Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Davis AIRFOIL (davis-il) Reynolds number: 200,000 Max Cl/Cd: 76.05 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-davis-il-200000.txt Download as CSV file: xf-davis-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: Davis AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3779 0.10261 0.09919 -0.0413 1.0000 0.0583
-9.500 -0.3992 0.09932 0.09601 -0.0442 1.0000 0.0591
-9.250 -0.4142 0.09614 0.09291 -0.0450 1.0000 0.0593
-9.000 -0.4102 0.09204 0.08884 -0.0415 1.0000 0.0607
-8.750 -0.4037 0.09053 0.08733 -0.0384 1.0000 0.0620
-8.500 -0.4080 0.08857 0.08542 -0.0366 1.0000 0.0630
-8.250 -0.4157 0.08672 0.08362 -0.0347 1.0000 0.0648
-8.000 -0.4316 0.08464 0.08162 -0.0328 1.0000 0.0656
-7.750 -0.4548 0.08295 0.08002 -0.0301 1.0000 0.0667
-7.500 -0.4746 0.08041 0.07756 -0.0297 0.9992 0.0674
-7.250 -0.4616 0.06562 0.06259 -0.0538 0.9872 0.0734
-7.000 -0.4805 0.03857 0.03372 -0.0665 0.9740 0.0381
-6.750 -0.4547 0.03391 0.02850 -0.0688 0.9696 0.0383
-6.500 -0.4328 0.03038 0.02448 -0.0691 0.9622 0.0384
-6.250 -0.4005 0.02733 0.02092 -0.0708 0.9585 0.0384
-6.000 -0.3727 0.02469 0.01793 -0.0713 0.9529 0.0393
-5.750 -0.3413 0.02309 0.01616 -0.0724 0.9473 0.0417
-5.500 -0.3034 0.02176 0.01462 -0.0745 0.9441 0.0450
-5.250 -0.2732 0.02059 0.01323 -0.0748 0.9385 0.0470
-5.000 -0.2436 0.01910 0.01165 -0.0752 0.9333 0.0502
-4.750 -0.2075 0.01823 0.01076 -0.0769 0.9302 0.0560
-4.500 -0.1693 0.01720 0.00967 -0.0790 0.9281 0.0621
-4.250 -0.1472 0.01671 0.00916 -0.0779 0.9193 0.0705
-4.000 -0.1109 0.01581 0.00835 -0.0795 0.9161 0.0899
-3.750 -0.0717 0.01497 0.00786 -0.0819 0.9141 0.1743
-3.500 -0.0483 0.01482 0.00775 -0.0811 0.9058 0.2048
-3.250 -0.0101 0.01456 0.00748 -0.0832 0.9026 0.2346
-3.000 0.0297 0.01419 0.00713 -0.0855 0.9002 0.2635
-2.750 0.0554 0.01393 0.00692 -0.0850 0.8925 0.2899
-2.500 0.0909 0.01345 0.00657 -0.0865 0.8878 0.3288
-2.250 0.1304 0.01290 0.00617 -0.0886 0.8846 0.3789
-2.000 0.1529 0.01260 0.00601 -0.0873 0.8748 0.4243
-1.750 0.1879 0.01203 0.00564 -0.0885 0.8706 0.4872
-1.500 0.2089 0.01161 0.00550 -0.0869 0.8613 0.5575
-1.250 0.2361 0.01070 0.00532 -0.0859 0.8561 0.7416
-1.000 0.3219 0.01032 0.00523 -0.0967 0.8534 0.9437
-0.750 0.3863 0.01025 0.00504 -0.1040 0.8465 0.9830
-0.500 0.4526 0.01002 0.00466 -0.1119 0.8408 1.0000
-0.250 0.4745 0.00996 0.00450 -0.1105 0.8284 1.0000
0.000 0.4976 0.00992 0.00435 -0.1094 0.8158 1.0000
0.250 0.5214 0.00988 0.00422 -0.1084 0.8032 1.0000
0.500 0.5456 0.00987 0.00411 -0.1075 0.7905 1.0000
0.750 0.5701 0.00989 0.00403 -0.1067 0.7782 1.0000
1.000 0.5946 0.00994 0.00397 -0.1058 0.7657 1.0000
1.250 0.6192 0.01001 0.00394 -0.1050 0.7530 1.0000
1.500 0.6420 0.01011 0.00396 -0.1038 0.7396 1.0000
1.750 0.6644 0.01023 0.00402 -0.1026 0.7260 1.0000
2.000 0.6866 0.01035 0.00409 -0.1013 0.7124 1.0000
