S8038 (13%) (s8038-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8038 (13%) (s8038-il) Reynolds number: 200,000 Max Cl/Cd: 52.86 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8038-il-200000-n5.txt Download as CSV file: xf-s8038-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8038 (13%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6993 0.10382 0.09961 -0.0275 1.0000 0.0149
-14.250 -0.7310 0.09216 0.08783 -0.0346 1.0000 0.0147
-14.000 -0.7612 0.08186 0.07735 -0.0413 1.0000 0.0145
-13.750 -0.7869 0.07349 0.06879 -0.0468 1.0000 0.0145
-13.500 -0.8075 0.06685 0.06197 -0.0507 1.0000 0.0144
-13.250 -0.8242 0.06143 0.05637 -0.0535 1.0000 0.0143
-13.000 -0.8436 0.05615 0.05085 -0.0557 1.0000 0.0144
-12.750 -0.8579 0.05194 0.04642 -0.0567 1.0000 0.0144
-12.500 -0.8693 0.04837 0.04264 -0.0569 1.0000 0.0145
-12.250 -0.8798 0.04517 0.03920 -0.0563 1.0000 0.0146
-12.000 -0.8855 0.04259 0.03642 -0.0552 1.0000 0.0146
-11.750 -0.8918 0.04012 0.03370 -0.0534 1.0000 0.0148
-11.500 -0.8938 0.03816 0.03154 -0.0513 1.0000 0.0149
-11.250 -0.8949 0.03637 0.02954 -0.0488 1.0000 0.0150
-11.000 -0.8936 0.03469 0.02772 -0.0460 1.0000 0.0152
-10.750 -0.8906 0.03328 0.02624 -0.0432 1.0000 0.0154
-10.500 -0.8867 0.03201 0.02489 -0.0402 1.0000 0.0156
-10.250 -0.8799 0.03099 0.02383 -0.0376 1.0000 0.0160
-10.000 -0.8707 0.02996 0.02270 -0.0352 1.0000 0.0165
-9.750 -0.8606 0.02887 0.02152 -0.0329 1.0000 0.0170
-9.500 -0.8493 0.02780 0.02033 -0.0306 1.0000 0.0175
-9.250 -0.8373 0.02674 0.01916 -0.0283 1.0000 0.0179
-9.000 -0.8250 0.02568 0.01800 -0.0260 1.0000 0.0182
-8.750 -0.8124 0.02471 0.01693 -0.0237 1.0000 0.0186
-8.500 -0.8004 0.02373 0.01588 -0.0212 1.0000 0.0190
-8.250 -0.7891 0.02279 0.01493 -0.0187 1.0000 0.0194
-8.000 -0.7766 0.02200 0.01412 -0.0163 1.0000 0.0200
-7.750 -0.7638 0.02127 0.01335 -0.0140 1.0000 0.0206
-7.500 -0.7507 0.02060 0.01263 -0.0116 1.0000 0.0212
-7.250 -0.7375 0.01997 0.01195 -0.0092 1.0000 0.0221
-7.000 -0.7095 0.01925 0.01115 -0.0098 0.9968 0.0238
-6.750 -0.6770 0.01850 0.01038 -0.0114 0.9917 0.0257
-6.500 -0.6447 0.01781 0.00961 -0.0127 0.9857 0.0283
-6.250 -0.6144 0.01705 0.00883 -0.0137 0.9787 0.0321
-6.000 -0.5829 0.01636 0.00813 -0.0149 0.9718 0.0393
-5.500 -0.5246 0.01498 0.00696 -0.0162 0.9550 0.0796
-5.250 -0.4947 0.01433 0.00646 -0.0170 0.9465 0.1116
-5.000 -0.4651 0.01369 0.00601 -0.0178 0.9375 0.1523
-4.750 -0.4333 0.01289 0.00556 -0.0191 0.9298 0.2218
