DF102 (df102-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: DF102 (df102-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.45 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-df102-il-1000000.txt Download as CSV file: xf-df102-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7848 0.07161 0.06938 -0.0446 1.0000 0.0072
-13.500 -0.8107 0.06293 0.06057 -0.0503 1.0000 0.0072
-13.250 -0.8403 0.05328 0.05077 -0.0576 1.0000 0.0072
-13.000 -0.7982 0.05681 0.05440 -0.0544 1.0000 0.0069
-12.750 -0.8459 0.04312 0.04038 -0.0669 1.0000 0.0070
-12.500 -0.8799 0.03556 0.03253 -0.0728 1.0000 0.0071
-12.250 -0.8635 0.03519 0.03217 -0.0724 1.0000 0.0070
-12.000 -0.9128 0.03054 0.02719 -0.0674 1.0000 0.0072
-11.750 -0.9184 0.02859 0.02508 -0.0642 1.0000 0.0072
-11.500 -0.9198 0.02683 0.02317 -0.0611 1.0000 0.0073
-11.250 -0.9155 0.02577 0.02204 -0.0581 1.0000 0.0075
-11.000 -0.9149 0.02481 0.02100 -0.0542 1.0000 0.0076
-10.750 -0.8993 0.02376 0.01985 -0.0531 0.9991 0.0077
-10.500 -0.8698 0.02282 0.01882 -0.0545 0.9970 0.0079
-10.250 -0.8413 0.02150 0.01735 -0.0559 0.9947 0.0081
-10.000 -0.8136 0.02032 0.01603 -0.0569 0.9922 0.0083
-9.750 -0.7850 0.01935 0.01495 -0.0578 0.9892 0.0086
-9.500 -0.7555 0.01830 0.01377 -0.0589 0.9868 0.0089
-9.250 -0.7244 0.01739 0.01275 -0.0601 0.9849 0.0091
-9.000 -0.6920 0.01664 0.01190 -0.0615 0.9835 0.0094
-8.750 -0.6657 0.01532 0.01043 -0.0619 0.9798 0.0097
-8.500 -0.6382 0.01436 0.00939 -0.0624 0.9757 0.0102
-8.250 -0.6073 0.01387 0.00888 -0.0633 0.9725 0.0107
-8.000 -0.5770 0.01339 0.00835 -0.0640 0.9690 0.0112
-7.750 -0.5516 0.01302 0.00793 -0.0635 0.9626 0.0119
-7.500 -0.5236 0.01273 0.00758 -0.0635 0.9576 0.0124
-7.250 -0.5019 0.01193 0.00669 -0.0625 0.9506 0.0132
-7.000 -0.4776 0.01149 0.00622 -0.0617 0.9443 0.0139
-6.750 -0.4523 0.01118 0.00587 -0.0612 0.9384 0.0148
-6.500 -0.4273 0.01089 0.00552 -0.0605 0.9319 0.0157
-6.250 -0.4018 0.01057 0.00514 -0.0599 0.9261 0.0165
-6.000 -0.3780 0.01004 0.00456 -0.0591 0.9192 0.0180
-5.750 -0.3521 0.00978 0.00426 -0.0585 0.9131 0.0195
-5.500 -0.3257 0.00959 0.00403 -0.0581 0.9068 0.0207
-5.250 -0.3006 0.00917 0.00356 -0.0574 0.9000 0.0232
-5.000 -0.2742 0.00893 0.00328 -0.0570 0.8936 0.0252
-4.750 -0.2478 0.00870 0.00302 -0.0566 0.8864 0.0277
-4.500 -0.2215 0.00843 0.00273 -0.0561 0.8797 0.0332
-4.250 -0.1963 0.00797 0.00241 -0.0555 0.8719 0.0624
