S8038 (13%) (s8038-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8038 (13%) (s8038-il) Reynolds number: 200,000 Max Cl/Cd: 59.8 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8038-il-200000.txt Download as CSV file: xf-s8038-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.3986 0.14448 0.14082 -0.0149 1.0000 0.0563
-14.250 -0.5573 0.15024 0.14628 -0.0128 1.0000 0.0537
-14.000 -0.5406 0.14833 0.14435 -0.0108 1.0000 0.0549
-13.750 -0.5313 0.14561 0.14163 -0.0107 1.0000 0.0562
-13.500 -0.5261 0.14224 0.13827 -0.0116 1.0000 0.0577
-13.250 -0.5238 0.13845 0.13448 -0.0131 1.0000 0.0597
-13.000 -0.5500 0.13040 0.12653 -0.0217 1.0000 0.0637
-12.750 -0.5617 0.12301 0.11920 -0.0253 1.0000 0.0644
-12.500 -0.5471 0.12089 0.11706 -0.0228 1.0000 0.0653
-12.250 -0.5005 0.09026 0.08664 -0.0395 1.0000 0.0430
-12.000 -0.5035 0.08603 0.08245 -0.0398 1.0000 0.0416
-11.750 -0.4994 0.08605 0.08253 -0.0408 1.0000 0.0546
-11.500 -0.4754 0.08874 0.08522 -0.0371 1.0000 0.0561
-11.250 -0.7208 0.04912 0.04460 -0.0575 1.0000 0.0361
-11.000 -0.7178 0.04532 0.04076 -0.0566 1.0000 0.0349
-10.750 -0.8086 0.05416 0.04923 -0.0494 1.0000 0.0351
-10.500 -0.8188 0.05045 0.04542 -0.0465 1.0000 0.0343
-10.250 -0.8301 0.04715 0.04192 -0.0432 1.0000 0.0337
-10.000 -0.8388 0.04390 0.03841 -0.0396 1.0000 0.0331
-9.750 -0.8451 0.04055 0.03473 -0.0359 1.0000 0.0323
-9.500 -0.8467 0.03737 0.03117 -0.0323 1.0000 0.0317
-9.250 -0.8423 0.03479 0.02826 -0.0293 1.0000 0.0316
-9.000 -0.8337 0.03255 0.02573 -0.0266 1.0000 0.0315
-8.750 -0.8215 0.03081 0.02377 -0.0243 1.0000 0.0321
-8.500 -0.8081 0.02950 0.02229 -0.0220 1.0000 0.0333
-8.250 -0.7935 0.02801 0.02060 -0.0199 1.0000 0.0340
-8.000 -0.7773 0.02649 0.01889 -0.0179 1.0000 0.0344
-7.750 -0.7604 0.02515 0.01741 -0.0159 1.0000 0.0348
-7.500 -0.7434 0.02405 0.01618 -0.0139 1.0000 0.0354
-7.250 -0.7272 0.02254 0.01463 -0.0120 1.0000 0.0362
-7.000 -0.7135 0.02132 0.01345 -0.0097 1.0000 0.0375
-6.750 -0.7002 0.02051 0.01266 -0.0073 1.0000 0.0389
-6.500 -0.6873 0.01984 0.01198 -0.0048 1.0000 0.0410
-6.250 -0.6737 0.01936 0.01141 -0.0023 1.0000 0.0436
-6.000 -0.6655 0.01835 0.01047 0.0007 1.0000 0.0464
-5.750 -0.6542 0.01780 0.00991 0.0033 1.0000 0.0498
-5.500 -0.6247 0.01683 0.00898 0.0024 0.9959 0.0615
-5.250 -0.5913 0.01534 0.00792 0.0003 0.9890 0.1207
-5.000 -0.5546 0.01433 0.00740 -0.0025 0.9829 0.2112
-4.750 -0.5211 0.01355 0.00698 -0.0044 0.9744 0.2893
-4.500 -0.4885 0.01279 0.00667 -0.0059 0.9661 0.3830
-4.250 -0.4531 0.01219 0.00650 -0.0077 0.9592 0.4768
-4.000 -0.4208 0.01191 0.00641 -0.0085 0.9499 0.5376
-3.750 -0.3803 0.01175 0.00634 -0.0107 0.9446 0.5854
-3.500 -0.3468 0.01165 0.00624 -0.0115 0.9354 0.6165
-3.250 -0.3052 0.01153 0.00612 -0.0139 0.9306 0.6441
-3.000 -0.2690 0.01145 0.00603 -0.0152 0.9225 0.6666
-2.750 -0.2291 0.01135 0.00587 -0.0172 0.9160 0.6868
-2.500 -0.1934 0.01125 0.00576 -0.0184 0.9072 0.7036
-2.250 -0.1547 0.01115 0.00563 -0.0201 0.8994 0.7199
-2.000 -0.1223 0.01108 0.00555 -0.0205 0.8880 0.7341
-1.750 -0.0877 0.01101 0.00546 -0.0214 0.8776 0.7463
-1.500 -0.0542 0.01094 0.00535 -0.0220 0.8668 0.7583
-1.250 -0.0264 0.01092 0.00530 -0.0216 0.8535 0.7706
-1.000 0.0010 0.01091 0.00524 -0.0211 0.8405 0.7831
-0.750 0.0298 0.01091 0.00522 -0.0208 0.8282 0.7931
-0.500 0.0580 0.01090 0.00517 -0.0205 0.8162 0.8037
-0.250 0.0843 0.01090 0.00511 -0.0198 0.8038 0.8153
0.000 0.1106 0.01092 0.00512 -0.0190 0.7905 0.8254
