S3021-095-84 (s3021-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3021-095-84 (s3021-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.44 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3021-il-1000000-n5.txt Download as CSV file: xf-s3021-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4304 0.08447 0.08286 -0.0284 1.0000 0.0065
-9.000 -0.4304 0.08089 0.07930 -0.0300 1.0000 0.0066
-8.750 -0.4321 0.07714 0.07557 -0.0317 1.0000 0.0067
-8.500 -0.4482 0.07123 0.06971 -0.0345 1.0000 0.0065
-8.250 -0.4604 0.06535 0.06386 -0.0397 0.9922 0.0065
-8.000 -0.5121 0.02521 0.02230 -0.0668 0.9528 0.0063
-7.750 -0.4963 0.02205 0.01871 -0.0663 0.9294 0.0063
-7.500 -0.4785 0.02026 0.01659 -0.0651 0.9019 0.0064
-7.250 -0.4584 0.01908 0.01513 -0.0641 0.8771 0.0065
-7.000 -0.4373 0.01797 0.01377 -0.0632 0.8554 0.0067
-6.750 -0.4156 0.01675 0.01227 -0.0624 0.8357 0.0067
-6.500 -0.3921 0.01593 0.01124 -0.0617 0.8181 0.0070
-6.250 -0.3682 0.01512 0.01023 -0.0611 0.8019 0.0072
-6.000 -0.3439 0.01428 0.00919 -0.0605 0.7875 0.0074
-5.750 -0.3190 0.01359 0.00832 -0.0600 0.7735 0.0077
-5.500 -0.2937 0.01296 0.00753 -0.0595 0.7607 0.0079
-5.250 -0.2681 0.01240 0.00683 -0.0591 0.7484 0.0081
-5.000 -0.2423 0.01188 0.00620 -0.0587 0.7368 0.0083
-4.750 -0.2163 0.01141 0.00561 -0.0583 0.7256 0.0084
-4.500 -0.1901 0.01097 0.00506 -0.0580 0.7149 0.0085
-4.250 -0.1637 0.01059 0.00459 -0.0577 0.7048 0.0086
-4.000 -0.1371 0.01027 0.00419 -0.0574 0.6953 0.0088
-3.750 -0.1102 0.01004 0.00389 -0.0571 0.6856 0.0089
-3.500 -0.0841 0.00954 0.00331 -0.0568 0.6767 0.0092
-3.250 -0.0577 0.00914 0.00281 -0.0564 0.6682 0.0094
-3.000 -0.0309 0.00881 0.00241 -0.0562 0.6593 0.0098
-2.750 -0.0038 0.00858 0.00212 -0.0559 0.6510 0.0103
-2.500 0.0235 0.00842 0.00190 -0.0558 0.6423 0.0108
-2.250 0.0510 0.00827 0.00170 -0.0556 0.6337 0.0115
-2.000 0.0784 0.00817 0.00154 -0.0555 0.6253 0.0121
-1.750 0.1061 0.00808 0.00140 -0.0553 0.6162 0.0127
-1.500 0.1337 0.00801 0.00129 -0.0552 0.6073 0.0131
-1.250 0.1613 0.00796 0.00118 -0.0551 0.5977 0.0140
-1.000 0.1889 0.00788 0.00108 -0.0550 0.5877 0.0179
-0.750 0.2158 0.00766 0.00099 -0.0548 0.5781 0.0663
-0.500 0.2426 0.00745 0.00094 -0.0547 0.5683 0.1284
-0.250 0.2692 0.00720 0.00090 -0.0545 0.5583 0.2116
0.000 0.2955 0.00692 0.00089 -0.0544 0.5483 0.3092
0.250 0.3215 0.00664 0.00089 -0.0542 0.5387 0.4206
0.500 0.3464 0.00624 0.00091 -0.0538 0.5284 0.5742
0.750 0.3706 0.00588 0.00095 -0.0531 0.5180 0.7130
1.000 0.3940 0.00563 0.00099 -0.0520 0.5074 0.8187
1.250 0.4170 0.00547 0.00108 -0.0506 0.4962 0.9229
1.500 0.4510 0.00555 0.00114 -0.0518 0.4830 0.9624
1.750 0.4849 0.00566 0.00118 -0.0531 0.4689 0.9762
2.000 0.5179 0.00578 0.00123 -0.0542 0.4540 0.9850
2.250 0.5540 0.00590 0.00128 -0.0561 0.4379 0.9904
2.500 0.5878 0.00605 0.00134 -0.0575 0.4203 0.9949
2.750 0.6246 0.00621 0.00142 -0.0596 0.4009 0.9989
3.000 0.6535 0.00636 0.00150 -0.0599 0.3839 1.0000
3.250 0.6780 0.00653 0.00160 -0.0593 0.3671 1.0000
