S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1221 w/o flap (s1221-il) Reynolds number: 1,000,000 Max Cl/Cd: 135.07 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1221-il-1000000-n5.txt Download as CSV file: xf-s1221-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2693 0.10032 0.09855 -0.0399 0.9874 0.0069
-9.000 -0.2709 0.09475 0.09299 -0.0422 0.9853 0.0070
-8.750 -0.4493 0.05312 0.05112 -0.0646 0.9823 0.0072
-8.250 -0.4375 0.02731 0.02460 -0.1093 0.9579 0.0071
-8.000 -0.3973 0.02374 0.02074 -0.1183 0.9491 0.0072
-7.500 -0.1903 0.01634 0.01166 -0.1595 0.7435 0.0075
-7.250 -0.1643 0.01563 0.01062 -0.1601 0.6914 0.0075
-7.000 -0.1358 0.01497 0.00972 -0.1609 0.6558 0.0076
-6.750 -0.1070 0.01441 0.00894 -0.1617 0.6151 0.0077
-6.500 -0.0782 0.01404 0.00836 -0.1623 0.5767 0.0078
-6.250 -0.0485 0.01363 0.00777 -0.1630 0.5472 0.0080
-6.000 -0.0185 0.01326 0.00724 -0.1636 0.5227 0.0081
-5.750 0.0120 0.01286 0.00669 -0.1644 0.5028 0.0083
-5.500 0.0431 0.01244 0.00614 -0.1652 0.4861 0.0083
-5.250 0.0743 0.01205 0.00563 -0.1660 0.4720 0.0085
-5.000 0.1056 0.01171 0.00517 -0.1668 0.4591 0.0086
-4.750 0.1368 0.01141 0.00476 -0.1675 0.4469 0.0088
-4.500 0.1679 0.01114 0.00438 -0.1682 0.4348 0.0090
-4.250 0.1991 0.01089 0.00405 -0.1688 0.4254 0.0092
-3.750 0.2606 0.01052 0.00352 -0.1698 0.4088 0.0096
-3.500 0.2918 0.01031 0.00322 -0.1704 0.4007 0.0100
-3.250 0.3228 0.01013 0.00298 -0.1709 0.3942 0.0104
-3.000 0.3531 0.01001 0.00281 -0.1712 0.3871 0.0109
-2.750 0.3833 0.00993 0.00266 -0.1715 0.3809 0.0114
-2.500 0.4134 0.00985 0.00253 -0.1718 0.3744 0.0119
-2.250 0.4433 0.00980 0.00242 -0.1720 0.3674 0.0126
-2.000 0.4735 0.00972 0.00231 -0.1722 0.3621 0.0144
-1.750 0.5037 0.00964 0.00222 -0.1725 0.3567 0.0206
-1.500 0.5351 0.00947 0.00211 -0.1732 0.3512 0.0561
-1.250 0.5684 0.00914 0.00199 -0.1744 0.3470 0.1358
-1.000 0.6008 0.00889 0.00196 -0.1754 0.3425 0.2249
-0.750 0.6303 0.00889 0.00200 -0.1756 0.3377 0.2550
-0.500 0.6593 0.00894 0.00205 -0.1756 0.3329 0.2723
-0.250 0.6885 0.00896 0.00208 -0.1756 0.3292 0.2831
0.000 0.7174 0.00902 0.00211 -0.1755 0.3253 0.2872
0.250 0.7462 0.00908 0.00213 -0.1755 0.3215 0.2897
0.750 0.8039 0.00921 0.00221 -0.1753 0.3147 0.2962
1.000 0.8327 0.00926 0.00226 -0.1753 0.3115 0.3005
1.250 0.8614 0.00933 0.00231 -0.1752 0.3085 0.3045
1.500 0.8900 0.00942 0.00237 -0.1751 0.3055 0.3080
1.750 0.9186 0.00950 0.00244 -0.1751 0.3025 0.3126
2.000 0.9473 0.00957 0.00252 -0.1750 0.3003 0.3179
2.250 0.9759 0.00963 0.00259 -0.1749 0.2981 0.3232
2.500 1.0044 0.00971 0.00267 -0.1748 0.2955 0.3287
2.750 1.0329 0.00979 0.00276 -0.1748 0.2932 0.3356
3.000 1.0612 0.00988 0.00286 -0.1747 0.2909 0.3424
3.250 1.0896 0.00998 0.00297 -0.1746 0.2885 0.3512
3.750 1.1463 0.01016 0.00321 -0.1744 0.2844 0.3713
4.000 1.1747 0.01024 0.00332 -0.1743 0.2825 0.3817
