S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: S1221 w/ 4 deg flap (s1221-flap-il) Reynolds number: 200,000 Max Cl/Cd: 76.29 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1221-flap-il-200000-n5.txt Download as CSV file: xf-s1221-flap-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1221 w/ 4 deg flap
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2236 0.09565 0.09216 -0.0428 0.9839 0.0224
-8.000 -0.2113 0.09183 0.08835 -0.0459 0.9799 0.0221
-7.750 -0.2018 0.08718 0.08371 -0.0499 0.9762 0.0223
-7.500 -0.1945 0.08356 0.08012 -0.0521 0.9710 0.0221
-7.000 -0.2089 0.06897 0.06557 -0.0613 0.9579 0.0189
-6.750 -0.1989 0.06477 0.06140 -0.0651 0.9516 0.0187
-6.500 -0.1897 0.05734 0.05396 -0.0731 0.9445 0.0183
-6.250 -0.0985 0.03019 0.02547 -0.1338 0.9390 0.0170
-6.000 -0.0397 0.02555 0.02017 -0.1450 0.9337 0.0170
-5.750 0.0149 0.02267 0.01683 -0.1523 0.9288 0.0172
-5.500 0.0585 0.02078 0.01464 -0.1564 0.9218 0.0175
-5.250 0.0987 0.01929 0.01294 -0.1592 0.9128 0.0179
-5.000 0.1360 0.01812 0.01162 -0.1613 0.9015 0.0184
-4.750 0.1755 0.01706 0.01042 -0.1636 0.8857 0.0189
-4.250 0.3606 0.01463 0.00680 -0.1898 0.6609 0.0238
-4.000 0.3936 0.01454 0.00636 -0.1910 0.6113 0.0253
-3.750 0.4254 0.01445 0.00595 -0.1919 0.5747 0.0275
-3.500 0.4579 0.01430 0.00557 -0.1930 0.5463 0.0318
-3.000 0.5340 0.01333 0.00490 -0.1984 0.5035 0.2111
-2.750 0.5627 0.01353 0.00503 -0.1985 0.4878 0.2700
-2.500 0.5907 0.01385 0.00525 -0.1983 0.4741 0.3057
-2.250 0.6190 0.01405 0.00534 -0.1981 0.4626 0.3203
-2.000 0.6475 0.01421 0.00531 -0.1980 0.4527 0.3286
-1.750 0.6762 0.01429 0.00532 -0.1980 0.4432 0.3341
-1.500 0.7048 0.01442 0.00532 -0.1979 0.4350 0.3397
-1.250 0.7338 0.01451 0.00529 -0.1979 0.4267 0.3447
-0.750 0.7911 0.01471 0.00537 -0.1979 0.4119 0.3532
-0.500 0.8196 0.01485 0.00541 -0.1978 0.4051 0.3590
-0.250 0.8482 0.01498 0.00548 -0.1978 0.3995 0.3641
0.000 0.8770 0.01508 0.00558 -0.1978 0.3937 0.3691
0.250 0.9054 0.01524 0.00567 -0.1977 0.3885 0.3753
0.500 0.9337 0.01541 0.00578 -0.1976 0.3838 0.3815
0.750 0.9624 0.01553 0.00593 -0.1976 0.3786 0.3884
1.250 1.0190 0.01589 0.00623 -0.1975 0.3693 0.4056
1.500 1.0475 0.01607 0.00642 -0.1974 0.3655 0.4154
1.750 1.0762 0.01622 0.00662 -0.1974 0.3614 0.4258
2.000 1.1044 0.01641 0.00682 -0.1974 0.3573 0.4373
2.250 1.1325 0.01663 0.00704 -0.1973 0.3535 0.4505
2.750 1.1892 0.01704 0.00755 -0.1972 0.3467 0.4833
3.000 1.2175 0.01723 0.00784 -0.1972 0.3434 0.5027
3.250 1.2456 0.01745 0.00811 -0.1971 0.3400 0.5243
