DF102 (df102-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: DF102 (df102-il) Reynolds number: 200,000 Max Cl/Cd: 64.86 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-df102-il-200000.txt Download as CSV file: xf-df102-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: DF102
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4603 0.09873 0.09519 -0.0392 1.0000 0.0647
-10.000 -0.4572 0.09386 0.09036 -0.0381 1.0000 0.0658
-9.750 -0.4443 0.09191 0.08840 -0.0360 1.0000 0.0670
-9.500 -0.4374 0.08938 0.08589 -0.0355 1.0000 0.0687
-9.250 -0.4367 0.08609 0.08263 -0.0363 1.0000 0.0706
-9.000 -0.4428 0.08193 0.07853 -0.0383 1.0000 0.0729
-8.000 -0.5964 0.03534 0.03144 -0.0441 1.0000 0.0417
-7.750 -0.6589 0.03841 0.03316 -0.0392 1.0000 0.0342
-7.500 -0.6508 0.03580 0.03038 -0.0369 1.0000 0.0333
-7.250 -0.6460 0.03258 0.02685 -0.0343 1.0000 0.0328
-7.000 -0.6371 0.02998 0.02390 -0.0319 1.0000 0.0325
-6.750 -0.6250 0.02782 0.02139 -0.0297 1.0000 0.0327
-6.500 -0.5959 0.02597 0.01912 -0.0304 0.9971 0.0334
-6.250 -0.5637 0.02332 0.01621 -0.0320 0.9938 0.0355
-6.000 -0.5304 0.02189 0.01467 -0.0335 0.9893 0.0373
-5.750 -0.4943 0.02057 0.01320 -0.0351 0.9852 0.0394
-5.500 -0.4577 0.01964 0.01212 -0.0369 0.9813 0.0421
-5.250 -0.4265 0.01822 0.01073 -0.0379 0.9758 0.0464
-5.000 -0.3890 0.01740 0.00985 -0.0399 0.9717 0.0511
-4.750 -0.3564 0.01649 0.00894 -0.0410 0.9662 0.0584
-4.500 -0.3225 0.01566 0.00813 -0.0423 0.9605 0.0716
-4.250 -0.2860 0.01435 0.00747 -0.0446 0.9567 0.1852
-4.000 -0.2546 0.01417 0.00735 -0.0453 0.9495 0.2302
-3.750 -0.2155 0.01402 0.00719 -0.0476 0.9447 0.2628
-3.500 -0.1723 0.01381 0.00701 -0.0507 0.9417 0.2928
-3.250 -0.1429 0.01367 0.00692 -0.0510 0.9335 0.3237
-3.000 -0.1026 0.01339 0.00672 -0.0535 0.9294 0.3564
-2.750 -0.0612 0.01301 0.00642 -0.0561 0.9264 0.3849
-2.500 -0.0353 0.01273 0.00625 -0.0555 0.9168 0.4115
-2.250 0.0017 0.01230 0.00599 -0.0571 0.9125 0.4512
-2.000 0.0271 0.01196 0.00585 -0.0564 0.9033 0.4991
-1.750 0.0580 0.01145 0.00566 -0.0566 0.8976 0.5758
-1.500 0.0799 0.01104 0.00561 -0.0548 0.8879 0.6661
-1.250 0.1091 0.01054 0.00553 -0.0540 0.8822 0.7777
-1.000 0.1504 0.01042 0.00562 -0.0554 0.8750 0.8822
-0.750 0.2009 0.01031 0.00546 -0.0588 0.8682 0.9331
-0.500 0.2497 0.01018 0.00524 -0.0621 0.8568 0.9603
-0.250 0.3027 0.01000 0.00496 -0.0665 0.8450 0.9782
0.000 0.3570 0.00980 0.00465 -0.0714 0.8323 0.9936
0.250 0.3945 0.00963 0.00437 -0.0732 0.8171 1.0000
0.500 0.4152 0.00955 0.00420 -0.0715 0.8003 1.0000
0.750 0.4366 0.00950 0.00406 -0.0699 0.7842 1.0000
1.000 0.4587 0.00949 0.00396 -0.0686 0.7687 1.0000
1.250 0.4809 0.00950 0.00389 -0.0672 0.7527 1.0000
1.500 0.5033 0.00952 0.00383 -0.0659 0.7361 1.0000
1.750 0.5259 0.00957 0.00379 -0.0645 0.7190 1.0000
2.000 0.5485 0.00964 0.00376 -0.0632 0.7014 1.0000
2.250 0.5707 0.00972 0.00378 -0.0619 0.6820 1.0000
2.500 0.5929 0.00982 0.00380 -0.0605 0.6613 1.0000
2.750 0.6149 0.00994 0.00382 -0.0591 0.6395 1.0000
