S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1221 w/o flap (s1221-il) Reynolds number: 200,000 Max Cl/Cd: 76.51 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1221-il-200000-n5.txt Download as CSV file: xf-s1221-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3050 0.09052 0.08712 -0.0264 1.0000 0.0188
-7.250 -0.3024 0.08826 0.08491 -0.0261 1.0000 0.0186
-7.000 -0.3061 0.08482 0.08154 -0.0263 1.0000 0.0186
-6.750 -0.3034 0.08112 0.07788 -0.0283 0.9987 0.0186
-6.500 -0.3021 0.07194 0.06872 -0.0375 0.9914 0.0188
-6.250 -0.2867 0.06688 0.06368 -0.0436 0.9828 0.0186
-6.000 -0.2785 0.05805 0.05486 -0.0535 0.9697 0.0183
-5.250 -0.1281 0.02428 0.01884 -0.1193 0.9281 0.0169
-5.000 -0.0810 0.02168 0.01581 -0.1245 0.9058 0.0170
-4.750 -0.0087 0.01911 0.01275 -0.1342 0.8602 0.0174
-4.500 0.1136 0.01683 0.00959 -0.1539 0.7519 0.0184
-4.250 0.1504 0.01635 0.00867 -0.1558 0.6937 0.0189
-4.000 0.1814 0.01587 0.00798 -0.1567 0.6530 0.0197
-3.750 0.2112 0.01558 0.00747 -0.1573 0.6147 0.0212
-3.500 0.2411 0.01532 0.00694 -0.1577 0.5824 0.0227
-3.250 0.2727 0.01495 0.00638 -0.1587 0.5558 0.0240
-3.000 0.3041 0.01468 0.00590 -0.1595 0.5345 0.0257
-2.750 0.3358 0.01443 0.00545 -0.1603 0.5164 0.0283
-2.500 0.3676 0.01420 0.00505 -0.1611 0.5007 0.0338
-2.250 0.4018 0.01373 0.00461 -0.1627 0.4862 0.0734
-2.000 0.4375 0.01311 0.00446 -0.1650 0.4729 0.2329
-1.750 0.4665 0.01329 0.00461 -0.1650 0.4618 0.2854
-1.500 0.4949 0.01356 0.00479 -0.1649 0.4517 0.3163
-1.250 0.5238 0.01367 0.00479 -0.1648 0.4429 0.3285
-1.000 0.5525 0.01376 0.00477 -0.1647 0.4348 0.3351
-0.750 0.5815 0.01382 0.00471 -0.1647 0.4273 0.3410
-0.500 0.6103 0.01388 0.00468 -0.1647 0.4199 0.3456
-0.250 0.6391 0.01395 0.00468 -0.1647 0.4132 0.3498
0.000 0.6680 0.01402 0.00468 -0.1646 0.4062 0.3550
0.250 0.6965 0.01415 0.00468 -0.1646 0.4003 0.3607
0.500 0.7255 0.01420 0.00475 -0.1646 0.3948 0.3658
0.750 0.7543 0.01430 0.00480 -0.1646 0.3894 0.3716
1.000 0.7828 0.01444 0.00486 -0.1645 0.3847 0.3779
1.250 0.8115 0.01454 0.00497 -0.1645 0.3802 0.3843
1.500 0.8401 0.01465 0.00507 -0.1644 0.3751 0.3925
1.750 0.8686 0.01478 0.00519 -0.1644 0.3705 0.4010
2.000 0.8968 0.01496 0.00532 -0.1643 0.3666 0.4113
2.250 0.9255 0.01508 0.00549 -0.1643 0.3629 0.4216
2.500 0.9542 0.01521 0.00567 -0.1643 0.3589 0.4334
2.750 0.9826 0.01537 0.00584 -0.1643 0.3549 0.4471
3.250 1.0393 0.01574 0.00625 -0.1642 0.3481 0.4808
3.500 1.0680 0.01588 0.00650 -0.1642 0.3448 0.5026
3.750 1.0965 0.01604 0.00675 -0.1643 0.3415 0.5284
4.000 1.1249 0.01621 0.00702 -0.1643 0.3382 0.5583