-4.000 -0.1719 0.00745 0.00213 -0.0549 0.8645 0.1239
-3.750 -0.1457 0.00718 0.00199 -0.0545 0.8562 0.1586
-3.500 -0.1189 0.00701 0.00186 -0.0542 0.8484 0.1824
-3.250 -0.0919 0.00687 0.00175 -0.0539 0.8395 0.2032
-3.000 -0.0647 0.00675 0.00166 -0.0536 0.8307 0.2214
-2.750 -0.0377 0.00665 0.00157 -0.0533 0.8214 0.2394
-2.500 -0.0106 0.00654 0.00149 -0.0530 0.8096 0.2591
-2.000 0.0427 0.00636 0.00134 -0.0522 0.7801 0.3033
-1.750 0.0695 0.00630 0.00128 -0.0519 0.7646 0.3243
-1.500 0.0962 0.00624 0.00122 -0.0515 0.7490 0.3455
-1.250 0.1228 0.00618 0.00117 -0.0511 0.7328 0.3696
-1.000 0.1493 0.00611 0.00113 -0.0507 0.7172 0.3996
-0.750 0.1754 0.00603 0.00111 -0.0503 0.7003 0.4375
-0.500 0.2013 0.00592 0.00109 -0.0498 0.6835 0.4865
-0.250 0.2269 0.00580 0.00108 -0.0493 0.6673 0.5448
0.000 0.2523 0.00569 0.00109 -0.0487 0.6505 0.6036
0.250 0.2773 0.00556 0.00111 -0.0480 0.6347 0.6661
0.500 0.3016 0.00542 0.00113 -0.0471 0.6197 0.7326
0.750 0.3243 0.00524 0.00118 -0.0458 0.6039 0.8166
1.000 0.3472 0.00517 0.00128 -0.0443 0.5859 0.8976
1.250 0.3745 0.00526 0.00136 -0.0439 0.5667 0.9348
1.500 0.4039 0.00539 0.00142 -0.0440 0.5446 0.9558
1.750 0.4359 0.00557 0.00150 -0.0448 0.5186 0.9691
2.000 0.4727 0.00578 0.00158 -0.0467 0.4881 0.9764
2.250 0.5058 0.00607 0.00168 -0.0479 0.4461 0.9832
2.500 0.5429 0.00646 0.00181 -0.0501 0.3889 0.9867
2.750 0.5765 0.00694 0.00199 -0.0516 0.3227 0.9911
3.000 0.6103 0.00742 0.00218 -0.0531 0.2657 0.9950
3.250 0.6466 0.00773 0.00234 -0.0551 0.2358 0.9979
3.500 0.6819 0.00797 0.00247 -0.0569 0.2168 1.0000
3.750 0.7038 0.00816 0.00260 -0.0557 0.2039 1.0000
4.000 0.7256 0.00837 0.00274 -0.0545 0.1919 1.0000
4.250 0.7482 0.00852 0.00287 -0.0534 0.1837 1.0000
4.500 0.7704 0.00871 0.00301 -0.0523 0.1755 1.0000
4.750 0.7929 0.00889 0.00316 -0.0512 0.1682 1.0000
5.000 0.8153 0.00908 0.00332 -0.0501 0.1614 1.0000
5.250 0.8382 0.00925 0.00347 -0.0491 0.1554 1.0000
5.500 0.8604 0.00948 0.00366 -0.0480 0.1485 1.0000
5.750 0.8839 0.00963 0.00382 -0.0471 0.1443 1.0000
6.000 0.9065 0.00986 0.00401 -0.0461 0.1381 1.0000
6.250 0.9294 0.01007 0.00421 -0.0451 0.1332 1.0000
6.500 0.9527 0.01025 0.00440 -0.0442 0.1292 1.0000
6.750 0.9753 0.01050 0.00462 -0.0432 0.1243 1.0000
7.000 0.9981 0.01075 0.00487 -0.0423 0.1201 1.0000
7.250 1.0217 0.01094 0.00508 -0.0415 0.1173 1.0000
