S3021-095-84 (s3021-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3021-095-84 (s3021-il) Reynolds number: 100,000 Max Cl/Cd: 55.06 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3021-il-100000-n5.txt Download as CSV file: xf-s3021-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S3021-095-84
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4035 0.08734 0.08250 -0.0330 1.0000 0.0351
-8.250 -0.3995 0.08431 0.07950 -0.0324 1.0000 0.0338
-8.000 -0.4011 0.08080 0.07607 -0.0334 1.0000 0.0326
-7.750 -0.4070 0.07718 0.07254 -0.0347 1.0000 0.0316
-7.500 -0.4126 0.07274 0.06816 -0.0374 1.0000 0.0304
-7.250 -0.4271 0.06169 0.05696 -0.0462 1.0000 0.0269
-7.000 -0.4279 0.05802 0.05327 -0.0460 1.0000 0.0266
-6.750 -0.4276 0.05460 0.04976 -0.0454 1.0000 0.0264
-6.500 -0.4286 0.05053 0.04548 -0.0448 1.0000 0.0266
-6.250 -0.4286 0.04685 0.04150 -0.0436 1.0000 0.0269
-5.750 -0.3834 0.03779 0.03161 -0.0488 0.9856 0.0274
-5.500 -0.3521 0.03435 0.02755 -0.0510 0.9763 0.0269
-5.250 -0.3207 0.03100 0.02371 -0.0531 0.9680 0.0268
-5.000 -0.2885 0.02819 0.02042 -0.0547 0.9593 0.0268
-4.750 -0.2562 0.02590 0.01768 -0.0559 0.9502 0.0269
-4.500 -0.2212 0.02374 0.01517 -0.0575 0.9430 0.0272
-4.250 -0.1907 0.02203 0.01325 -0.0582 0.9325 0.0277
-4.000 -0.1588 0.02067 0.01175 -0.0590 0.9227 0.0286
-3.750 -0.1251 0.01962 0.01061 -0.0601 0.9141 0.0310
-3.500 -0.0947 0.01881 0.00967 -0.0605 0.9027 0.0341
-3.250 -0.0648 0.01795 0.00866 -0.0607 0.8915 0.0362
-3.000 -0.0352 0.01710 0.00772 -0.0609 0.8807 0.0393
-2.750 -0.0044 0.01646 0.00693 -0.0612 0.8704 0.0452
-2.500 0.0239 0.01574 0.00624 -0.0610 0.8588 0.0636
-2.250 0.0499 0.01479 0.00581 -0.0608 0.8470 0.1794
-2.000 0.0740 0.01374 0.00565 -0.0605 0.8357 0.3934
-1.750 0.0949 0.01268 0.00560 -0.0585 0.8252 0.6541
-1.500 0.1551 0.01210 0.00546 -0.0630 0.8173 0.9211
-1.250 0.2135 0.01203 0.00510 -0.0688 0.8077 0.9887
-1.000 0.2484 0.01202 0.00485 -0.0703 0.7963 1.0000
-0.750 0.2730 0.01207 0.00467 -0.0695 0.7848 1.0000
-0.500 0.2970 0.01215 0.00458 -0.0687 0.7727 1.0000
-0.250 0.3211 0.01224 0.00451 -0.0679 0.7610 1.0000
0.000 0.3454 0.01234 0.00445 -0.0670 0.7497 1.0000
0.250 0.3698 0.01244 0.00441 -0.0662 0.7389 1.0000
0.500 0.3943 0.01255 0.00438 -0.0654 0.7282 1.0000
0.750 0.4184 0.01268 0.00441 -0.0646 0.7165 1.0000
1.000 0.4426 0.01281 0.00444 -0.0638 0.7051 1.0000
1.250 0.4671 0.01294 0.00448 -0.0630 0.6940 1.0000
1.500 0.4917 0.01307 0.00451 -0.0622 0.6831 1.0000
1.750 0.5161 0.01321 0.00459 -0.0614 0.6714 1.0000
2.000 0.5405 0.01336 0.00469 -0.0606 0.6594 1.0000
2.250 0.5650 0.01351 0.00480 -0.0598 0.6475 1.0000
2.500 0.5896 0.01367 0.00491 -0.0591 0.6358 1.0000
2.750 0.6142 0.01382 0.00505 -0.0583 0.6238 1.0000
3.000 0.6389 0.01399 0.00517 -0.0576 0.6118 1.0000
3.250 0.6635 0.01415 0.00532 -0.0568 0.5991 1.0000