3.500 1.2734 0.01771 0.00840 -0.1970 0.3368 0.5483
3.750 1.3012 0.01797 0.00873 -0.1968 0.3339 0.5747
4.000 1.3291 0.01818 0.00908 -0.1967 0.3308 0.6053
4.250 1.3563 0.01840 0.00945 -0.1964 0.3278 0.6413
4.500 1.3825 0.01864 0.00981 -0.1959 0.3249 0.6839
4.750 1.4080 0.01891 0.01016 -0.1952 0.3219 0.7251
5.000 1.4339 0.01925 0.01049 -0.1947 0.3192 0.7582
5.250 1.4601 0.01954 0.01086 -0.1942 0.3165 0.7848
5.500 1.4853 0.01977 0.01123 -0.1936 0.3134 0.8081
5.750 1.5091 0.01997 0.01154 -0.1926 0.3101 0.8333
6.000 1.5277 0.02006 0.01176 -0.1905 0.3070 0.8818
6.250 1.5503 0.02032 0.01204 -0.1893 0.3040 1.0000
6.500 1.5766 0.02070 0.01246 -0.1890 0.3006 1.0000
6.750 1.6025 0.02101 0.01288 -0.1886 0.2963 1.0000
7.000 1.6279 0.02134 0.01328 -0.1881 0.2922 1.0000
7.250 1.6529 0.02172 0.01365 -0.1876 0.2884 1.0000
7.500 1.6779 0.02212 0.01411 -0.1870 0.2848 1.0000
7.750 1.7026 0.02247 0.01461 -0.1864 0.2804 1.0000
8.000 1.7266 0.02282 0.01504 -0.1857 0.2758 1.0000
8.250 1.7499 0.02323 0.01545 -0.1848 0.2714 1.0000
8.500 1.7732 0.02359 0.01597 -0.1840 0.2658 1.0000
8.750 1.7957 0.02394 0.01642 -0.1830 0.2595 1.0000
9.000 1.8172 0.02435 0.01688 -0.1818 0.2534 1.0000
9.250 1.8389 0.02472 0.01739 -0.1807 0.2452 1.0000
9.500 1.8592 0.02517 0.01790 -0.1794 0.2375 1.0000
9.750 1.8792 0.02564 0.01846 -0.1781 0.2287 1.0000
10.000 1.8986 0.02618 0.01909 -0.1766 0.2200 1.0000
10.250 1.9156 0.02681 0.01978 -0.1749 0.2104 1.0000
10.500 1.9316 0.02753 0.02056 -0.1729 0.1993 1.0000
10.750 1.9445 0.02838 0.02146 -0.1705 0.1877 1.0000
11.000 1.9546 0.02936 0.02247 -0.1677 0.1757 1.0000
11.250 1.9622 0.03054 0.02367 -0.1647 0.1627 1.0000
11.500 1.9679 0.03192 0.02507 -0.1615 0.1507 1.0000
11.750 1.9712 0.03351 0.02669 -0.1582 0.1397 1.0000
12.250 1.9738 0.03720 0.03050 -0.1516 0.1205 1.0000
12.500 1.9718 0.03942 0.03279 -0.1484 0.1126 1.0000
12.750 1.9674 0.04196 0.03542 -0.1453 0.1054 1.0000
13.000 1.9626 0.04470 0.03827 -0.1426 0.0990 1.0000
13.250 1.9535 0.04805 0.04172 -0.1402 0.0936 1.0000
13.500 1.9436 0.05177 0.04560 -0.1384 0.0889 1.0000
13.750 1.9312 0.05620 0.05018 -0.1374 0.0847 1.0000
14.000 1.9138 0.06193 0.05607 -0.1378 0.0816 1.0000
14.250 1.8966 0.06829 0.06261 -0.1391 0.0788 1.0000
14.500 1.8784 0.07525 0.06976 -0.1411 0.0761 1.0000
14.750 1.8570 0.08300 0.07768 -0.1436 0.0738 1.0000
15.000 1.8342 0.09111 0.08595 -0.1463 0.0720 1.0000
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Polar data table (+)
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