S4022 (s4022-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4022 (s4022-il) Reynolds number: 1,000,000 Max Cl/Cd: 148.3 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4022-il-1000000.txt Download as CSV file: xf-s4022-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2255 0.08341 0.08176 -0.0790 0.9851 0.0111
-8.750 -0.2136 0.07772 0.07607 -0.0849 0.9841 0.0111
-8.500 -0.2108 0.07283 0.07119 -0.0879 0.9782 0.0111
-8.250 -0.2255 0.05734 0.05574 -0.1041 0.9731 0.0116
-8.000 -0.2276 0.03912 0.03718 -0.1306 0.9613 0.0117
-7.750 -0.2175 0.03443 0.03227 -0.1351 0.9532 0.0120
-7.500 -0.1912 0.03204 0.02974 -0.1390 0.9504 0.0123
-7.250 -0.1605 0.03013 0.02770 -0.1430 0.9485 0.0130
-7.000 -0.1358 0.02724 0.02458 -0.1456 0.9426 0.0138
-6.750 -0.1031 0.02516 0.02227 -0.1483 0.9385 0.0157
-6.500 -0.0623 0.02485 0.02172 -0.1514 0.9363 0.0166
-6.250 -0.0309 0.01772 0.01391 -0.1572 0.9310 0.0180
-6.000 0.0018 0.01643 0.01252 -0.1592 0.9252 0.0190
-5.750 0.0406 0.01414 0.00986 -0.1614 0.9211 0.0160
-5.500 0.0700 0.01303 0.00859 -0.1621 0.9132 0.0162
-5.250 0.1042 0.01191 0.00729 -0.1638 0.9072 0.0162
-5.000 0.1320 0.01098 0.00624 -0.1640 0.8985 0.0161
-4.750 0.1626 0.01021 0.00536 -0.1648 0.8912 0.0161
-4.500 0.1909 0.00979 0.00486 -0.1650 0.8826 0.0164
-4.250 0.2193 0.00914 0.00412 -0.1654 0.8746 0.0163
-4.000 0.2483 0.00860 0.00348 -0.1658 0.8665 0.0163
-3.750 0.2763 0.00821 0.00302 -0.1659 0.8581 0.0164
-3.500 0.3055 0.00781 0.00249 -0.1663 0.8504 0.0172
-3.250 0.3336 0.00748 0.00206 -0.1665 0.8419 0.0188
-3.000 0.3619 0.00734 0.00185 -0.1666 0.8342 0.0202
-2.750 0.3898 0.00723 0.00169 -0.1666 0.8261 0.0213
-2.500 0.4177 0.00715 0.00155 -0.1667 0.8184 0.0225
-2.250 0.4455 0.00709 0.00144 -0.1667 0.8106 0.0272
-2.000 0.4747 0.00655 0.00130 -0.1674 0.8030 0.1639
-1.750 0.5040 0.00601 0.00122 -0.1684 0.7955 0.3379
-1.500 0.5326 0.00569 0.00122 -0.1689 0.7877 0.4604
-1.250 0.5605 0.00561 0.00126 -0.1690 0.7801 0.5279
-1.000 0.5880 0.00561 0.00129 -0.1689 0.7719 0.5564
-0.750 0.6154 0.00563 0.00131 -0.1688 0.7641 0.5791
-0.500 0.6427 0.00567 0.00135 -0.1687 0.7556 0.5990
-0.250 0.6699 0.00571 0.00139 -0.1685 0.7473 0.6180
0.000 0.6968 0.00577 0.00143 -0.1683 0.7387 0.6279
0.250 0.7240 0.00581 0.00146 -0.1681 0.7295 0.6363
0.500 0.7509 0.00587 0.00149 -0.1679 0.7204 0.6448
1.250 0.8306 0.00607 0.00164 -0.1671 0.6889 0.6686
1.500 0.8569 0.00616 0.00169 -0.1668 0.6774 0.6763
1.750 0.8829 0.00624 0.00177 -0.1664 0.6657 0.6839
2.000 0.9088 0.00634 0.00184 -0.1660 0.6532 0.6918
2.250 0.9344 0.00645 0.00193 -0.1656 0.6389 0.7002
2.500 0.9597 0.00656 0.00202 -0.1651 0.6234 0.7086
2.750 0.9851 0.00670 0.00213 -0.1646 0.6081 0.7181
3.000 1.0103 0.00682 0.00224 -0.1641 0.5926 0.7275
3.250 1.0351 0.00698 0.00237 -0.1635 0.5756 0.7375
3.500 1.0594 0.00716 0.00250 -0.1629 0.5569 0.7484
3.750 1.0837 0.00734 0.00267 -0.1622 0.5383 0.7604
4.000 1.1076 0.00754 0.00283 -0.1615 0.5171 0.7732
4.250 1.1311 0.00776 0.00301 -0.1606 0.4959 0.7875
4.500 1.1543 0.00799 0.00320 -0.1598 0.4729 0.8035
4.750 1.1769 0.00824 0.00342 -0.1588 0.4489 0.8215
