S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1221 w/o flap (s1221-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.86 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1221-il-1000000.txt Download as CSV file: xf-s1221-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3344 0.11526 0.11361 -0.0162 1.0000 0.0124
-9.250 -0.3309 0.11176 0.11013 -0.0171 1.0000 0.0124
-9.000 -0.3323 0.10741 0.10581 -0.0179 1.0000 0.0126
-8.750 -0.3277 0.10497 0.10338 -0.0180 1.0000 0.0127
-8.500 -0.3238 0.10231 0.10074 -0.0183 1.0000 0.0128
-8.250 -0.3084 0.09859 0.09702 -0.0221 0.9990 0.0129
-8.000 -0.2891 0.09512 0.09355 -0.0263 0.9975 0.0131
-7.750 -0.2712 0.09097 0.08940 -0.0313 0.9958 0.0133
-7.500 -0.2527 0.08663 0.08506 -0.0367 0.9943 0.0136
-7.250 -0.2400 0.08227 0.08071 -0.0409 0.9917 0.0139
-7.000 -0.2281 0.07703 0.07549 -0.0463 0.9886 0.0146
-6.500 -0.2342 0.03228 0.03010 -0.1121 0.9650 0.0159
-6.250 -0.2035 0.02945 0.02716 -0.1170 0.9552 0.0161
-6.000 -0.1683 0.02702 0.02460 -0.1219 0.9431 0.0166
-5.500 0.0524 0.01331 0.00835 -0.1662 0.7539 0.0128
-5.250 0.0776 0.01289 0.00757 -0.1658 0.6931 0.0128
-5.000 0.1059 0.01237 0.00684 -0.1661 0.6537 0.0131
-4.750 0.1350 0.01195 0.00621 -0.1664 0.6100 0.0132
-4.500 0.1651 0.01153 0.00556 -0.1670 0.5698 0.0131
-4.250 0.1961 0.01115 0.00499 -0.1677 0.5387 0.0132
-4.000 0.2277 0.01081 0.00450 -0.1685 0.5153 0.0133
-3.750 0.2592 0.01052 0.00409 -0.1693 0.4960 0.0136
-3.500 0.2907 0.01028 0.00373 -0.1700 0.4799 0.0140
-3.250 0.3219 0.01008 0.00342 -0.1706 0.4658 0.0146
-3.000 0.3528 0.00992 0.00316 -0.1710 0.4534 0.0152
-2.750 0.3843 0.00971 0.00286 -0.1717 0.4425 0.0160
-2.500 0.4150 0.00959 0.00265 -0.1721 0.4317 0.0170
-2.250 0.4453 0.00950 0.00250 -0.1724 0.4219 0.0183
-2.000 0.4758 0.00941 0.00235 -0.1727 0.4131 0.0215
-1.750 0.5140 0.00863 0.00202 -0.1754 0.4044 0.1755
-1.500 0.5450 0.00851 0.00205 -0.1760 0.3969 0.2460
-1.250 0.5741 0.00855 0.00207 -0.1760 0.3899 0.2629
-1.000 0.6027 0.00864 0.00210 -0.1758 0.3825 0.2740
-0.750 0.6318 0.00867 0.00215 -0.1758 0.3770 0.2887
-0.500 0.6606 0.00874 0.00220 -0.1758 0.3705 0.3008
-0.250 0.6889 0.00886 0.00225 -0.1755 0.3646 0.3084
0.000 0.7183 0.00887 0.00226 -0.1756 0.3598 0.3142
0.250 0.7472 0.00893 0.00229 -0.1756 0.3547 0.3180
0.500 0.7758 0.00903 0.00234 -0.1755 0.3492 0.3218
0.750 0.8047 0.00908 0.00237 -0.1754 0.3456 0.3253
1.000 0.8338 0.00912 0.00241 -0.1754 0.3414 0.3310
1.250 0.8625 0.00921 0.00247 -0.1754 0.3373 0.3367
1.500 0.8908 0.00932 0.00255 -0.1753 0.3330 0.3420
1.750 0.9199 0.00936 0.00261 -0.1753 0.3306 0.3491
2.000 0.9487 0.00941 0.00268 -0.1753 0.3275 0.3569
2.250 0.9774 0.00949 0.00276 -0.1752 0.3241 0.3655
2.500 1.0058 0.00960 0.00286 -0.1751 0.3206 0.3756
2.750 1.0342 0.00973 0.00300 -0.1751 0.3171 0.3873
3.000 1.0630 0.00978 0.00309 -0.1751 0.3153 0.4006
3.250 1.0918 0.00984 0.00320 -0.1751 0.3132 0.4162
3.500 1.1205 0.00991 0.00332 -0.1750 0.3108 0.4344
