> <ul><li><a href="/facts/Anti-shock_body/1FG0qrlK">anti-shock bodies</a></li> <li><a href="/facts/Static_wick/l7hxDUC7">static wicks</a></li></ul> <h2 id="trailing-edge-shape">Trailing edge shape</h2> <p>The trailing edge is where the upper and lower surfaces of a wing meet. The angle between the upper and lower surfaces at the trailing edge is called the <i>trailing edge angle</i>. If the trailing edge angle is zero it is described as a <a href="/facts/Cusp_(singularity)/QH3fEGry">cusped</a> trailing edge.<a class="footnote-ref" id="fnref:5" href="#fn:5"><sup>5</sup></a> </p><p>In two-dimensional flow around a uniform wing of infinite span, the slope of the <a href="/facts/Lift_coefficient/Xz0sjYv9">lift curve</a> is determined primarily by the <i>trailing edge angle</i>. The slope is greatest if the angle is zero; and decreases as the angle increases.<a class="footnote-ref" id="fnref:6" href="#fn:6"><sup>6</sup></a><a class="footnote-ref" id="fnref:7" href="#fn:7"><sup>7</sup></a> For a wing of finite span, the <a href="/facts/Aspect_ratio_(aeronautics)/9dFXqYAV">aspect ratio</a> of the wing also significantly influences the slope of the curve. As aspect ratio decreases, the slope also decreases.<a class="footnote-ref" id="fnref:8" href="#fn:8"><sup>8</sup></a> </p> <h2 id="references">References</h2> <ol> <li id="fn:1"><p>Crane, Dale: Dictionary of Aeronautical Terms, third edition, page 521. Aviation Supplies & Academics, 1997. ISBN 1-56027-287-2 <a href="/wiki/ISBN_(identifier)" target="_blank">/wiki/ISBN_(identifier)</a> <a href="#fnref:1" class="footnote-back-ref">↩</a></p></li> <li id="fn:2"><p>Wragg, David W. (1973). A Dictionary of Aviation (first ed.). Osprey. p. 262. ISBN 9780850451634. <a href="9780850451634" target="_blank">9780850451634</a> <a href="#fnref:2" class="footnote-back-ref">↩</a></p></li> <li id="fn:3"><p>“It has been known from the very beginning of flight that wings with a sharp trailing edge must be used in order to obtain a well-defined lift.” von Mises, Richard (1945), Theory of Flight, Section VIII.2, p.179, Dover Publications Inc. ISBN 0-486-60541-8 <a href="/wiki/Richard_von_Mises" target="_blank">/wiki/Richard_von_Mises</a> <a href="#fnref:3" class="footnote-back-ref">↩</a></p></li> <li id="fn:4"><p>Batchelor, G. K. (1967), An Introduction to Fluid Dynamics, p.438, Cambridge University Press. <a href="#fnref:4" class="footnote-back-ref">↩</a></p></li> <li id="fn:5"><p>Anderson, John D. (2017). Fundamentals of aerodynamics. United States: McGraw-Hill Education. pp. 332–333. ISBN 978-0-07-339810-5. <a href="978-0-07-339810-5" target="_blank">978-0-07-339810-5</a> <a href="#fnref:5" class="footnote-back-ref">↩</a></p></li> <li id="fn:6"><p>Lyons, D.J., and Bisgood, P.L., (Jan 1945). An analysis of the lift slope of aerofoils of small aspect ratio. Reports and Memoranda of the Aeronautical Research Council of Great Britain No 2308 <a href="#fnref:6" class="footnote-back-ref">↩</a></p></li> <li id="fn:7"><p>Abbott, I.H., and Von Doenhoff, A.E. (1949) Theory of Wing Sections, section 7.4(b) <a href="#fnref:7" class="footnote-back-ref">↩</a></p></li> <li id="fn:8"><p>Abbott, I.H., and Von Doenhoff, A.E. (1949) Theory of Wing Sections, section 1.3 <a href="#fnref:8" class="footnote-back-ref">↩</a></p></li> </ol>