An Integrated Method for Designing Airfoils Shapes

<div>Comparison of the lift coefficient <svg height="9.16067pt" id="M126" style="vertical-align:-3.16062pt" version="1.1" viewbox="-0.0498162 -6.00005 7.32699 9.16067" width="7.32699pt" 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="M387 400C387 425 348 451 303 451C247 451 176 414 132 376C69 322 24 228 24 148C24 43 74 -12 147 -12C211 -12 301 33 363 103L346 128C319 99 249 51 193 51C148 51 112 84 112 165C112 230 130 287 154 330C170 359 199 400 243 400C277 400 304 383 326 354C333 345 343 343 354 348C378 360 387 382 387 400Z" id="g50-100"></path><glyph.data ascent="3443" descent="-2856" horiz-adv-x="411" vert-adv-y="411"></glyph.data></g><g transform="matrix(.0091,0,0,-0.0091,4.238,3.001)"><path d="M238 675C244 702 241 710 231 710C220 710 155 682 74 673L70 643H101C147 643 151 635 142 594L39 111C18 11 36 -12 55 -12C89 -12 170 38 223 103L207 129C176 98 130 68 118 68C113 68 108 72 114 102L238 675Z" id="g50-109"></path><glyph.data ascent="3443" descent="-2856" horiz-adv-x="271" vert-adv-y="271"></glyph.data></g></svg> (a) and the lift-drag ratio <svg height="12.449pt" id="M127" style="vertical-align:-3.16067pt" version="1.1" viewbox="-0.0498162 -9.28833 22.8285 12.449" width="22.8285pt" 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="M387 400C387 425 348 451 303 451C247 451 176 414 132 376C69 322 24 228 24 148C24 43 74 -12 147 -12C211 -12 301 33 363 103L346 128C319 99 249 51 193 51C148 51 112 84 112 165C112 230 130 287 154 330C170 359 199 400 243 400C277 400 304 383 326 354C333 345 343 343 354 348C378 360 387 382 387 400Z" id="g50-100"></path><glyph.data ascent="3443" descent="-2856" horiz-adv-x="411" vert-adv-y="411"></glyph.data></g><g transform="matrix(.0091,0,0,-0.0091,4.238,3.001)"><path d="M238 675C244 702 241 710 231 710C220 710 155 682 74 673L70 643H101C147 643 151 635 142 594L39 111C18 11 36 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Mathematical Problems in Engineering

An Integrated Method for Designing Airfoils Shapes

Figure 16