DF 101 AIRFOIL (df101-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: DF 101 AIRFOIL (df101-il) Reynolds number: 100,000 Max Cl/Cd: 49.6 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-df101-il-100000-n5.txt Download as CSV file: xf-df101-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DF 101 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4728 0.09301 0.08789 -0.0357 1.0000 0.0242
-10.250 -0.4822 0.08667 0.08162 -0.0386 1.0000 0.0239
-10.000 -0.4986 0.07858 0.07362 -0.0428 1.0000 0.0233
-9.750 -0.5374 0.06515 0.06018 -0.0529 1.0000 0.0223
-9.500 -0.5803 0.05639 0.05124 -0.0601 1.0000 0.0216
-9.250 -0.6127 0.05201 0.04663 -0.0587 1.0000 0.0212
-9.000 -0.6281 0.04873 0.04314 -0.0566 1.0000 0.0213
-8.750 -0.6386 0.04567 0.03982 -0.0540 1.0000 0.0213
-8.500 -0.6442 0.04295 0.03683 -0.0513 1.0000 0.0214
-8.250 -0.6459 0.04047 0.03409 -0.0484 1.0000 0.0216
-8.000 -0.6443 0.03812 0.03147 -0.0457 1.0000 0.0219
-7.750 -0.6397 0.03593 0.02899 -0.0431 1.0000 0.0223
-7.500 -0.6324 0.03388 0.02666 -0.0406 1.0000 0.0227
-7.250 -0.6227 0.03194 0.02444 -0.0383 1.0000 0.0234
-7.000 -0.6110 0.03017 0.02237 -0.0361 1.0000 0.0241
-6.750 -0.5930 0.02858 0.02043 -0.0349 0.9988 0.0257
-6.500 -0.5627 0.02678 0.01847 -0.0364 0.9940 0.0280
-6.250 -0.5328 0.02537 0.01692 -0.0375 0.9887 0.0303
-6.000 -0.5007 0.02396 0.01531 -0.0387 0.9839 0.0328
-5.750 -0.4717 0.02268 0.01391 -0.0395 0.9781 0.0365
-5.500 -0.4396 0.02172 0.01281 -0.0408 0.9726 0.0422
-5.250 -0.4088 0.02066 0.01168 -0.0419 0.9671 0.0492
-5.000 -0.3784 0.01971 0.01066 -0.0427 0.9607 0.0602
-4.750 -0.3442 0.01862 0.00971 -0.0445 0.9563 0.0890
-4.500 -0.3169 0.01781 0.00915 -0.0448 0.9488 0.1482
-4.250 -0.2817 0.01741 0.00886 -0.0466 0.9437 0.2021
-4.000 -0.2502 0.01717 0.00868 -0.0475 0.9371 0.2452
-3.750 -0.2172 0.01695 0.00848 -0.0487 0.9308 0.2836
-3.500 -0.1817 0.01669 0.00817 -0.0502 0.9258 0.3103
-3.250 -0.1534 0.01642 0.00791 -0.0503 0.9175 0.3306
-3.000 -0.1175 0.01613 0.00759 -0.0518 0.9126 0.3544
-2.750 -0.0910 0.01587 0.00736 -0.0515 0.9035 0.3767
-2.500 -0.0566 0.01555 0.00709 -0.0526 0.8980 0.4058
-2.250 -0.0304 0.01530 0.00692 -0.0522 0.8886 0.4373
-2.000 0.0028 0.01495 0.00669 -0.0530 0.8828 0.4806
-1.750 0.0278 0.01468 0.00659 -0.0522 0.8728 0.5316
-1.500 0.0582 0.01433 0.00645 -0.0523 0.8657 0.5981
-1.250 0.0843 0.01402 0.00637 -0.0514 0.8564 0.6743
-1.000 0.1149 0.01373 0.00637 -0.0510 0.8483 0.7631
-0.750 0.1634 0.01357 0.00637 -0.0541 0.8417 0.8600
-0.500 0.2111 0.01352 0.00627 -0.0575 0.8338 0.9199
-0.250 0.2567 0.01345 0.00611 -0.0606 0.8252 0.9560
0.000 0.3051 0.01338 0.00595 -0.0646 0.8144 0.9806
0.250 0.3546 0.01325 0.00573 -0.0689 0.8030 1.0000
0.500 0.3776 0.01321 0.00560 -0.0677 0.7888 1.0000
0.750 0.4006 0.01318 0.00548 -0.0666 0.7738 1.0000
1.000 0.4235 0.01317 0.00538 -0.0653 0.7577 1.0000
1.250 0.4466 0.01318 0.00530 -0.0641 0.7413 1.0000
1.500 0.4698 0.01320 0.00524 -0.0629 0.7249 1.0000
1.750 0.4932 0.01325 0.00520 -0.0618 0.7085 1.0000
2.000 0.5167 0.01332 0.00519 -0.0606 0.6923 1.0000
2.250 0.5397 0.01341 0.00523 -0.0595 0.6752 1.0000
2.500 0.5626 0.01353 0.00529 -0.0583 0.6577 1.0000
