S4022 (s4022-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4022 (s4022-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.12 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4022-il-1000000-n5.txt Download as CSV file: xf-s4022-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4022
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2467 0.08961 0.08787 -0.0792 0.9848 0.0054
-9.750 -0.2500 0.08286 0.08113 -0.0832 0.9823 0.0060
-9.250 -0.3717 0.03330 0.03118 -0.1286 0.9499 0.0063
-9.000 -0.3607 0.02614 0.02345 -0.1365 0.9419 0.0065
-8.750 -0.3328 0.02315 0.02011 -0.1405 0.9376 0.0066
-8.500 -0.2986 0.02101 0.01769 -0.1445 0.9350 0.0067
-8.250 -0.2690 0.01752 0.01374 -0.1484 0.9295 0.0071
-8.000 -0.2321 0.01651 0.01261 -0.1515 0.9253 0.0074
-7.750 -0.1935 0.01580 0.01179 -0.1547 0.9214 0.0077
-7.500 -0.1605 0.01504 0.01091 -0.1566 0.9148 0.0080
-7.250 -0.1262 0.01429 0.01000 -0.1587 0.9080 0.0083
-7.000 -0.0959 0.01350 0.00906 -0.1598 0.8995 0.0085
-6.750 -0.0653 0.01287 0.00829 -0.1609 0.8913 0.0089
-6.500 -0.0371 0.01217 0.00746 -0.1614 0.8820 0.0091
-6.250 -0.0092 0.01160 0.00676 -0.1618 0.8732 0.0093
-6.000 0.0185 0.01106 0.00610 -0.1621 0.8644 0.0096
-5.750 0.0455 0.01055 0.00548 -0.1622 0.8555 0.0097
-5.500 0.0727 0.01012 0.00495 -0.1623 0.8473 0.0099
-5.250 0.1000 0.00981 0.00455 -0.1624 0.8388 0.0103
-5.000 0.1273 0.00950 0.00417 -0.1624 0.8308 0.0105
-4.750 0.1546 0.00915 0.00373 -0.1625 0.8229 0.0106
-4.500 0.1822 0.00884 0.00335 -0.1626 0.8149 0.0108
-4.250 0.2098 0.00861 0.00304 -0.1627 0.8073 0.0109
-4.000 0.2374 0.00842 0.00280 -0.1628 0.7992 0.0111
-3.750 0.2655 0.00804 0.00231 -0.1630 0.7916 0.0120
-3.500 0.2932 0.00785 0.00205 -0.1631 0.7835 0.0130
-3.250 0.3210 0.00773 0.00188 -0.1632 0.7757 0.0136
-3.000 0.3484 0.00764 0.00173 -0.1631 0.7676 0.0142
-2.750 0.3762 0.00756 0.00161 -0.1632 0.7595 0.0147
-2.500 0.4037 0.00750 0.00150 -0.1631 0.7517 0.0153
-2.250 0.4313 0.00745 0.00140 -0.1631 0.7435 0.0162
-2.000 0.4588 0.00741 0.00132 -0.1631 0.7357 0.0181
-1.750 0.4867 0.00728 0.00125 -0.1632 0.7273 0.0471
-1.500 0.5153 0.00701 0.00118 -0.1637 0.7191 0.1288
-1.250 0.5439 0.00665 0.00113 -0.1643 0.7105 0.2529
-1.000 0.5725 0.00640 0.00112 -0.1648 0.7016 0.3495
-0.750 0.6008 0.00620 0.00114 -0.1652 0.6927 0.4454
-0.500 0.6282 0.00614 0.00119 -0.1652 0.6828 0.5068
-0.250 0.6557 0.00613 0.00125 -0.1652 0.6727 0.5518
0.000 0.6827 0.00618 0.00129 -0.1650 0.6623 0.5686
0.250 0.7094 0.00626 0.00133 -0.1648 0.6513 0.5788
0.500 0.7359 0.00635 0.00138 -0.1646 0.6395 0.5884
0.750 0.7625 0.00643 0.00144 -0.1643 0.6270 0.5975
1.000 0.7888 0.00653 0.00151 -0.1640 0.6135 0.6057
1.250 0.8148 0.00665 0.00158 -0.1637 0.5992 0.6137
1.500 0.8407 0.00677 0.00166 -0.1633 0.5843 0.6207
1.750 0.8666 0.00690 0.00175 -0.1630 0.5699 0.6278
2.000 0.8924 0.00704 0.00185 -0.1626 0.5553 0.6345
2.250 0.9179 0.00719 0.00195 -0.1622 0.5386 0.6419
2.500 0.9430 0.00737 0.00207 -0.1617 0.5187 0.6490
2.750 0.9679 0.00756 0.00222 -0.1611 0.4999 0.6567
3.000 0.9929 0.00775 0.00235 -0.1606 0.4816 0.6640
3.250 1.0176 0.00796 0.00250 -0.1601 0.4613 0.6718
3.500 1.0415 0.00821 0.00268 -0.1594 0.4380 0.6794
3.750 1.0652 0.00849 0.00287 -0.1587 0.4136 0.6877
