Parameter Analysis of Active Flap Control for Rotor Aerodynamic Control and Design

<div>Horizontal force of 0.84R section with different TEF span lengths: (a) <span class="nowrap"><svg height="12.4764pt" id="M86" style="vertical-align:-3.1685pt" version="1.1" viewbox="-0.0498162 -9.3079 76.1171 12.4764" width="76.1171pt" 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="M169 380V459C122 440 66 423 24 416V392C86 384 90 382 90 317V-135C90 -201 81 -207 17 -213V-240H253V-213C176 -207 169 -201 169 -125V6C182 -1 208 -11 238 -12C368 12 487 109 487 260C487 358 421 449 310 449C298 449 279 444 261 433L169 380ZM169 346C196 367 237 389 269 389C341 389 403 329 403 221C403 109 347 37 263 37C228 37 191 53 169 76V346Z"></path></g><g transform="matrix(.013,0,0,-0.013,6.721,0)"><path d="M513 0V26C455 31 447 37 447 103V278C447 398 390 449 309 449C255 449 202 412 166 376V712C127 700 67 684 19 677V653C85 647 87 643 87 580V103C87 37 79 31 19 26L18 0H231V26C171 32 166 39 166 103V341C194 373 232 392 270 392C337 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International Journal of Aerospace Engineering

fig17

Figure 17

Figure 17: Parameter Analysis of Active Flap Control for Rotor Aerodynamic Control and Design 