7.500 1.0448 0.01118 0.00531 -0.0406 0.1136 1.0000
7.750 1.0666 0.01151 0.00562 -0.0395 0.1088 1.0000
8.000 1.0899 0.01173 0.00588 -0.0387 0.1065 1.0000
8.250 1.1133 0.01195 0.00613 -0.0379 0.1044 1.0000
8.500 1.1361 0.01221 0.00640 -0.0371 0.1018 1.0000
8.750 1.1581 0.01252 0.00670 -0.0361 0.0981 1.0000
9.000 1.1793 0.01288 0.00706 -0.0350 0.0944 1.0000
9.250 1.2032 0.01304 0.00726 -0.0344 0.0920 1.0000
9.500 1.2257 0.01329 0.00751 -0.0336 0.0885 1.0000
9.750 1.2464 0.01366 0.00787 -0.0325 0.0842 1.0000
10.000 1.2681 0.01395 0.00819 -0.0315 0.0816 1.0000
10.250 1.2903 0.01418 0.00846 -0.0306 0.0789 1.0000
10.500 1.3109 0.01451 0.00878 -0.0295 0.0755 1.0000
10.750 1.3295 0.01495 0.00921 -0.0282 0.0708 1.0000
11.000 1.3506 0.01520 0.00952 -0.0271 0.0688 1.0000
11.250 1.3685 0.01555 0.00988 -0.0256 0.0649 1.0000
11.500 1.3835 0.01602 0.01032 -0.0236 0.0599 1.0000
11.750 1.3994 0.01643 0.01075 -0.0217 0.0547 1.0000
12.000 1.4117 0.01706 0.01133 -0.0195 0.0463 1.0000
12.250 1.4178 0.01809 0.01224 -0.0165 0.0332 1.0000
12.500 1.4184 0.01951 0.01356 -0.0130 0.0193 1.0000
12.750 1.4243 0.02065 0.01471 -0.0103 0.0142 1.0000
13.000 1.4313 0.02174 0.01584 -0.0079 0.0113 1.0000
13.250 1.4370 0.02296 0.01711 -0.0055 0.0095 1.0000
13.500 1.4464 0.02395 0.01817 -0.0037 0.0089 1.0000
13.750 1.4540 0.02510 0.01939 -0.0019 0.0080 1.0000
14.000 1.4582 0.02654 0.02090 0.0001 0.0073 1.0000
14.250 1.4622 0.02805 0.02251 0.0019 0.0067 1.0000
14.500 1.4684 0.02945 0.02400 0.0033 0.0064 1.0000
14.750 1.4745 0.03091 0.02553 0.0046 0.0061 1.0000
15.000 1.4767 0.03276 0.02748 0.0058 0.0058 1.0000
15.250 1.4775 0.03484 0.02965 0.0068 0.0055 1.0000
15.500 1.4747 0.03737 0.03229 0.0077 0.0053 1.0000
15.750 1.4626 0.04103 0.03610 0.0082 0.0050 1.0000
16.000 1.4644 0.04340 0.03857 0.0083 0.0048 1.0000
16.250 1.4616 0.04639 0.04166 0.0081 0.0048 1.0000
16.500 1.4530 0.05029 0.04569 0.0075 0.0048 1.0000
16.750 1.4444 0.05441 0.04994 0.0065 0.0047 1.0000
17.000 1.4320 0.05928 0.05494 0.0049 0.0046 1.0000
17.250 1.4200 0.06439 0.06019 0.0030 0.0045 1.0000
17.500 1.4032 0.07049 0.06643 0.0003 0.0045 1.0000
17.750 1.3778 0.07842 0.07453 -0.0035 0.0045 1.0000
18.000 1.3481 0.08756 0.08385 -0.0081 0.0046 1.0000
18.250 1.3134 0.09818 0.09467 -0.0137 0.0046 1.0000
18.500 1.2623 0.11236 0.10906 -0.0212 0.0049 1.0000
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