3.500 0.7023 0.00671 0.00171 -0.0586 0.3487 1.0000
3.750 0.7264 0.00692 0.00184 -0.0579 0.3294 1.0000
4.000 0.7507 0.00712 0.00197 -0.0572 0.3111 1.0000
4.250 0.7747 0.00735 0.00211 -0.0565 0.2911 1.0000
4.500 0.7985 0.00760 0.00228 -0.0558 0.2715 1.0000
4.750 0.8225 0.00785 0.00246 -0.0551 0.2519 1.0000
5.000 0.8456 0.00819 0.00267 -0.0543 0.2251 1.0000
5.250 0.8673 0.00866 0.00294 -0.0533 0.1863 1.0000
5.500 0.8905 0.00902 0.00318 -0.0526 0.1628 1.0000
5.750 0.9128 0.00947 0.00349 -0.0517 0.1325 1.0000
6.000 0.9351 0.00994 0.00381 -0.0509 0.1050 1.0000
6.250 0.9573 0.01042 0.00416 -0.0500 0.0800 1.0000
6.500 0.9792 0.01092 0.00454 -0.0492 0.0569 1.0000
6.750 0.9988 0.01166 0.00508 -0.0480 0.0253 1.0000
7.000 1.0192 0.01233 0.00565 -0.0468 0.0071 1.0000
7.250 1.0427 0.01267 0.00601 -0.0462 0.0062 1.0000
7.500 1.0660 0.01303 0.00639 -0.0455 0.0055 1.0000
7.750 1.0889 0.01342 0.00683 -0.0448 0.0049 1.0000
8.000 1.1115 0.01383 0.00728 -0.0440 0.0046 1.0000
8.250 1.1341 0.01421 0.00772 -0.0433 0.0045 1.0000
8.500 1.1561 0.01464 0.00819 -0.0424 0.0043 1.0000
8.750 1.1776 0.01509 0.00869 -0.0416 0.0041 1.0000
9.000 1.1985 0.01559 0.00924 -0.0406 0.0039 1.0000
9.250 1.2191 0.01607 0.00977 -0.0396 0.0037 1.0000
9.500 1.2389 0.01661 0.01035 -0.0385 0.0035 1.0000
9.750 1.2573 0.01722 0.01103 -0.0372 0.0033 1.0000
10.000 1.2751 0.01784 0.01171 -0.0359 0.0033 1.0000
10.250 1.2917 0.01851 0.01244 -0.0344 0.0032 1.0000
10.500 1.3065 0.01924 0.01324 -0.0326 0.0030 1.0000
10.750 1.3169 0.02004 0.01412 -0.0301 0.0030 1.0000
11.000 1.3225 0.02103 0.01520 -0.0270 0.0029 1.0000
11.250 1.3275 0.02210 0.01636 -0.0240 0.0028 1.0000
11.500 1.3295 0.02341 0.01779 -0.0210 0.0027 1.0000
11.750 1.3313 0.02483 0.01932 -0.0183 0.0027 1.0000
12.000 1.3397 0.02591 0.02047 -0.0166 0.0027 1.0000
12.250 1.3425 0.02747 0.02214 -0.0147 0.0027 1.0000
12.500 1.3486 0.02889 0.02364 -0.0133 0.0026 1.0000
12.750 1.3538 0.03047 0.02531 -0.0121 0.0026 1.0000
13.000 1.3561 0.03242 0.02736 -0.0110 0.0026 1.0000
13.250 1.3580 0.03454 0.02958 -0.0102 0.0025 1.0000
13.500 1.3615 0.03660 0.03173 -0.0097 0.0025 1.0000
13.750 1.3591 0.03939 0.03464 -0.0093 0.0025 1.0000
14.000 1.3553 0.04249 0.03786 -0.0092 0.0025 1.0000
14.250 1.3567 0.04513 0.04059 -0.0094 0.0024 1.0000
14.500 1.3530 0.04845 0.04403 -0.0097 0.0024 1.0000
14.750 1.3458 0.05239 0.04809 -0.0105 0.0024 1.0000
15.000 1.3407 0.05621 0.05203 -0.0114 0.0024 1.0000
15.250 1.3355 0.06021 0.05616 -0.0126 0.0023 1.0000
15.500 1.3278 0.06478 0.06084 -0.0142 0.0023 1.0000
15.750 1.3191 0.06971 0.06589 -0.0160 0.0023 1.0000
16.000 1.3088 0.07507 0.07138 -0.0183 0.0023 1.0000
16.250 1.3001 0.08043 0.07686 -0.0207 0.0023 1.0000
16.500 1.2919 0.08587 0.08241 -0.0232 0.0022 1.0000
16.750 1.2784 0.09241 0.08908 -0.0263 0.0022 1.0000
17.000 1.2641 0.09929 0.09608 -0.0297 0.0023 1.0000
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Polar data table (+)
Polar graphs
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