Knowledge-Based Shape Optimization of Morphing Wing for More Efficient Aircraft

<div>Comparison between the <svg height="14.1101pt" id="M234" style="vertical-align:-5.4742pt" version="1.1" viewbox="-0.0498162 -8.6359 14.7021 14.1101" width="14.7021pt" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink"><g transform="matrix(.013,0,0,-0.013,0,0)"><path d="M645 631C614 643 545 666 457 666C215 666 23 519 23 283C23 90 158 -16 337 -16C412 -16 489 2 522 10C543 39 590 127 606 167L580 181C519 89 459 18 348 18C201 18 122 136 122 287C122 464 244 632 435 632C544 632 602 595 608 472L639 475C643 526 645 581 645 631Z" id="g113-68"></path><glyph.data ascent="3473" descent="-2876" horiz-adv-x="668" vert-adv-y="668"></glyph.data></g><g transform="matrix(.0091,0,0,-0.0091,8.619,3.132)"><path d="M573 302C573 402 527 451 414 451C386 451 343 446 313 437L330 513L320 522C295 508 261 484 243 463L230 415C194 400 159 383 126 359L131 330C159 344 187 357 222 368L109 -147C96 -204 80 -214 18 -223L13 -255L256 -244L259 -212L236 -210C184 -205 180 -195 191 -141L219 -1C240 -10 268 -12 284 -12C352 4 431 48 484 104C543 166 573 240 573 302ZM481 290C481 165 381 37 305 37C280 37 249 56 235 71L302 395C328 399 353 402 372 402C427 402 481 378 481 290Z" id="g50-113"></path><glyph.data ascent="3443" descent="-2856" horiz-adv-x="597" vert-adv-y="597"></glyph.data></g></svg> distributions at cruise Mach over the reference wing (right) and over the wing equipped with morphing leading edge (left).</div>

International Journal of Aerospace Engineering

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Figure 13

Figure 13: Knowledge-Based Shape Optimization of Morphing Wing for More Efficient Aircraft 