-4.500 -0.4039 0.01222 0.00517 -0.0199 0.9195 0.2872
-4.250 -0.3715 0.01164 0.00483 -0.0211 0.9104 0.3488
-4.000 -0.3399 0.01114 0.00456 -0.0221 0.8998 0.4102
-3.750 -0.3087 0.01078 0.00435 -0.0227 0.8879 0.4611
-3.500 -0.2767 0.01052 0.00420 -0.0235 0.8761 0.5064
-3.250 -0.2444 0.01036 0.00408 -0.0242 0.8639 0.5445
-3.000 -0.2133 0.01026 0.00397 -0.0247 0.8509 0.5721
-2.750 -0.1840 0.01020 0.00387 -0.0247 0.8372 0.5941
-2.500 -0.1557 0.01015 0.00379 -0.0245 0.8237 0.6138
-2.250 -0.1279 0.01013 0.00372 -0.0243 0.8104 0.6314
-2.000 -0.1002 0.01012 0.00365 -0.0240 0.7974 0.6459
-1.750 -0.0729 0.01012 0.00358 -0.0236 0.7845 0.6591
-1.500 -0.0461 0.01013 0.00353 -0.0232 0.7718 0.6722
-1.250 -0.0198 0.01013 0.00350 -0.0226 0.7591 0.6846
-1.000 0.0066 0.01013 0.00347 -0.0220 0.7470 0.6959
-0.750 0.0331 0.01015 0.00344 -0.0215 0.7353 0.7066
-0.500 0.0595 0.01017 0.00341 -0.0210 0.7238 0.7175
-0.250 0.0856 0.01018 0.00341 -0.0204 0.7117 0.7277
0.000 0.1116 0.01020 0.00341 -0.0199 0.6998 0.7380
0.250 0.1377 0.01023 0.00341 -0.0193 0.6878 0.7481
0.500 0.1638 0.01026 0.00341 -0.0187 0.6754 0.7574
0.750 0.1895 0.01029 0.00341 -0.0181 0.6624 0.7678
1.000 0.2154 0.01032 0.00344 -0.0175 0.6495 0.7775
1.250 0.2411 0.01035 0.00347 -0.0168 0.6365 0.7875
1.500 0.2666 0.01039 0.00349 -0.0162 0.6224 0.7981
1.750 0.2922 0.01043 0.00352 -0.0155 0.6063 0.8077
2.000 0.3173 0.01049 0.00356 -0.0147 0.5891 0.8182
2.250 0.3425 0.01055 0.00360 -0.0140 0.5719 0.8295
2.500 0.3684 0.01062 0.00366 -0.0134 0.5544 0.8405
2.750 0.3943 0.01070 0.00373 -0.0129 0.5365 0.8523
3.000 0.4207 0.01080 0.00381 -0.0124 0.5171 0.8652
3.250 0.4482 0.01092 0.00391 -0.0122 0.4963 0.8787
3.500 0.4770 0.01109 0.00404 -0.0124 0.4731 0.8925
3.750 0.5081 0.01128 0.00418 -0.0130 0.4463 0.9058
4.000 0.5406 0.01154 0.00436 -0.0140 0.4154 0.9189
4.500 0.6071 0.01224 0.00480 -0.0167 0.3445 0.9439
5.000 0.6733 0.01312 0.00539 -0.0196 0.2737 0.9674
5.250 0.7049 0.01360 0.00573 -0.0208 0.2425 0.9798
5.500 0.7368 0.01407 0.00610 -0.0221 0.2158 0.9919
5.750 0.7686 0.01454 0.00647 -0.0235 0.1940 1.0000
6.000 0.7839 0.01491 0.00677 -0.0213 0.1791 1.0000
6.250 0.7998 0.01530 0.00709 -0.0193 0.1655 1.0000
6.500 0.8163 0.01571 0.00746 -0.0173 0.1538 1.0000
6.750 0.8337 0.01610 0.00782 -0.0155 0.1436 1.0000
7.000 0.8506 0.01652 0.00822 -0.0136 0.1355 1.0000
7.250 0.8675 0.01695 0.00864 -0.0118 0.1274 1.0000
7.500 0.8845 0.01739 0.00909 -0.0100 0.1205 1.0000
