XFOIL Version 6.96 Calculated polar for: WORTMANN FX 3 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.500 -0.5093 0.11118 0.10811 -0.0739 0.9616 0.0380 -12.250 -0.5353 0.10406 0.10092 -0.0768 0.9605 0.0374 -12.000 -0.5676 0.09681 0.09357 -0.0792 0.9596 0.0369 -11.750 -0.6009 0.09009 0.08671 -0.0806 0.9586 0.0364 -11.500 -0.6334 0.08392 0.08037 -0.0808 0.9577 0.0359 -11.250 -0.6650 0.07819 0.07447 -0.0802 0.9569 0.0355 -11.000 -0.6947 0.07306 0.06913 -0.0789 0.9561 0.0352 -10.750 -0.9058 0.07020 0.06530 -0.0627 0.9580 0.0314 -10.500 -0.8876 0.07107 0.06633 -0.0632 0.9569 0.0325 -10.250 -0.9395 0.06441 0.05910 -0.0551 0.9489 0.0317 -10.000 -0.9383 0.06171 0.05617 -0.0537 0.9458 0.0321 -9.750 -0.9296 0.05932 0.05356 -0.0532 0.9438 0.0326 -9.500 -0.9157 0.05746 0.05146 -0.0532 0.9424 0.0333 -9.250 -0.8999 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-0.5260 0.04081 0.03278 -0.0413 0.8962 0.1047 -4.250 -0.4917 0.04127 0.03327 -0.0440 0.8955 0.1126 -4.000 -0.4947 0.03951 0.03148 -0.0396 0.8869 0.1160 -3.750 -0.4602 0.03917 0.03123 -0.0428 0.8846 0.1280 -3.500 -0.4178 0.03865 0.03106 -0.0484 0.8833 0.1753 -3.250 -0.4146 0.04206 0.03712 -0.0387 0.8809 0.6229 -3.000 -0.3665 0.04502 0.03982 -0.0432 0.8799 0.6723 -2.750 -0.3768 0.04442 0.03921 -0.0360 0.8700 0.6819 -2.500 -0.3617 0.04641 0.04117 -0.0311 0.8669 0.6950 -2.250 -0.3399 0.04850 0.04320 -0.0279 0.8652 0.7081 -2.000 -0.3519 0.04837 0.04310 -0.0196 0.8574 0.7121 -1.750 -0.3319 0.04926 0.04391 -0.0174 0.8534 0.7239 -1.500 -0.3056 0.05058 0.04515 -0.0165 0.8511 0.7373 -1.250 -0.2909 0.05207 0.04663 -0.0109 0.8496 0.7440 -1.000 -0.2945 0.05122 0.04576 -0.0070 0.8404 0.7540 -0.750 -0.2686 0.05231 0.04678 -0.0062 0.8373 0.7683 -0.500 -0.2598 0.05309 0.04757 0.0011 0.8353 0.7786 -0.250 -0.1594 0.05772 0.05227 0.0006 0.8368 0.8700 0.000 -0.2664 0.05438 0.04893 0.0213 0.8236 0.8496 2.000 -0.0796 0.05125 0.04538 0.0197 0.7705 0.8756 2.250 -0.0422 0.05086 0.04494 0.0170 0.7681 0.8738 2.500 -0.0067 0.05092 0.04495 0.0110 0.7596 0.8611 2.750 0.0290 0.05056 0.04456 0.0086 0.7570 0.8603 3.000 0.0689 0.05039 0.04436 0.0055 0.7554 0.8600 3.250 0.0836 0.04990 0.04388 0.0060 0.7463 0.8575 3.500 0.1240 0.04964 0.04361 0.0027 0.7445 0.8559 3.750 0.1446 0.04954 0.04353 0.0018 0.7360 0.8539 4.000 0.1833 0.04930 0.04328 -0.0012 0.7337 0.8537 4.250 0.2263 0.04907 0.04306 -0.0051 0.7323 0.8527 4.500 0.2539 0.04934 0.04335 -0.0080 0.7232 0.8495 4.750 0.3070 0.04956 0.04360 -0.0146 0.7213 0.8473 5.000 0.3510 0.04930 0.04336 -0.0184 0.7199 0.8471 5.250 0.3647 0.04921 0.04332 -0.0175 0.7103 0.8463 5.500 0.4023 0.04863 0.04278 -0.0197 0.7082 0.8454 5.750 0.4424 0.04798 0.04218 -0.0224 0.7067 0.8445 6.000 0.4595 0.04808 0.04235 -0.0223 0.6965 0.8432 6.250 0.4998 0.04744 0.04177 -0.0250 0.6942 0.8430 6.500 0.5426 0.04663 0.04103 -0.0281 0.6927 0.8426 6.750 0.5620 0.04679 0.04127 -0.0283 0.6820 0.8412 7.000 0.6041 0.04597 0.04053 -0.0313 0.6797 0.8401 7.250 0.6470 0.04501 0.03967 -0.0342 0.6780 0.8398 7.500 0.6743 0.04455 0.03930 -0.0351 0.6672 0.8390 7.750 0.7345 0.04136 0.03621 -0.0391 0.6635 0.8378 8.000 0.7858 0.03948 0.03443 -0.0430 0.6612 0.8364 8.250 0.8171 0.03945 0.03452 -0.0452 0.6491 0.8344 8.500 0.8680 0.03777 0.03296 -0.0490 0.6453 0.8338 8.750 0.9016 0.03742 0.03271 -0.0509 0.6321 0.8331 9.000 0.9501 0.03598 0.03136 -0.0544 0.6159 0.8319 9.250 0.9926 0.03432 0.02967 -0.0563 0.5859 0.8312 9.500 1.0314 0.03305 0.02820 -0.0577 0.5373 0.8305 9.750 1.0502 0.03315 0.02798 -0.0567 0.4771 0.8296 10.000 1.0533 0.03439 0.02884 -0.0540 0.4125 0.8284 10.250 1.0506 0.03620 0.03028 -0.0509 0.3483 0.8273 10.500 1.0464 0.03833 0.03203 -0.0480 0.2834 0.8260 10.750 1.0438 0.04056 0.03388 -0.0456 0.2223 0.8249 11.000 1.0455 0.04265 0.03567 -0.0439 0.1750 0.8237 11.250 1.0525 0.04446 0.03729 -0.0428 0.1438 0.8229 11.500 1.0616 0.04613 0.03885 -0.0421 0.1200 0.8224 11.750 1.0708 0.04786 0.04048 -0.0413 0.0980 0.8218 12.000 1.0756 0.05008 0.04254 -0.0403 0.0743 0.8208 12.250 1.0829 0.05226 0.04467 -0.0396 0.0575 0.8197 12.500 1.0917 0.05441 0.04678 -0.0393 0.0495 0.8187 12.750 1.1039 0.05635 0.04872 -0.0394 0.0442 0.8177 13.000 1.1135 0.05852 0.05092 -0.0391 0.0410 0.8169 13.250 1.1234 0.06015 0.05264 -0.0383 0.0383 0.8164 13.500 1.1318 0.06194 0.05445 -0.0376 0.0361 0.8160 13.750 1.1401 0.06374 0.05626 -0.0366 0.0342 0.8155 14.000 1.1529 0.06523 0.05791 -0.0361 0.0326 0.8151 14.250 1.1660 0.06669 0.05947 -0.0356 0.0312 0.8146 14.500 1.1796 0.06816 0.06100 -0.0351 0.0300 0.8142 14.750 1.1938 0.06958 0.06247 -0.0348 0.0289 0.8138 15.000 1.2151 0.07055 0.06344 -0.0343 0.0275 0.8134 15.250 1.2304 0.07222 0.06531 -0.0339 0.0267 0.8130 15.500 1.2405 0.07426 0.06756 -0.0334 0.0260 0.8126 15.750 1.2510 0.07643 0.06997 -0.0330 0.0255 0.8122 16.000 1.2589 0.07893 0.07271 -0.0325 0.0250 0.8118 16.250 1.2633 0.08183 0.07586 -0.0320 0.0246 0.8113 16.500 1.2641 0.08513 0.07942 -0.0315 0.0244 0.8109 16.750 1.2607 0.08890 0.08346 -0.0311 0.0243 0.8105 17.000 1.2536 0.09308 0.08793 -0.0309 0.0241 0.8101 17.250 1.2431 0.09778 0.09291 -0.0311 0.0240 0.8098 17.500 1.2300 0.10290 0.09831 -0.0317 0.0240 0.8095 17.750 1.2150 0.10846 0.10413 -0.0330 0.0238 0.8092 18.000 1.1949 0.11509 0.11106 -0.0351 0.0240 0.8088 18.250 1.1735 0.12229 0.11854 -0.0382 0.0241 0.8083 18.500 1.1479 0.13081 0.12734 -0.0426 0.0244 0.8077