2.250 0.7088 0.01048 0.00417 -0.1000 0.6988 1.0000
2.500 0.7310 0.01061 0.00425 -0.0988 0.6853 1.0000
2.750 0.7530 0.01073 0.00435 -0.0975 0.6716 1.0000
3.000 0.7746 0.01085 0.00444 -0.0961 0.6571 1.0000
3.250 0.7959 0.01096 0.00452 -0.0946 0.6418 1.0000
3.500 0.8171 0.01108 0.00460 -0.0931 0.6255 1.0000
3.750 0.8381 0.01121 0.00470 -0.0916 0.6086 1.0000
4.000 0.8592 0.01137 0.00479 -0.0901 0.5913 1.0000
4.250 0.8795 0.01157 0.00494 -0.0885 0.5721 1.0000
4.500 0.8997 0.01183 0.00513 -0.0869 0.5522 1.0000
4.750 0.9200 0.01217 0.00535 -0.0853 0.5322 1.0000
5.000 0.9393 0.01251 0.00564 -0.0836 0.5102 1.0000
5.250 0.9588 0.01288 0.00593 -0.0819 0.4894 1.0000
5.500 0.9783 0.01323 0.00626 -0.0803 0.4695 1.0000
5.750 0.9979 0.01357 0.00658 -0.0787 0.4511 1.0000
6.000 1.0169 0.01389 0.00687 -0.0770 0.4329 1.0000
6.250 1.0344 0.01422 0.00713 -0.0750 0.4139 1.0000
6.750 1.0680 0.01495 0.00777 -0.0709 0.3749 1.0000
7.000 1.0854 0.01539 0.00817 -0.0691 0.3592 1.0000
7.250 1.1018 0.01587 0.00860 -0.0671 0.3426 1.0000
7.500 1.1171 0.01633 0.00904 -0.0649 0.3245 1.0000
7.750 1.1316 0.01674 0.00950 -0.0625 0.3050 1.0000
8.000 1.1445 0.01717 0.00994 -0.0599 0.2847 1.0000
8.250 1.1526 0.01761 0.01035 -0.0564 0.2520 1.0000
8.500 1.1422 0.01911 0.01119 -0.0504 0.1405 1.0000
8.750 1.1267 0.02160 0.01302 -0.0442 0.0612 1.0000
9.000 1.1269 0.02316 0.01447 -0.0403 0.0447 1.0000
9.250 1.1337 0.02429 0.01571 -0.0374 0.0396 1.0000
9.500 1.1357 0.02572 0.01720 -0.0342 0.0366 1.0000
9.750 1.1364 0.02727 0.01887 -0.0310 0.0346 1.0000
10.000 1.1416 0.02862 0.02033 -0.0285 0.0326 1.0000
10.250 1.1451 0.03015 0.02194 -0.0262 0.0307 1.0000
10.500 1.1464 0.03194 0.02381 -0.0238 0.0296 1.0000
10.750 1.1477 0.03385 0.02577 -0.0216 0.0289 1.0000
11.000 1.1470 0.03611 0.02808 -0.0194 0.0280 1.0000
11.250 1.1503 0.03841 0.03041 -0.0173 0.0272 1.0000
11.500 1.1609 0.04006 0.03216 -0.0158 0.0268 1.0000
11.750 1.1738 0.04173 0.03393 -0.0145 0.0263 1.0000
12.000 1.1866 0.04343 0.03577 -0.0132 0.0255 1.0000
12.250 1.1980 0.04518 0.03765 -0.0121 0.0245 1.0000
12.500 1.2109 0.04707 0.03966 -0.0110 0.0238 1.0000
12.750 1.2246 0.04917 0.04190 -0.0100 0.0233 1.0000
13.000 1.2378 0.05162 0.04455 -0.0089 0.0232 1.0000
13.250 1.2465 0.05443 0.04760 -0.0077 0.0231 1.0000
13.500 1.2491 0.05780 0.05126 -0.0065 0.0234 1.0000
13.750 1.2452 0.06169 0.05548 -0.0053 0.0239 1.0000
14.000 1.2364 0.06591 0.06000 -0.0045 0.0243 1.0000
14.250 1.2236 0.07058 0.06495 -0.0040 0.0248 1.0000
14.500 1.2100 0.07533 0.06995 -0.0040 0.0252 1.0000
14.750 1.1943 0.08049 0.07533 -0.0045 0.0257 1.0000
15.000 1.1769 0.08597 0.08102 -0.0057 0.0260 1.0000
15.250 1.1588 0.09187 0.08711 -0.0074 0.0264 1.0000
15.500 1.1393 0.09819 0.09361 -0.0097 0.0266 1.0000
15.750 0.9584 0.10320 0.09929 -0.0138 0.0260 1.0000
16.000 0.9334 0.10974 0.10602 -0.0180 0.0263 1.0000
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