S4022 (s4022-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4022 (s4022-il) Reynolds number: 500,000 Max Cl/Cd: 129.81 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4022-il-500000.txt Download as CSV file: xf-s4022-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3047 0.10268 0.10047 -0.0537 0.9920 0.0166
-9.250 -0.2935 0.09788 0.09568 -0.0580 0.9894 0.0167
-9.000 -0.2935 0.09077 0.08859 -0.0626 0.9871 0.0173
-8.750 -0.2785 0.08738 0.08520 -0.0660 0.9855 0.0178
-8.500 -0.2619 0.08377 0.08158 -0.0703 0.9841 0.0183
-8.250 -0.2528 0.08030 0.07812 -0.0731 0.9787 0.0190
-8.000 -0.2393 0.07582 0.07365 -0.0784 0.9753 0.0200
-7.750 -0.2244 0.07027 0.06811 -0.0859 0.9726 0.0208
-7.500 -0.2215 0.06494 0.06279 -0.0913 0.9633 0.0213
-5.250 0.0335 0.01680 0.01157 -0.1498 0.9255 0.0248
-5.000 0.0727 0.01608 0.01073 -0.1522 0.9235 0.0241
-4.750 0.1113 0.01439 0.00886 -0.1547 0.9215 0.0242
-4.500 0.1416 0.01364 0.00803 -0.1553 0.9158 0.0239
-4.250 0.1751 0.01200 0.00629 -0.1567 0.9112 0.0233
-4.000 0.2133 0.01104 0.00523 -0.1591 0.9077 0.0233
-3.750 0.2432 0.01045 0.00457 -0.1597 0.9008 0.0236
-3.500 0.2785 0.00974 0.00375 -0.1615 0.8954 0.0249
-3.250 0.3108 0.00931 0.00322 -0.1625 0.8889 0.0270
-3.000 0.3425 0.00905 0.00290 -0.1634 0.8821 0.0296
-2.750 0.3735 0.00887 0.00265 -0.1641 0.8752 0.0336
-2.500 0.4055 0.00817 0.00237 -0.1655 0.8680 0.1622
-2.250 0.4369 0.00737 0.00221 -0.1671 0.8607 0.3826
-2.000 0.4672 0.00709 0.00222 -0.1678 0.8534 0.4974
-1.750 0.4954 0.00706 0.00225 -0.1679 0.8455 0.5473
-1.500 0.5250 0.00708 0.00227 -0.1682 0.8382 0.5893
-1.250 0.5519 0.00710 0.00231 -0.1679 0.8299 0.6094
-1.000 0.5811 0.00717 0.00235 -0.1680 0.8228 0.6356
-0.750 0.6072 0.00721 0.00240 -0.1676 0.8141 0.6523
-0.500 0.6355 0.00726 0.00240 -0.1676 0.8065 0.6630
-0.250 0.6627 0.00730 0.00241 -0.1674 0.7981 0.6730
0.000 0.6897 0.00734 0.00244 -0.1672 0.7897 0.6820
0.250 0.7177 0.00740 0.00245 -0.1671 0.7816 0.6914
0.500 0.7438 0.00743 0.00250 -0.1667 0.7724 0.7002
0.750 0.7709 0.00748 0.00253 -0.1665 0.7637 0.7084
1.000 0.7979 0.00755 0.00257 -0.1663 0.7545 0.7173
1.250 0.8238 0.00758 0.00263 -0.1659 0.7447 0.7253
1.500 0.8504 0.00765 0.00267 -0.1656 0.7351 0.7342
1.750 0.8767 0.00772 0.00274 -0.1652 0.7249 0.7432
2.000 0.9021 0.00778 0.00281 -0.1647 0.7135 0.7523
2.250 0.9278 0.00785 0.00289 -0.1642 0.7020 0.7625
2.500 0.9531 0.00793 0.00297 -0.1637 0.6904 0.7727
2.750 0.9781 0.00801 0.00308 -0.1630 0.6781 0.7834
3.000 1.0026 0.00810 0.00318 -0.1623 0.6645 0.7951
3.250 1.0266 0.00821 0.00329 -0.1615 0.6498 0.8080
3.500 1.0503 0.00831 0.00341 -0.1606 0.6351 0.8224
3.750 1.0733 0.00843 0.00356 -0.1595 0.6198 0.8387
4.000 1.0952 0.00856 0.00370 -0.1583 0.6028 0.8583
4.250 1.1150 0.00868 0.00384 -0.1565 0.5854 0.8831
4.500 1.1300 0.00874 0.00394 -0.1536 0.5682 0.9278