4.250 1.2030 0.01033 0.00344 -0.1743 0.2805 0.3937
4.500 1.2313 0.01042 0.00357 -0.1742 0.2784 0.4071
4.750 1.2594 0.01052 0.00372 -0.1741 0.2759 0.4215
5.000 1.2874 0.01065 0.00387 -0.1740 0.2728 0.4372
5.250 1.3153 0.01079 0.00404 -0.1739 0.2697 0.4546
5.500 1.3436 0.01086 0.00418 -0.1738 0.2674 0.4740
5.750 1.3718 0.01095 0.00434 -0.1738 0.2640 0.4974
6.000 1.3999 0.01106 0.00451 -0.1738 0.2603 0.5254
6.250 1.4279 0.01120 0.00470 -0.1737 0.2569 0.5568
6.500 1.4561 0.01131 0.00490 -0.1737 0.2540 0.5929
6.750 1.4848 0.01138 0.00510 -0.1739 0.2512 0.6412
7.000 1.5137 0.01145 0.00534 -0.1740 0.2473 0.7235
7.250 1.5410 0.01161 0.00558 -0.1739 0.2419 0.7764
7.500 1.5681 0.01175 0.00579 -0.1737 0.2368 0.8133
7.750 1.5941 0.01190 0.00602 -0.1732 0.2297 0.8567
8.000 1.6127 0.01194 0.00618 -0.1711 0.2216 1.0000
8.250 1.6384 0.01229 0.00646 -0.1707 0.2100 1.0000
8.500 1.6640 0.01264 0.00676 -0.1703 0.1989 1.0000
8.750 1.6897 0.01296 0.00706 -0.1699 0.1900 1.0000
9.000 1.7146 0.01337 0.00743 -0.1694 0.1793 1.0000
9.250 1.7387 0.01388 0.00786 -0.1688 0.1650 1.0000
9.500 1.7620 0.01448 0.00837 -0.1681 0.1490 1.0000
9.750 1.7852 0.01507 0.00890 -0.1673 0.1357 1.0000
10.000 1.8082 0.01566 0.00944 -0.1666 0.1242 1.0000
10.250 1.8307 0.01630 0.01002 -0.1658 0.1125 1.0000
10.500 1.8527 0.01695 0.01062 -0.1649 0.1017 1.0000
10.750 1.8743 0.01763 0.01126 -0.1639 0.0918 1.0000
11.000 1.8957 0.01831 0.01190 -0.1630 0.0826 1.0000
11.250 1.9163 0.01904 0.01260 -0.1619 0.0734 1.0000
11.500 1.9357 0.01987 0.01338 -0.1606 0.0639 1.0000
11.750 1.9549 0.02066 0.01415 -0.1594 0.0566 1.0000
12.000 1.9731 0.02151 0.01498 -0.1580 0.0502 1.0000
12.250 1.9916 0.02228 0.01576 -0.1566 0.0459 1.0000
12.500 2.0089 0.02311 0.01660 -0.1551 0.0418 1.0000
12.750 2.0256 0.02392 0.01744 -0.1535 0.0388 1.0000
13.000 2.0399 0.02488 0.01842 -0.1515 0.0354 1.0000
13.250 2.0534 0.02579 0.01937 -0.1494 0.0332 1.0000
13.500 2.0614 0.02682 0.02045 -0.1464 0.0315 1.0000
13.750 2.0677 0.02788 0.02157 -0.1432 0.0301 1.0000
14.000 2.0748 0.02895 0.02271 -0.1403 0.0289 1.0000
14.250 2.0806 0.03017 0.02400 -0.1374 0.0280 1.0000
14.500 2.0833 0.03167 0.02557 -0.1343 0.0268 1.0000
14.750 2.0832 0.03346 0.02744 -0.1313 0.0257 1.0000
15.000 2.0821 0.03546 0.02953 -0.1287 0.0247 1.0000
15.250 2.0810 0.03765 0.03182 -0.1265 0.0241 1.0000
15.500 2.0769 0.04036 0.03463 -0.1247 0.0235 1.0000
15.750 2.0687 0.04388 0.03827 -0.1237 0.0226 1.0000
16.000 2.0589 0.04817 0.04269 -0.1238 0.0223 1.0000
16.250 2.0436 0.05382 0.04849 -0.1249 0.0216 1.0000
16.500 2.0246 0.06055 0.05537 -0.1268 0.0211 1.0000
16.750 2.0036 0.06794 0.06293 -0.1291 0.0210 1.0000
17.000 1.9754 0.07668 0.07184 -0.1320 0.0205 1.0000
17.250 1.9506 0.08491 0.08024 -0.1347 0.0209 1.0000
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