S8038 (13%) (s8038-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8038 (13%) (s8038-il) Reynolds number: 50,000 Max Cl/Cd: 30.33 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8038-il-50000-n5.txt Download as CSV file: xf-s8038-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5917 0.09482 0.08715 -0.0359 1.0000 0.0486
-11.500 -0.6230 0.08459 0.07689 -0.0426 1.0000 0.0474
-11.250 -0.6613 0.07561 0.06777 -0.0483 1.0000 0.0464
-11.000 -0.6939 0.06926 0.06126 -0.0511 1.0000 0.0458
-10.750 -0.7205 0.06460 0.05638 -0.0515 1.0000 0.0455
-10.500 -0.7403 0.06107 0.05266 -0.0500 1.0000 0.0454
-10.250 -0.7550 0.05815 0.04957 -0.0474 1.0000 0.0456
-10.000 -0.7635 0.05528 0.04648 -0.0449 1.0000 0.0458
-9.750 -0.7668 0.05252 0.04350 -0.0426 1.0000 0.0463
-9.500 -0.7662 0.04987 0.04060 -0.0403 1.0000 0.0470
-9.250 -0.7622 0.04733 0.03780 -0.0381 1.0000 0.0478
-9.000 -0.7550 0.04491 0.03512 -0.0360 1.0000 0.0490
-8.750 -0.7456 0.04268 0.03257 -0.0339 1.0000 0.0510
-8.500 -0.7335 0.04055 0.03008 -0.0319 1.0000 0.0533
-8.250 -0.7189 0.03882 0.02840 -0.0304 1.0000 0.0559
-8.000 -0.7028 0.03716 0.02663 -0.0288 1.0000 0.0589
-7.750 -0.6840 0.03546 0.02469 -0.0271 1.0000 0.0624
-7.500 -0.6681 0.03397 0.02319 -0.0254 1.0000 0.0666
-7.250 -0.6535 0.03267 0.02184 -0.0234 1.0000 0.0733
-7.000 -0.6404 0.03134 0.02053 -0.0212 1.0000 0.0809
-6.750 -0.6279 0.03010 0.01927 -0.0189 1.0000 0.0912
-6.500 -0.6175 0.02884 0.01812 -0.0164 1.0000 0.1064
-6.250 -0.6078 0.02759 0.01697 -0.0139 1.0000 0.1289
-6.000 -0.5993 0.02631 0.01592 -0.0112 1.0000 0.1597
-5.750 -0.5915 0.02508 0.01502 -0.0085 1.0000 0.1993
-5.500 -0.5833 0.02400 0.01423 -0.0057 1.0000 0.2508
-5.250 -0.5751 0.02305 0.01365 -0.0029 1.0000 0.3088
-5.000 -0.5660 0.02232 0.01324 0.0001 1.0000 0.3713
-4.750 -0.5555 0.02183 0.01306 0.0032 1.0000 0.4321
-4.500 -0.5437 0.02161 0.01304 0.0063 1.0000 0.4879
-4.250 -0.5312 0.02157 0.01311 0.0094 1.0000 0.5359
-4.000 -0.5185 0.02160 0.01314 0.0123 1.0000 0.5778
-3.750 -0.5055 0.02169 0.01320 0.0153 1.0000 0.6126
-3.500 -0.4808 0.02189 0.01332 0.0160 0.9949 0.6475
-3.250 -0.4452 0.02214 0.01346 0.0149 0.9846 0.6810
-3.000 -0.4103 0.02234 0.01353 0.0139 0.9739 0.7094
-2.750 -0.3766 0.02245 0.01350 0.0130 0.9629 0.7355
-2.500 -0.3404 0.02262 0.01356 0.0120 0.9528 0.7575
-2.250 -0.3016 0.02274 0.01353 0.0102 0.9435 0.7793
-2.000 -0.2680 0.02278 0.01347 0.0093 0.9321 0.7993
-1.750 -0.2299 0.02286 0.01345 0.0077 0.9221 0.8168
-1.500 -0.1851 0.02294 0.01340 0.0048 0.9139 0.8334
-1.250 -0.1467 0.02298 0.01336 0.0029 0.9031 0.8490
-1.000 -0.1011 0.02301 0.01327 -0.0003 0.8946 0.8633
-0.750 -0.0540 0.02303 0.01321 -0.0038 0.8853 0.8761
-0.500 -0.0040 0.02305 0.01316 -0.0080 0.8760 0.8869
-0.250 0.0473 0.02299 0.01303 -0.0124 0.8673 0.8975
0.000 0.0892 0.02295 0.01294 -0.0152 0.8553 0.9092