4.000 1.0885 0.00878 0.00309 -0.1579 0.3875 0.6958
4.250 1.1114 0.00911 0.00332 -0.1570 0.3597 0.7048
4.500 1.1339 0.00946 0.00357 -0.1561 0.3315 0.7142
4.750 1.1557 0.00984 0.00385 -0.1551 0.3017 0.7240
5.000 1.1768 0.01028 0.00416 -0.1540 0.2697 0.7347
5.250 1.1965 0.01081 0.00454 -0.1526 0.2316 0.7463
5.500 1.2144 0.01145 0.00497 -0.1509 0.1885 0.7587
5.750 1.2341 0.01193 0.00535 -0.1496 0.1598 0.7728
6.000 1.2546 0.01235 0.00572 -0.1483 0.1380 0.7886
6.250 1.2738 0.01283 0.00612 -0.1469 0.1151 0.8060
6.500 1.2916 0.01330 0.00653 -0.1451 0.0947 0.8272
6.750 1.3078 0.01376 0.00698 -0.1430 0.0748 0.8551
7.000 1.3222 0.01413 0.00738 -0.1405 0.0613 0.8993
7.250 1.3353 0.01439 0.00770 -0.1376 0.0524 1.0000
7.500 1.3536 0.01486 0.00813 -0.1360 0.0439 1.0000
7.750 1.3713 0.01536 0.00859 -0.1344 0.0356 1.0000
8.000 1.3879 0.01591 0.00909 -0.1326 0.0270 1.0000
8.250 1.4032 0.01654 0.00967 -0.1305 0.0184 1.0000
8.500 1.4163 0.01732 0.01041 -0.1282 0.0088 1.0000
8.750 1.4324 0.01789 0.01099 -0.1263 0.0070 1.0000
9.000 1.4481 0.01850 0.01163 -0.1245 0.0058 1.0000
9.250 1.4640 0.01910 0.01227 -0.1227 0.0051 1.0000
9.500 1.4798 0.01969 0.01291 -0.1209 0.0048 1.0000
9.750 1.4951 0.02033 0.01360 -0.1191 0.0045 1.0000
10.000 1.5093 0.02103 0.01435 -0.1172 0.0042 1.0000
10.250 1.5228 0.02180 0.01519 -0.1153 0.0039 1.0000
10.500 1.5354 0.02265 0.01608 -0.1132 0.0036 1.0000
10.750 1.5464 0.02362 0.01712 -0.1111 0.0033 1.0000
11.000 1.5557 0.02475 0.01833 -0.1088 0.0031 1.0000
11.250 1.5682 0.02565 0.01930 -0.1070 0.0030 1.0000
11.500 1.5799 0.02664 0.02034 -0.1052 0.0029 1.0000
11.750 1.5906 0.02771 0.02149 -0.1034 0.0028 1.0000
12.000 1.6005 0.02888 0.02273 -0.1015 0.0028 1.0000
12.250 1.6099 0.03012 0.02405 -0.0997 0.0027 1.0000
12.500 1.6186 0.03147 0.02547 -0.0980 0.0026 1.0000
12.750 1.6264 0.03292 0.02702 -0.0963 0.0025 1.0000
13.000 1.6337 0.03446 0.02864 -0.0946 0.0024 1.0000
13.250 1.6402 0.03612 0.03038 -0.0930 0.0023 1.0000
13.500 1.6465 0.03785 0.03219 -0.0916 0.0022 1.0000
13.750 1.6517 0.03973 0.03416 -0.0902 0.0021 1.0000
14.000 1.6562 0.04175 0.03626 -0.0889 0.0020 1.0000
14.250 1.6598 0.04393 0.03854 -0.0877 0.0020 1.0000
14.500 1.6624 0.04631 0.04101 -0.0866 0.0019 1.0000
14.750 1.6638 0.04889 0.04368 -0.0857 0.0018 1.0000
15.000 1.6635 0.05178 0.04669 -0.0849 0.0018 1.0000
15.250 1.6603 0.05515 0.05018 -0.0842 0.0017 1.0000
15.500 1.6548 0.05897 0.05413 -0.0838 0.0016 1.0000
15.750 1.6462 0.06337 0.05868 -0.0838 0.0016 1.0000
16.000 1.6441 0.06703 0.06246 -0.0839 0.0016 1.0000
16.250 1.6412 0.07094 0.06649 -0.0844 0.0016 1.0000
16.500 1.6365 0.07525 0.07093 -0.0851 0.0015 1.0000
16.750 1.6320 0.07967 0.07547 -0.0860 0.0015 1.0000
17.000 1.6253 0.08459 0.08051 -0.0872 0.0015 1.0000
17.250 1.6177 0.08983 0.08589 -0.0888 0.0015 1.0000
17.500 1.6099 0.09523 0.09142 -0.0906 0.0015 1.0000
17.750 1.6002 0.10111 0.09743 -0.0929 0.0015 1.0000
18.000 1.5891 0.10742 0.10388 -0.0955 0.0015 1.0000
18.250 1.5771 0.11405 0.11065 -0.0985 0.0015 1.0000
18.500 1.5663 0.12057 0.11730 -0.1016 0.0014 1.0000
18.750 1.5522 0.12788 0.12476 -0.1054 0.0014 1.0000
19.000 1.5405 0.13480 0.13181 -0.1091 0.0014 1.0000
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