S4022 (s4022-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S4022 (s4022-il) Reynolds number: 200,000 Max Cl/Cd: 93.42 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4022-il-200000.txt Download as CSV file: xf-s4022-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3589 0.11288 0.10959 -0.0327 1.0000 0.0389
-9.000 -0.3644 0.11075 0.10751 -0.0316 1.0000 0.0400
-8.750 -0.3713 0.10866 0.10548 -0.0305 1.0000 0.0411
-8.500 -0.2724 0.09072 0.08777 -0.0513 0.9850 0.0467
-8.250 -0.2468 0.08829 0.08531 -0.0501 0.9827 0.0501
-8.000 -0.2399 0.08438 0.08141 -0.0523 0.9780 0.0526
-7.750 -0.2334 0.07951 0.07654 -0.0565 0.9745 0.0551
-7.500 -0.3666 0.08639 0.08338 -0.0581 0.9792 0.0462
-7.250 -0.3391 0.08583 0.08279 -0.0505 0.9801 0.0496
-7.000 -0.3275 0.08231 0.07927 -0.0546 0.9744 0.0521
-6.750 -0.3171 0.07700 0.07398 -0.0624 0.9659 0.0553
-6.500 -0.2928 0.06467 0.06106 -0.0928 0.9517 0.0586
-6.250 -0.2784 0.05829 0.05493 -0.0933 0.9497 0.0608
-6.000 -0.2501 0.05535 0.05199 -0.0962 0.9476 0.0637
-5.750 -0.2329 0.05115 0.04757 -0.1004 0.9388 0.0685
-5.500 -0.1980 0.04495 0.04098 -0.1091 0.9356 0.0754
-5.250 -0.1727 0.04232 0.03820 -0.1112 0.9302 0.0807
-5.000 -0.1409 0.03853 0.03411 -0.1155 0.9255 0.0906
-4.750 -0.0855 0.03034 0.02447 -0.1223 0.9240 0.0603
-4.500 -0.0408 0.02710 0.02059 -0.1247 0.9226 0.0461
-4.250 -0.0005 0.02378 0.01699 -0.1276 0.9215 0.0426
-4.000 0.0280 0.02214 0.01510 -0.1277 0.9159 0.0411
-3.750 0.0633 0.02071 0.01346 -0.1291 0.9124 0.0403
-3.500 0.1024 0.01944 0.01209 -0.1311 0.9101 0.0411
-3.250 0.1433 0.01837 0.01096 -0.1336 0.9084 0.0426
-3.000 0.1862 0.01748 0.01001 -0.1365 0.9071 0.0453
-2.750 0.2118 0.01690 0.00943 -0.1365 0.8993 0.0520
-2.500 0.2537 0.01610 0.00858 -0.1393 0.8969 0.0664
-2.250 0.3015 0.01402 0.00818 -0.1448 0.8961 0.5038
-2.000 0.3429 0.01376 0.00806 -0.1470 0.8944 0.5977
-1.750 0.3704 0.01379 0.00810 -0.1466 0.8879 0.6361
-1.500 0.4039 0.01376 0.00815 -0.1469 0.8837 0.6839
-1.250 0.4430 0.01357 0.00795 -0.1485 0.8812 0.7107
-1.000 0.4761 0.01343 0.00777 -0.1492 0.8763 0.7273
-0.750 0.5065 0.01331 0.00763 -0.1495 0.8700 0.7417
-0.500 0.5461 0.01303 0.00731 -0.1515 0.8667 0.7554
-0.250 0.5727 0.01299 0.00725 -0.1510 0.8590 0.7676
0.000 0.6085 0.01277 0.00701 -0.1523 0.8540 0.7798
0.250 0.6391 0.01267 0.00689 -0.1527 0.8472 0.7914
0.500 0.6710 0.01253 0.00674 -0.1533 0.8404 0.8027
0.750 0.6996 0.01244 0.00665 -0.1532 0.8329 0.8134
1.000 0.7303 0.01231 0.00652 -0.1536 0.8256 0.8245
1.250 0.7563 0.01228 0.00650 -0.1530 0.8168 0.8364
1.500 0.7888 0.01214 0.00634 -0.1537 0.8099 0.8487
1.750 0.8110 0.01213 0.00637 -0.1524 0.7997 0.8622
2.000 0.8368 0.01205 0.00632 -0.1517 0.7909 0.8767
2.250 0.8628 0.01193 0.00621 -0.1510 0.7822 0.8928
2.500 0.8821 0.01186 0.00618 -0.1490 0.7714 0.9142
2.750 0.9036 0.01170 0.00607 -0.1474 0.7612 0.9467
3.000 0.9412 0.01161 0.00599 -0.1495 0.7511 1.0000
