S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1221 w/o flap (s1221-il) Reynolds number: 100,000 Max Cl/Cd: 45.22 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1221-il-100000.txt Download as CSV file: xf-s1221-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S1221 w/o flap
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.2569 0.09921 0.09475 -0.0210 1.0000 0.1121
-6.500 -0.2707 0.09805 0.09372 -0.0220 1.0000 0.1171
-6.250 -0.3068 0.09855 0.09443 -0.0236 1.0000 0.1185
-6.000 -0.2695 0.09254 0.08838 -0.0201 1.0000 0.1217
-5.750 -0.2613 0.09027 0.08618 -0.0183 1.0000 0.1254
-5.500 -0.2694 0.08883 0.08486 -0.0168 1.0000 0.1296
-5.250 -0.3016 0.08724 0.08351 -0.0238 1.0000 0.1342
-5.000 -0.2870 0.08445 0.08076 -0.0166 1.0000 0.1365
-4.750 -0.2812 0.08257 0.07895 -0.0138 1.0000 0.1401
-4.500 -0.2954 0.08109 0.07766 -0.0184 1.0000 0.1480
-4.250 -0.2653 0.07684 0.07344 -0.0208 0.9938 0.1530
-4.000 -0.1367 0.03886 0.03395 -0.0951 0.9883 0.0753
-3.750 -0.0503 0.03048 0.02436 -0.1114 0.9849 0.0634
-3.500 0.0205 0.02682 0.02003 -0.1208 0.9729 0.0640
-3.250 0.0852 0.02394 0.01670 -0.1278 0.9561 0.0645
-3.000 0.1412 0.02136 0.01397 -0.1325 0.9304 0.0658
-2.750 0.1962 0.01922 0.01197 -0.1367 0.8939 0.0702
-2.500 0.2822 0.01709 0.00972 -0.1469 0.8400 0.0886
-2.250 0.3788 0.01701 0.00995 -0.1596 0.7536 0.3635
-2.000 0.4088 0.01854 0.01128 -0.1582 0.7041 0.4081
-1.750 0.4374 0.01916 0.01161 -0.1574 0.6705 0.4316
-1.500 0.4676 0.01936 0.01150 -0.1576 0.6433 0.4466
-1.250 0.4958 0.01949 0.01139 -0.1572 0.6223 0.4569
-1.000 0.5269 0.01952 0.01112 -0.1578 0.6037 0.4665
-0.750 0.5573 0.01958 0.01093 -0.1582 0.5874 0.4756
-0.500 0.5880 0.01959 0.01075 -0.1587 0.5727 0.4833
-0.250 0.6183 0.01968 0.01068 -0.1592 0.5599 0.4915
0.000 0.6495 0.01978 0.01058 -0.1599 0.5490 0.4991
0.250 0.6793 0.01991 0.01056 -0.1602 0.5385 0.5068
0.500 0.7096 0.02005 0.01061 -0.1607 0.5285 0.5158
0.750 0.7396 0.02025 0.01065 -0.1610 0.5201 0.5252
1.000 0.7692 0.02043 0.01083 -0.1613 0.5119 0.5344
1.250 0.7998 0.02067 0.01095 -0.1618 0.5047 0.5466
1.500 0.8283 0.02093 0.01122 -0.1619 0.4979 0.5590
1.750 0.8570 0.02115 0.01148 -0.1620 0.4906 0.5735
2.000 0.8869 0.02146 0.01169 -0.1622 0.4850 0.5904
2.250 0.9150 0.02176 0.01214 -0.1623 0.4788 0.6105
2.500 0.9425 0.02204 0.01252 -0.1621 0.4732 0.6346
2.750 0.9698 0.02237 0.01286 -0.1618 0.4684 0.6663
3.000 0.9939 0.02271 0.01344 -0.1608 0.4631 0.7061
3.250 1.0160 0.02298 0.01394 -0.1594 0.4579 0.7650
3.500 1.0276 0.02296 0.01415 -0.1554 0.4542 0.8615
3.750 1.0528 0.02328 0.01433 -0.1549 0.4506 1.0000
4.000 1.0823 0.02402 0.01514 -0.1557 0.4453 1.0000
4.250 1.1113 0.02469 0.01581 -0.1561 0.4401 1.0000
