FX 63-120 AIRFOIL (fx63120-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-120 AIRFOIL (fx63120-il) Reynolds number: 500,000 Max Cl/Cd: 125.74 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63120-il-500000.txt Download as CSV file: xf-fx63120-il-500000.csv |
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 -0.1694 0.8952 0.0335
-6.000 0.0768 0.01420 0.00850 -0.1708 0.8875 0.0346
-5.750 0.1047 0.01284 0.00707 -0.1713 0.8781 0.0359
-5.500 0.1359 0.01225 0.00641 -0.1721 0.8706 0.0370
-5.250 0.1642 0.01181 0.00594 -0.1723 0.8617 0.0381
-5.000 0.1949 0.01147 0.00551 -0.1729 0.8544 0.0397
-4.750 0.2233 0.01113 0.00512 -0.1731 0.8459 0.0409
-4.500 0.2538 0.01076 0.00464 -0.1736 0.8379 0.0419
-4.250 0.2836 0.01020 0.00406 -0.1742 0.8282 0.0438
-4.000 0.3137 0.00997 0.00377 -0.1747 0.8199 0.0460
-3.750 0.3431 0.00976 0.00352 -0.1750 0.8117 0.0484
-3.500 0.3739 0.00953 0.00320 -0.1756 0.8051 0.0511
-3.250 0.4038 0.00929 0.00297 -0.1761 0.7974 0.0562
-3.000 0.4345 0.00908 0.00273 -0.1766 0.7907 0.0676
-2.750 0.4687 0.00831 0.00244 -0.1787 0.7836 0.2105
-2.500 0.5009 0.00791 0.00243 -0.1800 0.7767 0.3636
-2.250 0.5300 0.00792 0.00242 -0.1801 0.7700 0.3941
-2.000 0.5588 0.00791 0.00241 -0.1802 0.7626 0.4145
-1.750 0.5879 0.00794 0.00240 -0.1803 0.7563 0.4335
-1.500 0.6165 0.00792 0.00241 -0.1803 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
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