2.750 0.5854 0.01366 0.00536 -0.0571 0.6396 1.0000
3.000 0.6083 0.01380 0.00544 -0.0559 0.6212 1.0000
3.250 0.6311 0.01397 0.00555 -0.0547 0.6023 1.0000
3.500 0.6532 0.01415 0.00570 -0.0535 0.5816 1.0000
3.750 0.6756 0.01435 0.00583 -0.0522 0.5605 1.0000
4.000 0.6975 0.01458 0.00601 -0.0509 0.5375 1.0000
4.250 0.7193 0.01483 0.00620 -0.0496 0.5142 1.0000
4.500 0.7406 0.01511 0.00642 -0.0483 0.4885 1.0000
4.750 0.7616 0.01542 0.00667 -0.0469 0.4616 1.0000
5.000 0.7823 0.01578 0.00693 -0.0455 0.4341 1.0000
5.250 0.8026 0.01618 0.00726 -0.0441 0.4066 1.0000
5.500 0.8225 0.01662 0.00761 -0.0427 0.3803 1.0000
5.750 0.8423 0.01710 0.00800 -0.0413 0.3556 1.0000
6.000 0.8622 0.01761 0.00843 -0.0399 0.3330 1.0000
6.250 0.8819 0.01814 0.00892 -0.0386 0.3131 1.0000
6.500 0.9015 0.01869 0.00942 -0.0373 0.2956 1.0000
6.750 0.9213 0.01925 0.00996 -0.0360 0.2797 1.0000
7.000 0.9411 0.01983 0.01052 -0.0347 0.2655 1.0000
7.250 0.9607 0.02042 0.01112 -0.0335 0.2521 1.0000
7.500 0.9805 0.02100 0.01177 -0.0323 0.2397 1.0000
7.750 1.0002 0.02160 0.01243 -0.0310 0.2281 1.0000
8.000 1.0193 0.02224 0.01311 -0.0298 0.2173 1.0000
8.250 1.0377 0.02291 0.01380 -0.0284 0.2071 1.0000
8.500 1.0560 0.02356 0.01456 -0.0271 0.1962 1.0000
8.750 1.0739 0.02421 0.01533 -0.0257 0.1854 1.0000
9.000 1.0904 0.02491 0.01609 -0.0242 0.1745 1.0000
9.250 1.1054 0.02561 0.01686 -0.0225 0.1631 1.0000
9.500 1.1188 0.02630 0.01762 -0.0207 0.1494 1.0000
9.750 1.1307 0.02701 0.01840 -0.0187 0.1345 1.0000
10.000 1.1410 0.02779 0.01926 -0.0165 0.1194 1.0000
10.250 1.1506 0.02870 0.02022 -0.0143 0.1053 1.0000
10.500 1.1591 0.02977 0.02132 -0.0122 0.0917 1.0000
10.750 1.1657 0.03103 0.02261 -0.0100 0.0785 1.0000
11.000 1.1700 0.03253 0.02411 -0.0079 0.0665 1.0000
11.250 1.1722 0.03427 0.02587 -0.0057 0.0562 1.0000
11.500 1.1723 0.03624 0.02786 -0.0037 0.0492 1.0000
11.750 1.1710 0.03839 0.03008 -0.0019 0.0439 1.0000
12.000 1.1679 0.04081 0.03258 -0.0004 0.0410 1.0000
12.250 1.1662 0.04326 0.03520 0.0008 0.0382 1.0000
12.500 1.1630 0.04596 0.03807 0.0017 0.0363 1.0000
12.750 1.1577 0.04901 0.04124 0.0022 0.0347 1.0000
13.000 1.1495 0.05255 0.04485 0.0023 0.0335 1.0000
13.250 1.1454 0.05588 0.04836 0.0021 0.0321 1.0000
13.500 1.1410 0.05940 0.05206 0.0017 0.0308 1.0000
13.750 1.1352 0.06323 0.05606 0.0010 0.0299 1.0000
14.000 1.1290 0.06726 0.06024 0.0000 0.0290 1.0000
14.250 1.1217 0.07164 0.06477 -0.0015 0.0281 1.0000
14.500 1.1133 0.07637 0.06962 -0.0033 0.0273 1.0000
14.750 1.1052 0.08120 0.07456 -0.0051 0.0267 1.0000
15.000 1.0982 0.08597 0.07945 -0.0069 0.0263 1.0000
15.250 1.0923 0.09062 0.08419 -0.0087 0.0259 1.0000
15.500 1.0854 0.09568 0.08939 -0.0107 0.0255 1.0000
15.750 1.0764 0.10144 0.09535 -0.0134 0.0252 1.0000
16.000 1.0669 0.10750 0.10159 -0.0164 0.0250 1.0000
16.250 1.0556 0.11411 0.10839 -0.0199 0.0248 1.0000
16.500 1.0420 0.12151 0.11596 -0.0239 0.0247 1.0000
16.750 1.0269 0.12955 0.12418 -0.0286 0.0247 1.0000
17.000 1.0084 0.13883 0.13363 -0.0340 0.0247 1.0000
17.250 0.9869 0.14937 0.14431 -0.0402 0.0249 1.0000
17.500 0.9594 0.16252 0.15756 -0.0478 0.0251 1.0000
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