0.250 0.1365 0.01092 0.00511 -0.0183 0.7774 0.8357
0.500 0.1618 0.01093 0.00507 -0.0174 0.7645 0.8470
0.750 0.1894 0.01095 0.00507 -0.0169 0.7520 0.8568
1.000 0.2167 0.01097 0.00504 -0.0164 0.7396 0.8672
1.250 0.2416 0.01097 0.00505 -0.0155 0.7259 0.8790
1.500 0.2698 0.01101 0.00507 -0.0152 0.7118 0.8894
1.750 0.2989 0.01104 0.00507 -0.0151 0.6967 0.8995
2.000 0.3274 0.01107 0.00507 -0.0149 0.6811 0.9108
2.250 0.3618 0.01114 0.00512 -0.0159 0.6651 0.9195
2.500 0.3958 0.01122 0.00517 -0.0169 0.6489 0.9286
2.750 0.4320 0.01131 0.00523 -0.0185 0.6318 0.9372
3.000 0.4705 0.01142 0.00528 -0.0205 0.6140 0.9443
3.250 0.5100 0.01153 0.00538 -0.0228 0.5937 0.9513
3.500 0.5485 0.01164 0.00545 -0.0249 0.5715 0.9585
3.750 0.5879 0.01177 0.00553 -0.0273 0.5471 0.9659
4.000 0.6263 0.01191 0.00558 -0.0295 0.5196 0.9738
4.250 0.6638 0.01207 0.00567 -0.0317 0.4896 0.9830
4.500 0.7046 0.01224 0.00576 -0.0347 0.4539 0.9906
4.750 0.7447 0.01250 0.00585 -0.0377 0.4111 0.9985
5.000 0.7594 0.01270 0.00592 -0.0357 0.3761 1.0000
5.250 0.7666 0.01297 0.00605 -0.0322 0.3446 1.0000
5.500 0.7748 0.01333 0.00625 -0.0288 0.3116 1.0000
5.750 0.7848 0.01379 0.00653 -0.0257 0.2790 1.0000
6.000 0.7963 0.01432 0.00688 -0.0229 0.2497 1.0000
6.250 0.8088 0.01490 0.00729 -0.0202 0.2254 1.0000
6.500 0.8230 0.01545 0.00774 -0.0178 0.2047 1.0000
6.750 0.8374 0.01604 0.00822 -0.0155 0.1883 1.0000
7.000 0.8524 0.01664 0.00874 -0.0133 0.1749 1.0000
7.250 0.8672 0.01727 0.00930 -0.0111 0.1635 1.0000
7.500 0.8820 0.01796 0.00989 -0.0089 0.1536 1.0000
7.750 0.8995 0.01848 0.01046 -0.0071 0.1451 1.0000
8.000 0.9149 0.01930 0.01116 -0.0052 0.1381 1.0000
8.250 0.9329 0.01979 0.01175 -0.0035 0.1312 1.0000
8.500 0.9494 0.02060 0.01247 -0.0018 0.1253 1.0000
8.750 0.9674 0.02121 0.01317 -0.0003 0.1200 1.0000
9.000 0.9847 0.02182 0.01380 0.0014 0.1149 1.0000
9.250 1.0029 0.02283 0.01473 0.0026 0.1099 1.0000
9.500 1.0196 0.02339 0.01545 0.0043 0.1058 1.0000
9.750 1.0361 0.02403 0.01613 0.0060 0.1016 1.0000
10.000 1.0565 0.02532 0.01731 0.0066 0.0970 1.0000
10.250 1.0710 0.02595 0.01813 0.0086 0.0941 1.0000
10.500 1.0854 0.02668 0.01898 0.0105 0.0906 1.0000
10.750 1.0994 0.02743 0.01974 0.0124 0.0872 1.0000
11.000 1.1190 0.02892 0.02123 0.0129 0.0835 1.0000
11.250 1.1280 0.02970 0.02220 0.0156 0.0810 1.0000
11.500 1.1389 0.03064 0.02326 0.0178 0.0782 1.0000
11.750 1.1513 0.03159 0.02425 0.0196 0.0757 1.0000
12.000 1.1706 0.03330 0.02594 0.0200 0.0727 1.0000
12.250 1.1772 0.03472 0.02758 0.0223 0.0708 1.0000
12.500 1.1818 0.03593 0.02899 0.0248 0.0690 1.0000
12.750 1.1868 0.03725 0.03047 0.0270 0.0670 1.0000
13.000 1.1926 0.03857 0.03190 0.0289 0.0652 1.0000
13.250 1.2005 0.03998 0.03337 0.0303 0.0637 1.0000
13.500 1.2114 0.04182 0.03525 0.0313 0.0621 1.0000
13.750 1.2115 0.04498 0.03861 0.0327 0.0607 1.0000
14.000 1.2038 0.04709 0.04097 0.0346 0.0600 1.0000
14.250 1.1949 0.04965 0.04377 0.0360 0.0592 1.0000
14.500 1.1841 0.05255 0.04692 0.0369 0.0584 1.0000
14.750 1.1711 0.05599 0.05058 0.0373 0.0577 1.0000
15.000 1.1567 0.05978 0.05459 0.0371 0.0570 1.0000
15.250 1.1391 0.06420 0.05922 0.0362 0.0565 1.0000
15.500 1.1152 0.06977 0.06501 0.0344 0.0563 1.0000
15.750 1.0818 0.07711 0.07258 0.0310 0.0562 1.0000
16.000 1.0246 0.08910 0.08488 0.0241 0.0570 1.0000
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Polar data table (+)
Polar graphs
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