7.750 0.9014 0.01784 0.00954 -0.0081 0.1140 1.0000
8.000 0.9177 0.01834 0.01003 -0.0062 0.1088 1.0000
8.250 0.9349 0.01880 0.01054 -0.0045 0.1036 1.0000
8.500 0.9505 0.01934 0.01107 -0.0026 0.0989 1.0000
8.750 0.9664 0.01987 0.01162 -0.0007 0.0948 1.0000
9.000 0.9829 0.02036 0.01218 0.0011 0.0906 1.0000
9.250 0.9975 0.02093 0.01275 0.0030 0.0868 1.0000
9.500 1.0094 0.02157 0.01340 0.0054 0.0835 1.0000
9.750 1.0237 0.02209 0.01402 0.0075 0.0804 1.0000
10.000 1.0369 0.02267 0.01466 0.0096 0.0773 1.0000
10.250 1.0483 0.02335 0.01535 0.0119 0.0745 1.0000
10.500 1.0578 0.02420 0.01619 0.0142 0.0721 1.0000
10.750 1.0715 0.02486 0.01699 0.0160 0.0698 1.0000
11.000 1.0839 0.02562 0.01784 0.0178 0.0674 1.0000
11.250 1.0953 0.02643 0.01873 0.0196 0.0651 1.0000
11.500 1.1048 0.02738 0.01971 0.0214 0.0628 1.0000
11.750 1.1119 0.02857 0.02091 0.0233 0.0608 1.0000
12.000 1.1235 0.02951 0.02200 0.0247 0.0590 1.0000
12.250 1.1334 0.03061 0.02323 0.0260 0.0570 1.0000
12.500 1.1421 0.03180 0.02452 0.0274 0.0553 1.0000
12.750 1.1498 0.03311 0.02591 0.0285 0.0537 1.0000
13.000 1.1555 0.03461 0.02746 0.0296 0.0522 1.0000
13.250 1.1594 0.03636 0.02924 0.0307 0.0508 1.0000
13.500 1.1667 0.03792 0.03097 0.0315 0.0495 1.0000
13.750 1.1726 0.03964 0.03283 0.0321 0.0480 1.0000
14.000 1.1772 0.04152 0.03484 0.0326 0.0466 1.0000
14.250 1.1807 0.04354 0.03699 0.0330 0.0454 1.0000
14.500 1.1832 0.04574 0.03928 0.0331 0.0444 1.0000
14.750 1.1841 0.04814 0.04177 0.0331 0.0435 1.0000
15.000 1.1838 0.05077 0.04446 0.0330 0.0427 1.0000
15.250 1.1825 0.05360 0.04738 0.0327 0.0418 1.0000
15.500 1.1813 0.05654 0.05050 0.0322 0.0411 1.0000
15.750 1.1785 0.05980 0.05394 0.0315 0.0403 1.0000
16.000 1.1743 0.06333 0.05762 0.0304 0.0395 1.0000
16.250 1.1692 0.06710 0.06155 0.0292 0.0389 1.0000
16.500 1.1629 0.07120 0.06580 0.0275 0.0382 1.0000
16.750 1.1553 0.07564 0.07037 0.0257 0.0376 1.0000
17.000 1.1472 0.08030 0.07516 0.0235 0.0370 1.0000
17.250 1.1375 0.08537 0.08036 0.0210 0.0365 1.0000
17.500 1.1266 0.09082 0.08594 0.0182 0.0361 1.0000
17.750 1.1144 0.09664 0.09189 0.0151 0.0358 1.0000
18.000 1.1013 0.10276 0.09812 0.0118 0.0354 1.0000
18.250 1.0892 0.10882 0.10428 0.0085 0.0349 1.0000
18.750 1.0465 0.12532 0.12106 -0.0010 0.0344 1.0000
19.000 0.9565 0.15040 0.14647 -0.0162 0.0344 1.0000
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Polar data table (+)
Polar graphs
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