3.500 0.6878 0.01433 0.00550 -0.0560 0.5856 1.0000
3.750 0.7122 0.01451 0.00571 -0.0553 0.5718 1.0000
4.000 0.7365 0.01470 0.00590 -0.0545 0.5574 1.0000
4.250 0.7607 0.01489 0.00610 -0.0537 0.5425 1.0000
4.500 0.7847 0.01510 0.00632 -0.0529 0.5269 1.0000
4.750 0.8084 0.01533 0.00661 -0.0520 0.5098 1.0000
5.000 0.8320 0.01556 0.00687 -0.0511 0.4919 1.0000
5.250 0.8553 0.01582 0.00714 -0.0502 0.4735 1.0000
5.500 0.8783 0.01610 0.00744 -0.0493 0.4541 1.0000
5.750 0.9010 0.01642 0.00781 -0.0483 0.4332 1.0000
6.000 0.9232 0.01677 0.00816 -0.0473 0.4119 1.0000
6.250 0.9449 0.01716 0.00856 -0.0462 0.3891 1.0000
6.500 0.9662 0.01760 0.00901 -0.0451 0.3659 1.0000
6.750 0.9868 0.01810 0.00948 -0.0440 0.3423 1.0000
7.000 1.0070 0.01863 0.01006 -0.0428 0.3183 1.0000
7.250 1.0267 0.01922 0.01065 -0.0416 0.2949 1.0000
7.500 1.0454 0.01988 0.01129 -0.0402 0.2726 1.0000
7.750 1.0640 0.02055 0.01200 -0.0390 0.2494 1.0000
8.000 1.0809 0.02132 0.01274 -0.0375 0.2230 1.0000
8.250 1.0964 0.02218 0.01353 -0.0360 0.1947 1.0000
8.500 1.1109 0.02312 0.01443 -0.0344 0.1661 1.0000
8.750 1.1246 0.02412 0.01536 -0.0327 0.1395 1.0000
9.000 1.1366 0.02526 0.01639 -0.0310 0.1116 1.0000
9.250 1.1461 0.02660 0.01754 -0.0290 0.0813 1.0000
9.500 1.1539 0.02805 0.01888 -0.0269 0.0562 1.0000
10.000 1.1590 0.03140 0.02214 -0.0213 0.0301 1.0000
10.250 1.1608 0.03316 0.02400 -0.0187 0.0262 1.0000
10.500 1.1623 0.03500 0.02599 -0.0165 0.0237 1.0000
10.750 1.1621 0.03707 0.02823 -0.0146 0.0221 1.0000
11.250 1.1580 0.04193 0.03338 -0.0118 0.0202 1.0000
11.500 1.1577 0.04441 0.03606 -0.0109 0.0192 1.0000
11.750 1.1562 0.04717 0.03898 -0.0104 0.0182 1.0000
12.000 1.1549 0.05001 0.04199 -0.0101 0.0178 1.0000
12.250 1.1522 0.05314 0.04525 -0.0102 0.0168 1.0000
12.500 1.1485 0.05652 0.04876 -0.0105 0.0162 1.0000
12.750 1.1451 0.05999 0.05237 -0.0109 0.0160 1.0000
13.000 1.1382 0.06401 0.05651 -0.0117 0.0155 1.0000
13.250 1.1346 0.06780 0.06045 -0.0124 0.0152 1.0000
13.500 1.1315 0.07160 0.06443 -0.0131 0.0151 1.0000
13.750 1.1279 0.07563 0.06863 -0.0141 0.0149 1.0000
14.000 1.1234 0.07992 0.07311 -0.0153 0.0148 1.0000
14.250 1.1181 0.08452 0.07790 -0.0169 0.0147 1.0000
14.500 1.1106 0.08966 0.08326 -0.0188 0.0145 1.0000
14.750 1.1031 0.09502 0.08881 -0.0211 0.0145 1.0000
15.000 1.0930 0.10111 0.09510 -0.0240 0.0144 1.0000
15.250 1.0823 0.10756 0.10174 -0.0274 0.0144 1.0000
15.500 1.0704 0.11456 0.10893 -0.0312 0.0144 1.0000
15.750 1.0566 0.12234 0.11688 -0.0356 0.0144 1.0000
16.000 1.0427 0.13049 0.12520 -0.0404 0.0145 1.0000
16.250 1.0282 0.13923 0.13408 -0.0456 0.0147 1.0000
16.500 1.0117 0.14902 0.14400 -0.0514 0.0148 1.0000
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Polar data table (+)
Polar graphs
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