3.000 0.6365 0.01008 0.00389 -0.0576 0.6146 1.0000
3.250 0.6576 0.01025 0.00396 -0.0560 0.5863 1.0000
3.500 0.6779 0.01047 0.00403 -0.0543 0.5522 1.0000
3.750 0.6972 0.01075 0.00414 -0.0525 0.5091 1.0000
4.000 0.7136 0.01119 0.00430 -0.0502 0.4473 1.0000
4.250 0.7266 0.01191 0.00456 -0.0474 0.3671 1.0000
4.500 0.7405 0.01269 0.00495 -0.0450 0.3087 1.0000
4.750 0.7575 0.01335 0.00537 -0.0431 0.2772 1.0000
5.000 0.7761 0.01394 0.00582 -0.0415 0.2571 1.0000
5.250 0.7958 0.01449 0.00626 -0.0401 0.2423 1.0000
5.500 0.8161 0.01503 0.00673 -0.0388 0.2301 1.0000
5.750 0.8365 0.01562 0.00721 -0.0375 0.2197 1.0000
6.000 0.8579 0.01610 0.00767 -0.0364 0.2098 1.0000
6.250 0.8795 0.01662 0.00818 -0.0353 0.2012 1.0000
6.500 0.9010 0.01719 0.00868 -0.0343 0.1939 1.0000
6.750 0.9233 0.01773 0.00925 -0.0334 0.1870 1.0000
7.000 0.9455 0.01826 0.00977 -0.0325 0.1809 1.0000
7.250 0.9682 0.01897 0.01045 -0.0317 0.1753 1.0000
7.500 0.9905 0.01944 0.01100 -0.0308 0.1695 1.0000
7.750 1.0131 0.02010 0.01161 -0.0301 0.1645 1.0000
8.000 1.0360 0.02078 0.01237 -0.0294 0.1600 1.0000
8.250 1.0585 0.02136 0.01304 -0.0285 0.1556 1.0000
8.500 1.0816 0.02201 0.01369 -0.0279 0.1519 1.0000
8.750 1.1067 0.02306 0.01471 -0.0277 0.1481 1.0000
9.000 1.1273 0.02360 0.01546 -0.0266 0.1446 1.0000
9.250 1.1490 0.02425 0.01621 -0.0257 0.1408 1.0000
9.500 1.1719 0.02499 0.01697 -0.0251 0.1377 1.0000
9.750 1.1980 0.02637 0.01833 -0.0253 0.1345 1.0000
10.000 1.2169 0.02705 0.01927 -0.0239 0.1320 1.0000
10.250 1.2359 0.02778 0.02018 -0.0227 0.1287 1.0000
10.500 1.2560 0.02852 0.02102 -0.0217 0.1256 1.0000
10.750 1.2782 0.02935 0.02180 -0.0213 0.1221 1.0000
11.000 1.2915 0.03006 0.02273 -0.0194 0.1182 1.0000
11.250 1.3021 0.03015 0.02295 -0.0170 0.1134 1.0000
11.500 1.3168 0.03035 0.02307 -0.0154 0.1089 1.0000
11.750 1.3270 0.03113 0.02404 -0.0132 0.1054 1.0000
12.000 1.3317 0.03152 0.02462 -0.0100 0.1019 1.0000
12.250 1.3388 0.03188 0.02503 -0.0073 0.0985 1.0000
12.500 1.3496 0.03263 0.02572 -0.0056 0.0946 1.0000
12.750 1.3496 0.03329 0.02667 -0.0025 0.0915 1.0000
13.000 1.3533 0.03397 0.02749 -0.0002 0.0876 1.0000
13.250 1.3571 0.03468 0.02821 0.0018 0.0838 1.0000
13.500 1.3597 0.03584 0.02960 0.0036 0.0796 1.0000
13.750 1.3623 0.03686 0.03078 0.0049 0.0740 1.0000
14.000 1.3645 0.03827 0.03234 0.0060 0.0669 1.0000
14.250 1.3663 0.04001 0.03416 0.0066 0.0548 1.0000
14.500 1.3576 0.04318 0.03726 0.0071 0.0425 1.0000
14.750 1.3472 0.04682 0.04098 0.0074 0.0367 1.0000
15.000 1.3300 0.05148 0.04567 0.0069 0.0332 1.0000
15.250 1.3194 0.05569 0.05005 0.0062 0.0311 1.0000
15.500 1.3060 0.06052 0.05504 0.0049 0.0295 1.0000
15.750 1.2887 0.06624 0.06090 0.0028 0.0283 1.0000
16.000 1.2716 0.07233 0.06713 0.0001 0.0277 1.0000
16.250 1.2542 0.07880 0.07374 -0.0029 0.0274 1.0000
16.500 1.2321 0.08643 0.08150 -0.0068 0.0269 1.0000
16.750 1.2131 0.09380 0.08901 -0.0106 0.0266 1.0000
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