S4022 (s4022-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4022 (s4022-il) Reynolds number: 500,000 Max Cl/Cd: 113.52 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4022-il-500000-n5.txt Download as CSV file: xf-s4022-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2431 0.08206 0.07971 -0.0781 0.9760 0.0088
-8.750 -0.2357 0.07652 0.07418 -0.0834 0.9731 0.0089
-8.500 -0.2360 0.07159 0.06928 -0.0866 0.9655 0.0089
-8.250 -0.2319 0.06471 0.06241 -0.0939 0.9607 0.0091
-8.000 -0.2385 0.05723 0.05495 -0.1008 0.9493 0.0091
-7.750 -0.2406 0.03802 0.03529 -0.1267 0.9357 0.0089
-7.500 -0.2264 0.03023 0.02697 -0.1331 0.9274 0.0094
-7.250 -0.1978 0.02492 0.02106 -0.1382 0.9232 0.0100
-7.000 -0.1624 0.02142 0.01704 -0.1425 0.9207 0.0104
-6.750 -0.1338 0.01964 0.01494 -0.1439 0.9145 0.0107
-6.500 -0.0976 0.01823 0.01324 -0.1466 0.9108 0.0110
-6.250 -0.0600 0.01649 0.01119 -0.1496 0.9075 0.0113
-6.000 -0.0297 0.01482 0.00930 -0.1510 0.9013 0.0117
-5.750 0.0044 0.01377 0.00811 -0.1529 0.8959 0.0120
-5.500 0.0376 0.01310 0.00735 -0.1545 0.8902 0.0127
-5.250 0.0690 0.01250 0.00666 -0.1556 0.8833 0.0133
-5.000 0.1012 0.01182 0.00587 -0.1568 0.8769 0.0135
-4.750 0.1312 0.01124 0.00520 -0.1575 0.8695 0.0137
-4.500 0.1621 0.01074 0.00460 -0.1584 0.8626 0.0140
-4.250 0.1918 0.01033 0.00409 -0.1590 0.8549 0.0144
-4.000 0.2217 0.00997 0.00365 -0.1596 0.8477 0.0151
-3.750 0.2511 0.00969 0.00329 -0.1601 0.8400 0.0157
-3.500 0.2801 0.00948 0.00299 -0.1604 0.8326 0.0164
-3.250 0.3092 0.00928 0.00270 -0.1608 0.8249 0.0170
-3.000 0.3377 0.00910 0.00244 -0.1610 0.8172 0.0182
-2.750 0.3666 0.00896 0.00224 -0.1613 0.8097 0.0207
-2.500 0.3945 0.00885 0.00209 -0.1613 0.8016 0.0233
-2.250 0.4233 0.00865 0.00193 -0.1617 0.7941 0.0540
-2.000 0.4521 0.00826 0.00181 -0.1623 0.7858 0.1468
-1.750 0.4811 0.00791 0.00172 -0.1630 0.7781 0.2497
-1.500 0.5106 0.00739 0.00170 -0.1640 0.7699 0.4252
-1.250 0.5387 0.00727 0.00174 -0.1641 0.7620 0.4969
-1.000 0.5663 0.00725 0.00180 -0.1641 0.7538 0.5522
-0.750 0.5937 0.00727 0.00185 -0.1640 0.7454 0.5831
-0.500 0.6210 0.00732 0.00187 -0.1639 0.7372 0.5960
-0.250 0.6481 0.00737 0.00189 -0.1637 0.7281 0.6068
0.000 0.6752 0.00743 0.00192 -0.1635 0.7193 0.6173
0.250 0.7020 0.00749 0.00196 -0.1633 0.7101 0.6266
0.500 0.7288 0.00755 0.00200 -0.1631 0.7001 0.6354
0.750 0.7554 0.00763 0.00205 -0.1628 0.6901 0.6439
1.000 0.7818 0.00771 0.00211 -0.1625 0.6798 0.6514
1.250 0.8080 0.00780 0.00217 -0.1622 0.6687 0.6594
1.500 0.8340 0.00789 0.00225 -0.1618 0.6568 0.6669
2.000 0.8853 0.00811 0.00243 -0.1609 0.6306 0.6830
2.250 0.9105 0.00824 0.00253 -0.1604 0.6164 0.6913
2.500 0.9355 0.00838 0.00265 -0.1598 0.6020 0.6997
2.750 0.9602 0.00853 0.00279 -0.1592 0.5871 0.7080
3.000 0.9844 0.00871 0.00293 -0.1585 0.5703 0.7172
3.250 1.0082 0.00889 0.00308 -0.1577 0.5517 0.7263
3.500 1.0319 0.00909 0.00325 -0.1569 0.5333 0.7361
4.000 1.0781 0.00954 0.00366 -0.1551 0.4941 0.7581