4.500 1.1408 0.02534 0.01636 -0.1565 0.4359 1.0000
4.750 1.1693 0.02618 0.01715 -0.1567 0.4324 1.0000
5.000 1.1943 0.02709 0.01825 -0.1566 0.4275 1.0000
5.250 1.2210 0.02786 0.01907 -0.1565 0.4228 1.0000
5.500 1.2491 0.02854 0.01970 -0.1566 0.4188 1.0000
5.750 1.2759 0.02951 0.02067 -0.1566 0.4153 1.0000
6.000 1.2979 0.03066 0.02210 -0.1560 0.4101 1.0000
6.250 1.3234 0.03150 0.02301 -0.1558 0.4054 1.0000
6.500 1.3512 0.03217 0.02364 -0.1557 0.4015 1.0000
6.750 1.3744 0.03337 0.02498 -0.1553 0.3972 1.0000
7.000 1.3944 0.03470 0.02655 -0.1545 0.3915 1.0000
7.250 1.4205 0.03542 0.02730 -0.1542 0.3870 1.0000
7.500 1.4498 0.03597 0.02777 -0.1543 0.3832 1.0000
7.750 1.4632 0.03790 0.03010 -0.1529 0.3768 1.0000
8.000 1.4866 0.03875 0.03104 -0.1523 0.3714 1.0000
8.250 1.5175 0.03890 0.03110 -0.1524 0.3672 1.0000
8.500 1.5288 0.04105 0.03362 -0.1508 0.3607 1.0000
8.750 1.5512 0.04184 0.03453 -0.1500 0.3548 1.0000
9.000 1.5843 0.04167 0.03422 -0.1502 0.3506 1.0000
9.250 1.5899 0.04421 0.03721 -0.1481 0.3431 1.0000
9.500 1.6165 0.04439 0.03743 -0.1476 0.3374 1.0000
9.750 1.6484 0.04416 0.03710 -0.1476 0.3324 1.0000
10.000 1.6519 0.04647 0.03985 -0.1451 0.3241 1.0000
10.250 1.6920 0.04494 0.03813 -0.1456 0.3186 1.0000
10.500 1.6950 0.04720 0.04077 -0.1430 0.3103 1.0000
10.750 1.7324 0.04561 0.03906 -0.1431 0.3036 1.0000
11.000 1.7422 0.04693 0.04065 -0.1410 0.2955 1.0000
11.250 1.7766 0.04540 0.03902 -0.1408 0.2879 1.0000
11.500 1.7867 0.04634 0.04020 -0.1385 0.2794 1.0000
11.750 1.8240 0.04433 0.03801 -0.1386 0.2712 1.0000
12.000 1.8256 0.04574 0.03978 -0.1354 0.2619 1.0000
12.250 1.8556 0.04436 0.03827 -0.1347 0.2532 1.0000
12.500 1.8608 0.04501 0.03917 -0.1317 0.2435 1.0000
12.750 1.8670 0.04559 0.03992 -0.1287 0.2341 1.0000
13.000 1.8827 0.04516 0.03942 -0.1266 0.2243 1.0000
13.250 1.8711 0.04679 0.04129 -0.1218 0.2156 1.0000
13.500 1.8655 0.04819 0.04277 -0.1180 0.2070 1.0000
13.750 1.8673 0.04910 0.04357 -0.1152 0.1972 1.0000
14.000 1.8443 0.05283 0.04760 -0.1119 0.1896 1.0000
14.250 1.8361 0.05554 0.05029 -0.1101 0.1810 1.0000
14.500 1.8182 0.05981 0.05469 -0.1092 0.1734 1.0000
14.750 1.8031 0.06437 0.05931 -0.1090 0.1661 1.0000
15.000 1.7902 0.06896 0.06391 -0.1095 0.1586 1.0000
15.250 1.7713 0.07492 0.06999 -0.1107 0.1522 1.0000
15.500 1.7652 0.07902 0.07403 -0.1113 0.1446 1.0000
15.750 1.7443 0.08585 0.08103 -0.1134 0.1393 1.0000
16.000 1.7329 0.09126 0.08651 -0.1150 0.1334 1.0000
16.250 1.7288 0.09555 0.09080 -0.1157 0.1276 1.0000
16.500 1.7044 0.10366 0.09916 -0.1193 0.1240 1.0000
16.750 1.4164 0.17504 0.17121 -0.1646 0.1307 1.0000
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Polar data table (+)
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