3.250 0.9753 0.01169 0.00602 -0.1510 0.7396 1.0000
3.500 1.0056 0.01179 0.00611 -0.1517 0.7271 1.0000
3.750 1.0348 0.01190 0.00620 -0.1521 0.7143 1.0000
4.000 1.0629 0.01201 0.00632 -0.1522 0.7006 1.0000
4.250 1.0901 0.01212 0.00641 -0.1521 0.6861 1.0000
4.500 1.1165 0.01225 0.00652 -0.1517 0.6711 1.0000
4.750 1.1424 0.01240 0.00664 -0.1513 0.6555 1.0000
5.000 1.1668 0.01257 0.00679 -0.1505 0.6382 1.0000
5.250 1.1896 0.01276 0.00702 -0.1494 0.6191 1.0000
5.500 1.2126 0.01298 0.00720 -0.1484 0.5995 1.0000
5.750 1.2342 0.01323 0.00744 -0.1471 0.5783 1.0000
6.000 1.2553 0.01353 0.00769 -0.1457 0.5564 1.0000
6.250 1.2748 0.01386 0.00800 -0.1441 0.5325 1.0000
6.500 1.2936 0.01423 0.00834 -0.1423 0.5074 1.0000
6.750 1.3109 0.01466 0.00874 -0.1403 0.4805 1.0000
7.000 1.3267 0.01515 0.00917 -0.1380 0.4513 1.0000
7.250 1.3405 0.01571 0.00965 -0.1354 0.4193 1.0000
7.500 1.3516 0.01637 0.01019 -0.1324 0.3855 1.0000
7.750 1.3603 0.01709 0.01080 -0.1290 0.3491 1.0000
8.000 1.3659 0.01800 0.01153 -0.1252 0.3079 1.0000
8.250 1.3691 0.01913 0.01241 -0.1212 0.2629 1.0000
8.500 1.3711 0.02044 0.01345 -0.1173 0.2181 1.0000
8.750 1.3745 0.02180 0.01461 -0.1138 0.1788 1.0000
9.000 1.3788 0.02319 0.01583 -0.1106 0.1486 1.0000
9.250 1.3850 0.02454 0.01707 -0.1078 0.1246 1.0000
9.500 1.3910 0.02594 0.01838 -0.1050 0.1061 1.0000
9.750 1.3985 0.02729 0.01972 -0.1026 0.0914 1.0000
10.000 1.4055 0.02872 0.02115 -0.1003 0.0776 1.0000
10.250 1.4113 0.03030 0.02270 -0.0979 0.0620 1.0000
10.500 1.4100 0.03255 0.02485 -0.0950 0.0445 1.0000
10.750 1.4058 0.03520 0.02750 -0.0918 0.0333 1.0000
11.000 1.4071 0.03743 0.02982 -0.0895 0.0286 1.0000
11.250 1.3990 0.04066 0.03311 -0.0867 0.0259 1.0000
11.500 1.4025 0.04294 0.03558 -0.0849 0.0244 1.0000
11.750 1.4057 0.04537 0.03815 -0.0832 0.0230 1.0000
12.000 1.4092 0.04784 0.04074 -0.0817 0.0217 1.0000
12.250 1.4127 0.05030 0.04330 -0.0804 0.0205 1.0000
12.500 1.4143 0.05311 0.04618 -0.0793 0.0192 1.0000
12.750 1.4164 0.05668 0.04985 -0.0777 0.0180 1.0000
13.000 1.4227 0.05924 0.05262 -0.0768 0.0176 1.0000
13.250 1.4284 0.06212 0.05570 -0.0758 0.0172 1.0000
13.500 1.4326 0.06530 0.05911 -0.0749 0.0168 1.0000
13.750 1.4346 0.06882 0.06288 -0.0742 0.0165 1.0000
14.000 1.4335 0.07275 0.06706 -0.0736 0.0163 1.0000
14.250 1.4292 0.07712 0.07171 -0.0734 0.0161 1.0000
14.500 1.4215 0.08197 0.07684 -0.0735 0.0161 1.0000
14.750 1.4109 0.08730 0.08245 -0.0742 0.0160 1.0000
15.000 1.3979 0.09310 0.08852 -0.0754 0.0160 1.0000
15.250 1.3828 0.09942 0.09511 -0.0773 0.0161 1.0000
15.500 1.3663 0.10619 0.10213 -0.0799 0.0162 1.0000
15.750 1.3485 0.11348 0.10968 -0.0832 0.0163 1.0000
16.000 1.3300 0.12128 0.11771 -0.0874 0.0164 1.0000
16.250 1.3110 0.12964 0.12628 -0.0923 0.0166 1.0000
16.500 1.2911 0.13872 0.13557 -0.0982 0.0167 1.0000
16.750 1.2708 0.14848 0.14551 -0.1049 0.0169 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S4022 (s4022-il)