XFOIL Version 6.96 Calculated polar for: FX 63-120 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.2639 0.09582 0.09356 -0.0555 0.9932 0.0279 -9.250 -0.2618 0.08548 0.08322 -0.0680 0.9880 0.0289 -9.000 -0.2503 0.08053 0.07828 -0.0720 0.9855 0.0294 -8.750 -0.2317 0.07801 0.07576 -0.0746 0.9818 0.0298 -8.500 -0.2131 0.07531 0.07306 -0.0777 0.9767 0.0305 -8.250 -0.1945 0.07096 0.06871 -0.0836 0.9730 0.0316 -8.000 -0.2227 0.03431 0.03120 -0.1380 0.9383 0.0297 -7.750 -0.1848 0.02750 0.02389 -0.1476 0.9346 0.0276 -7.500 -0.1453 0.02211 0.01780 -0.1549 0.9285 0.0279 -7.250 -0.1031 0.02008 0.01528 -0.1594 0.9236 0.0288 -7.000 -0.0624 0.01740 0.01237 -0.1639 0.9192 0.0303 -6.750 -0.0276 0.01654 0.01143 -0.1658 0.9110 0.0314 -6.500 0.0103 0.01542 0.01011 -0.1683 0.9045 0.0325 -6.250 0.0423 0.01456 0.00907 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0.7490 0.4499 -1.250 0.6454 0.00795 0.00241 -0.1804 0.7423 0.4654 -1.000 0.6741 0.00795 0.00244 -0.1805 0.7352 0.4818 -0.750 0.7027 0.00797 0.00248 -0.1805 0.7282 0.5027 -0.500 0.7313 0.00801 0.00252 -0.1805 0.7214 0.5188 -0.250 0.7597 0.00803 0.00257 -0.1805 0.7139 0.5341 0.000 0.7882 0.00810 0.00262 -0.1805 0.7071 0.5490 0.250 0.8165 0.00811 0.00268 -0.1805 0.6992 0.5633 0.500 0.8449 0.00820 0.00273 -0.1805 0.6920 0.5788 0.750 0.8730 0.00822 0.00281 -0.1804 0.6837 0.5960 1.000 0.9008 0.00831 0.00287 -0.1802 0.6752 0.6129 1.250 0.9282 0.00835 0.00294 -0.1800 0.6639 0.6286 1.500 0.9555 0.00842 0.00301 -0.1797 0.6527 0.6434 1.750 0.9828 0.00853 0.00309 -0.1795 0.6430 0.6573 2.000 1.0102 0.00861 0.00319 -0.1793 0.6326 0.6703 2.250 1.0373 0.00870 0.00330 -0.1790 0.6224 0.6821 2.750 1.0912 0.00892 0.00353 -0.1784 0.6002 0.7057 3.000 1.1178 0.00904 0.00366 -0.1781 0.5881 0.7167 3.250 1.1441 0.00918 0.00379 -0.1777 0.5748 0.7269 3.500 1.1701 0.00935 0.00393 -0.1772 0.5593 0.7378 3.750 1.1956 0.00952 0.00409 -0.1767 0.5421 0.7483 4.000 1.2209 0.00971 0.00426 -0.1761 0.5243 0.7588 4.250 1.2459 0.00994 0.00445 -0.1755 0.5053 0.7702 4.500 1.2701 0.01021 0.00467 -0.1748 0.4857 0.7820 4.750 1.2943 0.01048 0.00491 -0.1741 0.4680 0.7945 5.000 1.3185 0.01074 0.00516 -0.1734 0.4512 0.8088 5.250 1.3421 0.01100 0.00543 -0.1726 0.4337 0.8257 5.750 1.3848 0.01153 0.00598 -0.1699 0.3954 0.8823 6.000 1.4010 0.01170 0.00617 -0.1675 0.3767 1.0000 6.250 1.4246 0.01214 0.00652 -0.1669 0.3558 1.0000 6.500 1.4480 0.01257 0.00687 -0.1662 0.3319 1.0000 6.750 1.4697 0.01311 0.00728 -0.1653 0.3065 1.0000 7.000 1.4901 0.01373 0.00776 -0.1641 0.2788 1.0000 7.250 1.5099 0.01439 0.00828 -0.1629 0.2516 1.0000 7.500 1.5290 0.01507 0.00884 -0.1616 0.2279 1.0000 7.750 1.5478 0.01575 0.00942 -0.1602 0.2066 1.0000 8.000 1.5656 0.01647 0.01004 -0.1586 0.1867 1.0000 8.250 1.5828 0.01718 0.01067 -0.1570 0.1652 1.0000 8.500 1.5965 0.01804 0.01138 -0.1548 0.1427 1.0000 8.750 1.6082 0.01891 0.01215 -0.1522 0.1218 1.0000 9.000 1.6185 0.01985 0.01299 -0.1495 0.1056 1.0000 9.250 1.6291 0.02079 0.01388 -0.1469 0.0935 1.0000 9.500 1.6402 0.02171 0.01478 -0.1444 0.0844 1.0000 9.750 1.6503 0.02272 0.01578 -0.1419 0.0765 1.0000 10.000 1.6598 0.02380 0.01685 -0.1395 0.0696 1.0000 10.250 1.6704 0.02483 0.01793 -0.1373 0.0640 1.0000 10.500 1.6787 0.02607 0.01916 -0.1349 0.0588 1.0000 10.750 1.6882 0.02726 0.02041 -0.1328 0.0549 1.0000 11.000 1.6976 0.02851 0.02169 -0.1308 0.0515 1.0000 11.250 1.7021 0.03020 0.02340 -0.1285 0.0481 1.0000 11.500 1.7125 0.03148 0.02477 -0.1269 0.0460 1.0000 11.750 1.7209 0.03296 0.02632 -0.1252 0.0438 1.0000 12.000 1.7261 0.03479 0.02818 -0.1235 0.0416 1.0000 12.250 1.7285 0.03696 0.03041 -0.1216 0.0396 1.0000 12.500 1.7369 0.03862 0.03217 -0.1204 0.0380 1.0000 12.750 1.7428 0.04057 0.03420 -0.1191 0.0363 1.0000 13.000 1.7448 0.04300 0.03668 -0.1178 0.0346 1.0000 13.250 1.7406 0.04621 0.03998 -0.1164 0.0331 1.0000 13.500 1.7471 0.04832 0.04221 -0.1155 0.0319 1.0000 13.750 1.7511 0.05078 0.04476 -0.1147 0.0305 1.0000 14.000 1.7522 0.05364 0.04770 -0.1141 0.0292 1.0000 14.250 1.7466 0.05749 0.05161 -0.1135 0.0279 1.0000 14.500 1.7455 0.06089 0.05513 -0.1131 0.0268 1.0000 14.750 1.7479 0.06391 0.05827 -0.1129 0.0256 1.0000 15.000 1.7486 0.06724 0.06170 -0.1129 0.0246 1.0000 15.250 1.7465 0.07107 0.06562 -0.1131 0.0236 1.0000 15.500 1.7374 0.07605 0.07068 -0.1136 0.0227 1.0000 15.750 1.7333 0.08043 0.07519 -0.1142 0.0220 1.0000 16.000 1.7323 0.08441 0.07931 -0.1149 0.0212 1.0000 16.250 1.7299 0.08871 0.08373 -0.1157 0.0205 1.0000 16.500 1.7270 0.09317 0.08829 -0.1168 0.0198 1.0000 16.750 1.7218 0.09808 0.09329 -0.1182 0.0192 1.0000 17.000 1.7123 0.10379 0.09909 -0.1200 0.0187 1.0000