4.750 1.1527 0.00888 0.00406 -0.1526 0.5478 1.0000
5.250 1.1986 0.00947 0.00451 -0.1510 0.5038 1.0000
5.500 1.2202 0.00981 0.00477 -0.1499 0.4799 1.0000
5.750 1.2410 0.01019 0.00505 -0.1486 0.4546 1.0000
6.000 1.2604 0.01062 0.00537 -0.1471 0.4238 1.0000
6.250 1.2783 0.01114 0.00573 -0.1454 0.3886 1.0000
6.500 1.2951 0.01171 0.00614 -0.1434 0.3519 1.0000
6.750 1.3095 0.01237 0.00662 -0.1411 0.3118 1.0000
7.000 1.3230 0.01311 0.00714 -0.1386 0.2706 1.0000
7.250 1.3352 0.01394 0.00774 -0.1360 0.2275 1.0000
7.500 1.3480 0.01477 0.00837 -0.1335 0.1900 1.0000
7.750 1.3611 0.01558 0.00901 -0.1312 0.1584 1.0000
8.000 1.3739 0.01640 0.00969 -0.1288 0.1306 1.0000
8.250 1.3862 0.01726 0.01041 -0.1264 0.1054 1.0000
8.500 1.3988 0.01810 0.01115 -0.1241 0.0852 1.0000
8.750 1.4121 0.01890 0.01189 -0.1219 0.0711 1.0000
9.000 1.4252 0.01970 0.01266 -0.1198 0.0591 1.0000
9.250 1.4372 0.02060 0.01350 -0.1175 0.0465 1.0000
9.500 1.4458 0.02173 0.01455 -0.1148 0.0296 1.0000
9.750 1.4506 0.02319 0.01592 -0.1116 0.0168 1.0000
10.000 1.4585 0.02445 0.01720 -0.1090 0.0135 1.0000
10.250 1.4672 0.02569 0.01854 -0.1065 0.0118 1.0000
10.500 1.4769 0.02687 0.01981 -0.1044 0.0110 1.0000
10.750 1.4851 0.02820 0.02126 -0.1021 0.0103 1.0000
11.000 1.4918 0.02968 0.02284 -0.0999 0.0097 1.0000
11.250 1.4959 0.03143 0.02469 -0.0975 0.0092 1.0000
11.500 1.4957 0.03362 0.02701 -0.0949 0.0087 1.0000
11.750 1.4909 0.03634 0.02988 -0.0921 0.0084 1.0000
12.000 1.4928 0.03855 0.03221 -0.0901 0.0081 1.0000
12.250 1.4980 0.04050 0.03428 -0.0886 0.0079 1.0000
12.500 1.5018 0.04265 0.03655 -0.0872 0.0076 1.0000
12.750 1.5043 0.04503 0.03904 -0.0859 0.0073 1.0000
13.000 1.5061 0.04758 0.04171 -0.0847 0.0070 1.0000
13.250 1.5062 0.05039 0.04466 -0.0836 0.0068 1.0000
13.500 1.5058 0.05340 0.04779 -0.0827 0.0066 1.0000
13.750 1.5049 0.05657 0.05109 -0.0820 0.0065 1.0000
14.000 1.5033 0.05994 0.05461 -0.0815 0.0063 1.0000
14.250 1.5012 0.06349 0.05830 -0.0812 0.0062 1.0000
14.500 1.4983 0.06727 0.06221 -0.0811 0.0061 1.0000
14.750 1.4947 0.07129 0.06636 -0.0812 0.0060 1.0000
15.000 1.4901 0.07556 0.07078 -0.0816 0.0059 1.0000
15.250 1.4844 0.08014 0.07551 -0.0822 0.0058 1.0000
15.500 1.4781 0.08498 0.08050 -0.0831 0.0057 1.0000
15.750 1.4696 0.09029 0.08598 -0.0843 0.0056 1.0000
16.000 1.4616 0.09566 0.09152 -0.0858 0.0055 1.0000
16.250 1.4509 0.10167 0.09772 -0.0877 0.0055 1.0000
16.500 1.4411 0.10770 0.10393 -0.0900 0.0055 1.0000
16.750 1.4301 0.11408 0.11050 -0.0927 0.0054 1.0000
17.000 1.4195 0.12055 0.11715 -0.0958 0.0054 1.0000
17.250 1.4086 0.12728 0.12405 -0.0993 0.0054 1.0000
17.500 1.3945 0.13488 0.13184 -0.1036 0.0054 1.0000
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Polar data table (+)
Polar graphs
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