FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-110 AIRFOIL (fx63110-il) Reynolds number: 500,000 Max Cl/Cd: 118.34 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63110-il-500000.txt Download as CSV file: xf-fx63110-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-110 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3535 0.09220 0.08995 -0.0397 1.0000 0.0285
-9.000 -0.3562 0.08958 0.08737 -0.0394 1.0000 0.0290
-8.750 -0.4546 0.02522 0.02117 -0.1158 0.9759 0.0222
-8.500 -0.4187 0.02394 0.01982 -0.1190 0.9738 0.0230
-8.250 -0.3836 0.02279 0.01856 -0.1217 0.9710 0.0238
-8.000 -0.3516 0.02103 0.01651 -0.1239 0.9652 0.0251
-7.750 -0.3140 0.01975 0.01487 -0.1268 0.9623 0.0264
-7.500 -0.2781 0.01786 0.01290 -0.1298 0.9602 0.0280
-7.250 -0.2469 0.01720 0.01218 -0.1308 0.9538 0.0293
-7.000 -0.2114 0.01623 0.01104 -0.1327 0.9497 0.0308
-6.750 -0.1729 0.01522 0.00982 -0.1352 0.9468 0.0323
-6.500 -0.1393 0.01413 0.00873 -0.1369 0.9404 0.0342
-6.250 -0.1021 0.01354 0.00809 -0.1390 0.9352 0.0360
-6.000 -0.0637 0.01290 0.00734 -0.1413 0.9301 0.0377
-5.750 -0.0280 0.01205 0.00639 -0.1431 0.9222 0.0396
-5.500 0.0088 0.01139 0.00571 -0.1452 0.9150 0.0417
-5.250 0.0424 0.01098 0.00524 -0.1464 0.9053 0.0437
-5.000 0.0745 0.01069 0.00486 -0.1473 0.8956 0.0458
-4.750 0.1066 0.01020 0.00427 -0.1482 0.8863 0.0478
-4.500 0.1362 0.00982 0.00386 -0.1487 0.8755 0.0506
-4.250 0.1658 0.00963 0.00360 -0.1489 0.8646 0.0538
-4.000 0.1954 0.00940 0.00327 -0.1492 0.8537 0.0573
-3.750 0.2244 0.00913 0.00299 -0.1494 0.8428 0.0635
-3.500 0.2541 0.00890 0.00275 -0.1498 0.8343 0.0742
-3.250 0.2833 0.00871 0.00257 -0.1500 0.8254 0.0946
-3.000 0.3130 0.00847 0.00238 -0.1504 0.8172 0.1207
-2.750 0.3431 0.00812 0.00220 -0.1511 0.8087 0.1769
-2.500 0.3741 0.00763 0.00213 -0.1522 0.8008 0.3314
-2.250 0.4031 0.00753 0.00210 -0.1524 0.7925 0.3759
-2.000 0.4321 0.00747 0.00207 -0.1525 0.7846 0.4052
-1.750 0.4609 0.00741 0.00204 -0.1526 0.7763 0.4329
-1.500 0.4900 0.00733 0.00206 -0.1528 0.7686 0.4755
-1.250 0.5187 0.00729 0.00213 -0.1529 0.7605 0.5243
-1.000 0.5472 0.00733 0.00218 -0.1528 0.7525 0.5539
-0.750 0.5756 0.00737 0.00221 -0.1527 0.7443 0.5758
-0.500 0.6039 0.00742 0.00226 -0.1526 0.7365 0.5952
-0.250 0.6321 0.00747 0.00230 -0.1525 0.7281 0.6107
0.000 0.6603 0.00753 0.00235 -0.1524 0.7199 0.6252
0.250 0.6883 0.00759 0.00239 -0.1522 0.7115 0.6390
0.500 0.7162 0.00764 0.00246 -0.1521 0.7029 0.6526
0.750 0.7439 0.00771 0.00252 -0.1518 0.6941 0.6649
1.000 0.7716 0.00776 0.00256 -0.1516 0.6826 0.6748
1.250 0.7989 0.00783 0.00261 -0.1513 0.6695 0.6838
1.500 0.8261 0.00790 0.00266 -0.1510 0.6566 0.6921
1.750 0.8534 0.00801 0.00273 -0.1507 0.6452 0.7010
2.000 0.8809 0.00807 0.00281 -0.1505 0.6337 0.7094
2.250 0.9083 0.00817 0.00290 -0.1503 0.6219 0.7188
2.500 0.9353 0.00826 0.00300 -0.1500 0.6096 0.7270
2.750 0.9622 0.00839 0.00310 -0.1496 0.5941 0.7361
3.000 0.9886 0.00850 0.00321 -0.1492 0.5765 0.7447
3.250 1.0151 0.00864 0.00333 -0.1488 0.5593 0.7544
3.500 1.0414 0.00880 0.00347 -0.1485 0.5418 0.7653
4.000 1.0918 0.00923 0.00380 -0.1473 0.4930 0.7881
4.250 1.1162 0.00950 0.00400 -0.1466 0.4664 0.8027