3.750 1.1490 0.01000 0.00345 -0.1750 0.3080 0.4548
4.000 1.1774 0.01012 0.00359 -0.1750 0.3050 0.4769
4.250 1.2054 0.01029 0.00379 -0.1749 0.3016 0.5015
4.750 1.2631 0.01039 0.00408 -0.1750 0.2981 0.5642
5.000 1.2923 0.01043 0.00423 -0.1752 0.2955 0.6079
5.250 1.3218 0.01047 0.00443 -0.1755 0.2926 0.6809
5.500 1.3502 0.01055 0.00466 -0.1755 0.2892 0.7657
5.750 1.3771 0.01072 0.00491 -0.1751 0.2853 0.8172
6.000 1.4037 0.01071 0.00504 -0.1747 0.2834 0.8681
6.250 1.4228 0.01061 0.00510 -0.1725 0.2813 1.0000
6.500 1.4506 0.01075 0.00525 -0.1724 0.2787 1.0000
6.750 1.4781 0.01091 0.00541 -0.1722 0.2757 1.0000
7.000 1.5051 0.01114 0.00562 -0.1719 0.2721 1.0000
7.250 1.5323 0.01132 0.00581 -0.1717 0.2688 1.0000
7.500 1.5601 0.01141 0.00594 -0.1716 0.2656 1.0000
7.750 1.5874 0.01156 0.00610 -0.1714 0.2615 1.0000
8.000 1.6139 0.01180 0.00630 -0.1711 0.2557 1.0000
8.250 1.6412 0.01193 0.00647 -0.1710 0.2513 1.0000
8.500 1.6681 0.01210 0.00665 -0.1707 0.2462 1.0000
8.750 1.6943 0.01235 0.00689 -0.1704 0.2409 1.0000
9.000 1.7210 0.01253 0.00710 -0.1701 0.2365 1.0000
9.250 1.7472 0.01277 0.00734 -0.1698 0.2298 1.0000
9.500 1.7729 0.01304 0.00760 -0.1694 0.2225 1.0000
9.750 1.7983 0.01336 0.00790 -0.1689 0.2137 1.0000
10.000 1.8234 0.01369 0.00823 -0.1685 0.2045 1.0000
10.250 1.8476 0.01414 0.00862 -0.1679 0.1923 1.0000
10.500 1.8708 0.01467 0.00909 -0.1672 0.1779 1.0000
10.750 1.8931 0.01532 0.00966 -0.1663 0.1617 1.0000
11.000 1.9140 0.01611 0.01034 -0.1653 0.1447 1.0000
11.250 1.9344 0.01692 0.01107 -0.1642 0.1290 1.0000
11.500 1.9542 0.01777 0.01184 -0.1630 0.1138 1.0000
11.750 1.9736 0.01862 0.01263 -0.1618 0.1009 1.0000
12.000 1.9923 0.01950 0.01345 -0.1605 0.0893 1.0000
12.250 2.0102 0.02040 0.01431 -0.1590 0.0790 1.0000
12.500 2.0269 0.02138 0.01524 -0.1574 0.0695 1.0000
12.750 2.0430 0.02235 0.01619 -0.1557 0.0619 1.0000
13.000 2.0583 0.02331 0.01716 -0.1539 0.0554 1.0000
13.250 2.0719 0.02434 0.01819 -0.1519 0.0503 1.0000
13.500 2.0839 0.02537 0.01926 -0.1496 0.0466 1.0000
13.750 2.0895 0.02656 0.02048 -0.1462 0.0432 1.0000
14.000 2.0967 0.02756 0.02154 -0.1431 0.0412 1.0000
14.250 2.1008 0.02882 0.02286 -0.1398 0.0393 1.0000
14.500 2.1016 0.03039 0.02449 -0.1363 0.0370 1.0000
14.750 2.1045 0.03189 0.02607 -0.1333 0.0357 1.0000
15.000 2.1061 0.03358 0.02785 -0.1306 0.0344 1.0000
15.250 2.1040 0.03569 0.03005 -0.1279 0.0333 1.0000
15.500 2.0982 0.03833 0.03278 -0.1255 0.0322 1.0000
15.750 2.0884 0.04173 0.03629 -0.1239 0.0311 1.0000
16.000 2.0754 0.04609 0.04078 -0.1233 0.0304 1.0000
16.250 2.0661 0.05061 0.04544 -0.1238 0.0298 1.0000
16.500 2.0530 0.05614 0.05113 -0.1251 0.0294 1.0000
16.750 2.0342 0.06294 0.05809 -0.1271 0.0291 1.0000
17.000 2.0109 0.07075 0.06608 -0.1296 0.0287 1.0000
17.250 1.9825 0.07953 0.07504 -0.1325 0.0288 1.0000
17.500 1.9532 0.08850 0.08417 -0.1355 0.0284 1.0000
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