4.250 1.1000 0.00982 0.00388 -0.1540 0.4707 0.7703
4.500 1.1216 0.01011 0.00412 -0.1528 0.4459 0.7835
4.750 1.1425 0.01044 0.00439 -0.1515 0.4198 0.7985
5.000 1.1626 0.01079 0.00468 -0.1501 0.3926 0.8159
5.250 1.1819 0.01116 0.00501 -0.1485 0.3647 0.8356
5.750 1.2136 0.01191 0.00567 -0.1439 0.3049 0.9013
6.000 1.2280 0.01232 0.00598 -0.1414 0.2736 1.0000
6.250 1.2442 0.01298 0.00645 -0.1394 0.2356 1.0000
6.500 1.2599 0.01367 0.00695 -0.1374 0.2008 1.0000
6.750 1.2753 0.01437 0.00747 -0.1354 0.1678 1.0000
7.000 1.2910 0.01504 0.00803 -0.1334 0.1406 1.0000
7.250 1.3064 0.01574 0.00860 -0.1315 0.1157 1.0000
7.500 1.3210 0.01647 0.00920 -0.1294 0.0934 1.0000
7.750 1.3372 0.01709 0.00977 -0.1276 0.0790 1.0000
8.000 1.3531 0.01774 0.01037 -0.1257 0.0664 1.0000
8.250 1.3682 0.01842 0.01101 -0.1238 0.0550 1.0000
8.500 1.3823 0.01917 0.01172 -0.1218 0.0435 1.0000
8.750 1.3965 0.01991 0.01244 -0.1198 0.0350 1.0000
9.000 1.4103 0.02069 0.01320 -0.1178 0.0272 1.0000
9.250 1.4218 0.02162 0.01411 -0.1155 0.0182 1.0000
9.500 1.4322 0.02266 0.01512 -0.1132 0.0113 1.0000
9.750 1.4433 0.02366 0.01615 -0.1110 0.0088 1.0000
10.000 1.4556 0.02460 0.01716 -0.1090 0.0078 1.0000
10.250 1.4674 0.02558 0.01822 -0.1070 0.0071 1.0000
10.500 1.4781 0.02667 0.01939 -0.1050 0.0065 1.0000
10.750 1.4874 0.02790 0.02072 -0.1029 0.0059 1.0000
11.000 1.4954 0.02928 0.02220 -0.1008 0.0054 1.0000
11.250 1.5028 0.03074 0.02377 -0.0987 0.0052 1.0000
11.500 1.5117 0.03211 0.02524 -0.0970 0.0050 1.0000
11.750 1.5192 0.03363 0.02687 -0.0952 0.0049 1.0000
12.000 1.5257 0.03528 0.02863 -0.0934 0.0047 1.0000
12.250 1.5317 0.03704 0.03050 -0.0918 0.0045 1.0000
12.500 1.5370 0.03892 0.03248 -0.0902 0.0043 1.0000
12.750 1.5415 0.04092 0.03460 -0.0888 0.0042 1.0000
13.000 1.5453 0.04306 0.03684 -0.0874 0.0040 1.0000
13.250 1.5483 0.04536 0.03925 -0.0862 0.0038 1.0000
13.500 1.5505 0.04782 0.04185 -0.0852 0.0036 1.0000
13.750 1.5509 0.05058 0.04473 -0.0843 0.0035 1.0000
14.000 1.5486 0.05379 0.04806 -0.0835 0.0034 1.0000
14.250 1.5435 0.05748 0.05189 -0.0829 0.0032 1.0000
14.500 1.5357 0.06170 0.05626 -0.0826 0.0031 1.0000
14.750 1.5289 0.06596 0.06067 -0.0827 0.0031 1.0000
15.000 1.5266 0.06977 0.06462 -0.0829 0.0030 1.0000
15.250 1.5235 0.07381 0.06879 -0.0834 0.0030 1.0000
15.500 1.5193 0.07816 0.07329 -0.0842 0.0029 1.0000
15.750 1.5145 0.08274 0.07801 -0.0853 0.0029 1.0000
16.000 1.5081 0.08772 0.08315 -0.0866 0.0029 1.0000
16.250 1.5016 0.09288 0.08845 -0.0882 0.0028 1.0000
16.500 1.4936 0.09843 0.09416 -0.0902 0.0028 1.0000
16.750 1.4856 0.10414 0.10002 -0.0924 0.0028 1.0000
17.000 1.4770 0.11007 0.10610 -0.0949 0.0027 1.0000
17.250 1.4678 0.11627 0.11245 -0.0977 0.0027 1.0000
17.500 1.4588 0.12254 0.11888 -0.1007 0.0027 1.0000
17.750 1.4492 0.12903 0.12552 -0.1041 0.0026 1.0000
18.000 1.4395 0.13567 0.13231 -0.1077 0.0026 1.0000
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Polar data table (+)
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