4.500 1.1403 0.00977 0.00423 -0.1458 0.4434 0.8208
4.750 1.1641 0.01001 0.00447 -0.1449 0.4236 0.8437
5.000 1.1853 0.01019 0.00470 -0.1435 0.4023 0.8798
5.250 1.2028 0.01031 0.00484 -0.1412 0.3814 1.0000
5.500 1.2281 0.01071 0.00512 -0.1409 0.3531 1.0000
5.750 1.2523 0.01119 0.00546 -0.1404 0.3205 1.0000
6.000 1.2752 0.01177 0.00584 -0.1397 0.2837 1.0000
6.250 1.2973 0.01243 0.00630 -0.1388 0.2460 1.0000
6.500 1.3191 0.01310 0.00680 -0.1380 0.2148 1.0000
6.750 1.3411 0.01373 0.00730 -0.1371 0.1884 1.0000
7.000 1.3625 0.01441 0.00783 -0.1362 0.1610 1.0000
7.250 1.3826 0.01519 0.00842 -0.1351 0.1289 1.0000
7.500 1.4012 0.01609 0.00912 -0.1338 0.0987 1.0000
7.750 1.4203 0.01690 0.00983 -0.1325 0.0813 1.0000
8.000 1.4392 0.01770 0.01056 -0.1312 0.0689 1.0000
8.250 1.4572 0.01854 0.01135 -0.1297 0.0600 1.0000
8.500 1.4770 0.01916 0.01200 -0.1285 0.0549 1.0000
8.750 1.4931 0.02004 0.01287 -0.1267 0.0504 1.0000
9.000 1.5123 0.02062 0.01351 -0.1254 0.0480 1.0000
9.250 1.5288 0.02130 0.01421 -0.1237 0.0455 1.0000
9.500 1.5401 0.02220 0.01513 -0.1211 0.0431 1.0000
9.750 1.5504 0.02314 0.01614 -0.1185 0.0414 1.0000
10.000 1.5640 0.02388 0.01695 -0.1164 0.0400 1.0000
10.250 1.5763 0.02473 0.01787 -0.1143 0.0386 1.0000
10.500 1.5868 0.02572 0.01890 -0.1120 0.0371 1.0000
10.750 1.5926 0.02708 0.02031 -0.1094 0.0356 1.0000
11.000 1.5949 0.02880 0.02211 -0.1065 0.0343 1.0000
11.250 1.6066 0.02985 0.02327 -0.1049 0.0334 1.0000
11.500 1.6158 0.03115 0.02465 -0.1031 0.0323 1.0000
11.750 1.6239 0.03258 0.02616 -0.1014 0.0311 1.0000
12.000 1.6305 0.03421 0.02785 -0.0998 0.0300 1.0000
12.250 1.6304 0.03656 0.03025 -0.0979 0.0289 1.0000
12.500 1.6304 0.03904 0.03285 -0.0961 0.0279 1.0000
12.750 1.6397 0.04066 0.03458 -0.0952 0.0270 1.0000
13.000 1.6464 0.04258 0.03661 -0.0942 0.0260 1.0000
13.250 1.6514 0.04474 0.03885 -0.0933 0.0251 1.0000
13.500 1.6551 0.04711 0.04129 -0.0925 0.0243 1.0000
13.750 1.6540 0.05014 0.04439 -0.0918 0.0235 1.0000
14.000 1.6475 0.05395 0.04830 -0.0910 0.0227 1.0000
14.250 1.6530 0.05638 0.05086 -0.0908 0.0221 1.0000
14.500 1.6565 0.05913 0.05376 -0.0907 0.0213 1.0000
14.750 1.6587 0.06213 0.05686 -0.0907 0.0206 1.0000
15.000 1.6599 0.06534 0.06016 -0.0910 0.0200 1.0000
15.250 1.6596 0.06887 0.06377 -0.0914 0.0194 1.0000
15.500 1.6552 0.07310 0.06807 -0.0921 0.0189 1.0000
15.750 1.6463 0.07809 0.07317 -0.0928 0.0184 1.0000
16.000 1.6457 0.08206 0.07730 -0.0939 0.0180 1.0000
16.250 1.6431 0.08645 0.08184 -0.0951 0.0176 1.0000
16.500 1.6401 0.09101 0.08654 -0.0965 0.0171 1.0000
16.750 1.6357 0.09587 0.09153 -0.0982 0.0168 1.0000
17.000 1.6315 0.10080 0.09659 -0.1001 0.0164 1.0000
17.250 1.6270 0.10587 0.10177 -0.1022 0.0160 1.0000
17.500 1.6224 0.11105 0.10705 -0.1045 0.0157 1.0000
17.750 1.6170 0.11639 0.11248 -0.1069 0.0154 1.0000
18.000 1.6097 0.12207 0.11824 -0.1096 0.0151 1.0000
18.250 1.5997 0.12810 0.12437 -0.1124 0.0147 1.0000
18.500 1.5933 0.13397 0.13041 -0.1156 0.0146 1.0000
18.750 1.5864 0.13998 0.13658 -0.1191 0.0144 1.0000
19.000 1.5788 0.14630 0.14305 -0.1229 0.0141 1.0000
19.250 1.5705 0.15270 0.14960 -0.1269 0.0138 1.0000
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