5.000 1.1985 0.00853 0.00366 -0.1577 0.4216 0.8432
5.250 1.2178 0.00890 0.00395 -0.1561 0.3867 0.8702
5.500 1.2337 0.00925 0.00423 -0.1537 0.3507 0.9133
5.750 1.2501 0.00957 0.00447 -0.1514 0.3186 1.0000
6.000 1.2698 0.01011 0.00483 -0.1501 0.2824 1.0000
6.250 1.2880 0.01074 0.00525 -0.1485 0.2419 1.0000
6.500 1.3055 0.01140 0.00569 -0.1468 0.2032 1.0000
6.750 1.3210 0.01210 0.00619 -0.1447 0.1641 1.0000
7.000 1.3369 0.01273 0.00665 -0.1427 0.1353 1.0000
7.250 1.3536 0.01330 0.00711 -0.1407 0.1123 1.0000
7.500 1.3696 0.01388 0.00758 -0.1387 0.0928 1.0000
7.750 1.3862 0.01444 0.00806 -0.1369 0.0767 1.0000
8.000 1.4017 0.01507 0.00859 -0.1348 0.0607 1.0000
8.250 1.4177 0.01565 0.00913 -0.1329 0.0492 1.0000
8.500 1.4324 0.01630 0.00972 -0.1308 0.0375 1.0000
8.750 1.4453 0.01709 0.01042 -0.1284 0.0234 1.0000
9.000 1.4537 0.01815 0.01137 -0.1253 0.0107 1.0000
9.250 1.4668 0.01894 0.01219 -0.1229 0.0082 1.0000
9.500 1.4818 0.01959 0.01291 -0.1210 0.0076 1.0000
9.750 1.4958 0.02032 0.01370 -0.1190 0.0071 1.0000
10.000 1.5085 0.02114 0.01457 -0.1168 0.0065 1.0000
10.250 1.5195 0.02210 0.01561 -0.1145 0.0060 1.0000
10.500 1.5278 0.02327 0.01688 -0.1118 0.0055 1.0000
10.750 1.5346 0.02459 0.01831 -0.1091 0.0052 1.0000
11.000 1.5459 0.02558 0.01937 -0.1071 0.0051 1.0000
11.250 1.5558 0.02670 0.02057 -0.1050 0.0049 1.0000
11.500 1.5650 0.02791 0.02185 -0.1030 0.0047 1.0000
11.750 1.5727 0.02926 0.02329 -0.1009 0.0045 1.0000
12.000 1.5795 0.03075 0.02487 -0.0988 0.0044 1.0000
12.250 1.5856 0.03233 0.02654 -0.0968 0.0042 1.0000
12.500 1.5907 0.03405 0.02835 -0.0949 0.0040 1.0000
12.750 1.5948 0.03593 0.03032 -0.0931 0.0039 1.0000
13.000 1.5978 0.03798 0.03249 -0.0913 0.0037 1.0000
13.250 1.5990 0.04028 0.03489 -0.0896 0.0036 1.0000
13.500 1.5975 0.04296 0.03768 -0.0880 0.0035 1.0000
13.750 1.5938 0.04603 0.04087 -0.0865 0.0034 1.0000
14.000 1.5856 0.04975 0.04474 -0.0852 0.0033 1.0000
14.250 1.5738 0.05414 0.04930 -0.0841 0.0032 1.0000
14.500 1.5597 0.05909 0.05443 -0.0834 0.0031 1.0000
14.750 1.5499 0.06371 0.05921 -0.0831 0.0031 1.0000
15.000 1.5504 0.06706 0.06268 -0.0833 0.0030 1.0000
15.250 1.5497 0.07069 0.06641 -0.0836 0.0030 1.0000
15.500 1.5475 0.07465 0.07050 -0.0842 0.0030 1.0000
15.750 1.5445 0.07886 0.07484 -0.0850 0.0029 1.0000
16.000 1.5385 0.08371 0.07982 -0.0861 0.0029 1.0000
16.250 1.5332 0.08859 0.08483 -0.0875 0.0028 1.0000
16.500 1.5246 0.09417 0.09056 -0.0893 0.0028 1.0000
16.750 1.5165 0.09981 0.09633 -0.0914 0.0028 1.0000
17.000 1.5074 0.10579 0.10245 -0.0938 0.0027 1.0000
17.250 1.4968 0.11221 0.10902 -0.0966 0.0027 1.0000
17.500 1.4873 0.11859 0.11553 -0.0996 0.0027 1.0000
17.750 1.4767 0.12526 0.12235 -0.1030 0.0026 1.0000
18.000 1.4650 0.13230 0.12953 -0.1067 0.0026 1.0000
18.250 1.4531 0.13952 0.13689 -0.1108 0.0026 1.0000
18.500 1.4425 0.14665 0.14416 -0.1150 0.0026 1.0000
18.750 1.4303 0.15423 0.15187 -0.1197 0.0026 1.0000
19.000 1.4191 0.16172 0.15949 -0.1245 0.0026 1.0000
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Polar data table (+)
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