4.250 1.1530 0.01640 0.00727 -0.1642 0.3352 0.5945
4.500 1.1807 0.01658 0.00758 -0.1640 0.3322 0.6426
4.750 1.2066 0.01668 0.00792 -0.1634 0.3294 0.7181
5.000 1.2303 0.01680 0.00822 -0.1622 0.3266 0.7951
5.250 1.2491 0.01683 0.00840 -0.1600 0.3239 0.8719
5.500 1.2699 0.01693 0.00855 -0.1583 0.3212 1.0000
5.750 1.2976 0.01727 0.00884 -0.1582 0.3184 1.0000
6.000 1.3253 0.01760 0.00919 -0.1582 0.3157 1.0000
6.250 1.3528 0.01789 0.00955 -0.1581 0.3126 1.0000
6.500 1.3800 0.01819 0.00991 -0.1579 0.3091 1.0000
6.750 1.4070 0.01849 0.01023 -0.1577 0.3058 1.0000
7.000 1.4337 0.01884 0.01056 -0.1574 0.3027 1.0000
7.250 1.4602 0.01918 0.01096 -0.1572 0.2993 1.0000
7.500 1.4866 0.01947 0.01136 -0.1569 0.2951 1.0000
7.750 1.5126 0.01977 0.01172 -0.1565 0.2910 1.0000
8.000 1.5383 0.02011 0.01207 -0.1561 0.2873 1.0000
8.250 1.5640 0.02049 0.01250 -0.1557 0.2837 1.0000
8.500 1.5894 0.02081 0.01297 -0.1553 0.2793 1.0000
8.750 1.6145 0.02113 0.01338 -0.1548 0.2748 1.0000
9.000 1.6389 0.02150 0.01375 -0.1542 0.2706 1.0000
9.250 1.6635 0.02183 0.01424 -0.1537 0.2649 1.0000
9.500 1.6875 0.02214 0.01465 -0.1530 0.2587 1.0000
9.750 1.7108 0.02250 0.01507 -0.1523 0.2528 1.0000
10.000 1.7343 0.02283 0.01553 -0.1515 0.2447 1.0000
10.250 1.7567 0.02321 0.01599 -0.1507 0.2368 1.0000
10.500 1.7787 0.02363 0.01649 -0.1498 0.2277 1.0000
10.750 1.8004 0.02411 0.01707 -0.1488 0.2182 1.0000
11.000 1.8205 0.02468 0.01768 -0.1477 0.2082 1.0000
11.250 1.8391 0.02536 0.01840 -0.1464 0.1971 1.0000
11.500 1.8565 0.02614 0.01923 -0.1450 0.1846 1.0000
11.750 1.8719 0.02706 0.02018 -0.1433 0.1716 1.0000
12.000 1.8842 0.02817 0.02131 -0.1412 0.1582 1.0000
12.250 1.8933 0.02947 0.02263 -0.1387 0.1455 1.0000
12.500 1.8977 0.03086 0.02406 -0.1356 0.1348 1.0000
12.750 1.8991 0.03243 0.02568 -0.1321 0.1257 1.0000
13.000 1.8976 0.03428 0.02758 -0.1287 0.1175 1.0000
13.250 1.8967 0.03619 0.02959 -0.1256 0.1101 1.0000
13.500 1.8901 0.03869 0.03217 -0.1226 0.1040 1.0000
13.750 1.8848 0.04133 0.03494 -0.1203 0.0981 1.0000
14.000 1.8729 0.04491 0.03863 -0.1186 0.0933 1.0000
14.250 1.8619 0.04893 0.04280 -0.1180 0.0893 1.0000
14.500 1.8480 0.05392 0.04795 -0.1185 0.0856 1.0000
14.750 1.8293 0.06014 0.05432 -0.1200 0.0826 1.0000
15.000 1.8094 0.06697 0.06132 -0.1222 0.0802 1.0000
15.250 1.7910 0.07382 0.06835 -0.1244 0.0776 1.0000
15.500 1.7700 0.08118 0.07587 -0.1269 0.0753 1.0000
15.750 1.7479 0.08884 0.08367 -0.1296 0.0732 1.0000
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Polar data table (+)
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