0.250 0.1431 0.02287 0.01283 -0.0201 0.8449 0.9167
0.500 0.1921 0.02272 0.01264 -0.0241 0.8346 0.9260
0.750 0.2396 0.02263 0.01254 -0.0280 0.8213 0.9339
1.000 0.2820 0.02254 0.01244 -0.0309 0.8075 0.9434
1.250 0.3253 0.02242 0.01233 -0.0340 0.7934 0.9525
1.500 0.3679 0.02230 0.01223 -0.0368 0.7783 0.9614
1.750 0.4078 0.02219 0.01213 -0.0392 0.7622 0.9713
2.000 0.4480 0.02206 0.01203 -0.0417 0.7452 0.9811
2.250 0.4883 0.02191 0.01190 -0.0441 0.7273 0.9909
2.500 0.5269 0.02176 0.01176 -0.0462 0.7087 1.0000
2.750 0.5419 0.02177 0.01177 -0.0440 0.6903 1.0000
3.000 0.5551 0.02181 0.01182 -0.0415 0.6708 1.0000
3.250 0.5689 0.02185 0.01185 -0.0389 0.6512 1.0000
3.500 0.5838 0.02186 0.01184 -0.0364 0.6315 1.0000
3.750 0.5982 0.02191 0.01188 -0.0338 0.6112 1.0000
4.000 0.6113 0.02203 0.01199 -0.0311 0.5894 1.0000
4.250 0.6272 0.02210 0.01202 -0.0286 0.5677 1.0000
4.500 0.6414 0.02227 0.01217 -0.0260 0.5440 1.0000
4.750 0.6577 0.02241 0.01226 -0.0235 0.5197 1.0000
5.000 0.6721 0.02264 0.01247 -0.0210 0.4929 1.0000
5.250 0.6870 0.02290 0.01266 -0.0184 0.4647 1.0000
5.500 0.7019 0.02322 0.01288 -0.0159 0.4355 1.0000
5.750 0.7162 0.02361 0.01319 -0.0134 0.4048 1.0000
6.000 0.7299 0.02411 0.01354 -0.0109 0.3737 1.0000
6.250 0.7435 0.02470 0.01399 -0.0084 0.3436 1.0000
6.500 0.7567 0.02540 0.01453 -0.0061 0.3157 1.0000
6.750 0.7697 0.02618 0.01518 -0.0038 0.2899 1.0000
7.000 0.7835 0.02703 0.01593 -0.0017 0.2674 1.0000
7.250 0.7976 0.02793 0.01674 0.0002 0.2476 1.0000
7.500 0.8122 0.02888 0.01761 0.0020 0.2307 1.0000
7.750 0.8280 0.02986 0.01856 0.0037 0.2161 1.0000
8.000 0.8439 0.03087 0.01958 0.0052 0.2028 1.0000
8.250 0.8601 0.03192 0.02062 0.0067 0.1909 1.0000
8.500 0.8783 0.03301 0.02164 0.0078 0.1816 1.0000
8.750 0.8961 0.03417 0.02293 0.0090 0.1720 1.0000
9.000 0.9137 0.03537 0.02418 0.0102 0.1635 1.0000
9.250 0.9307 0.03656 0.02543 0.0114 0.1558 1.0000
9.500 0.9497 0.03797 0.02695 0.0123 0.1494 1.0000
9.750 0.9657 0.03937 0.02850 0.0135 0.1430 1.0000
10.000 0.9834 0.04074 0.02988 0.0144 0.1373 1.0000
10.250 0.9936 0.04245 0.03189 0.0161 0.1317 1.0000
10.500 1.0086 0.04401 0.03355 0.0172 0.1272 1.0000
10.750 1.0228 0.04572 0.03533 0.0183 0.1229 1.0000
11.000 1.0232 0.04782 0.03778 0.0208 0.1190 1.0000
11.250 1.0267 0.04968 0.03981 0.0229 0.1152 1.0000
11.500 1.0389 0.05132 0.04149 0.0240 0.1117 1.0000
11.750 1.0388 0.05375 0.04411 0.0259 0.1092 1.0000
12.000 1.0243 0.05682 0.04751 0.0282 0.1072 1.0000
12.250 1.0086 0.06024 0.05121 0.0297 0.1052 1.0000
12.500 0.9912 0.06405 0.05526 0.0304 0.1035 1.0000
12.750 0.9710 0.06855 0.05996 0.0301 0.1022 1.0000
13.000 0.9430 0.07442 0.06602 0.0284 0.1014 1.0000
13.250 0.8516 0.09114 0.08298 0.0189 0.1042 1.0000
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Polar data table (+)
Polar graphs
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