DF102 (df102-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: DF102 (df102-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.02 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-df102-il-1000000-n5.txt Download as CSV file: xf-df102-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.8460 0.08867 0.08628 -0.0356 1.0000 0.0043
-15.250 -0.8786 0.07936 0.07688 -0.0408 1.0000 0.0043
-15.000 -0.9407 0.06557 0.06291 -0.0492 1.0000 0.0042
-14.750 -0.9784 0.05554 0.05274 -0.0557 1.0000 0.0041
-14.500 -1.0231 0.04263 0.03957 -0.0663 1.0000 0.0040
-14.250 -1.0349 0.03643 0.03319 -0.0722 1.0000 0.0041
-14.000 -1.0506 0.03215 0.02874 -0.0744 1.0000 0.0040
-13.750 -1.0572 0.02995 0.02641 -0.0732 1.0000 0.0041
-13.500 -1.0610 0.02844 0.02480 -0.0706 1.0000 0.0042
-13.250 -1.0639 0.02710 0.02335 -0.0673 1.0000 0.0042
-13.000 -1.0583 0.02586 0.02199 -0.0651 1.0000 0.0043
-12.750 -1.0489 0.02483 0.02087 -0.0631 1.0000 0.0043
-12.500 -1.0392 0.02381 0.01976 -0.0610 1.0000 0.0044
-12.250 -1.0275 0.02295 0.01881 -0.0589 1.0000 0.0045
-12.000 -1.0161 0.02214 0.01790 -0.0567 1.0000 0.0045
-11.750 -0.9903 0.02111 0.01675 -0.0575 0.9968 0.0046
-11.500 -0.9643 0.02024 0.01579 -0.0580 0.9924 0.0047
-11.250 -0.9405 0.01895 0.01436 -0.0585 0.9878 0.0048
-11.000 -0.9129 0.01795 0.01324 -0.0594 0.9847 0.0050
-10.750 -0.8844 0.01714 0.01235 -0.0602 0.9814 0.0052
-10.500 -0.8564 0.01651 0.01166 -0.0607 0.9768 0.0055
-10.250 -0.8274 0.01582 0.01089 -0.0615 0.9725 0.0056
-10.000 -0.7984 0.01527 0.01028 -0.0622 0.9680 0.0058
-9.750 -0.7719 0.01475 0.00969 -0.0622 0.9615 0.0061
-9.500 -0.7449 0.01423 0.00909 -0.0623 0.9558 0.0063
-9.250 -0.7205 0.01377 0.00856 -0.0617 0.9486 0.0065
-9.000 -0.6954 0.01337 0.00807 -0.0613 0.9420 0.0067
-8.750 -0.6709 0.01296 0.00760 -0.0607 0.9353 0.0069
-8.500 -0.6469 0.01249 0.00706 -0.0601 0.9284 0.0074
-8.250 -0.6219 0.01215 0.00669 -0.0596 0.9222 0.0079
-8.000 -0.5966 0.01184 0.00634 -0.0591 0.9156 0.0084
-7.750 -0.5710 0.01156 0.00600 -0.0586 0.9097 0.0091
-7.500 -0.5454 0.01127 0.00566 -0.0581 0.9031 0.0095
-7.250 -0.5199 0.01095 0.00530 -0.0576 0.8968 0.0104
-7.000 -0.4938 0.01069 0.00502 -0.0572 0.8905 0.0112
-6.750 -0.4677 0.01045 0.00473 -0.0568 0.8837 0.0121
-6.500 -0.4411 0.01024 0.00447 -0.0565 0.8774 0.0128
-6.250 -0.4150 0.00997 0.00416 -0.0561 0.8701 0.0138
-6.000 -0.3886 0.00974 0.00390 -0.0557 0.8634 0.0149
-5.750 -0.3618 0.00955 0.00368 -0.0554 0.8556 0.0161
-5.500 -0.3350 0.00939 0.00346 -0.0551 0.8482 0.0170
-5.250 -0.3084 0.00915 0.00319 -0.0548 0.8399 0.0183
-5.000 -0.2816 0.00896 0.00297 -0.0544 0.8318 0.0198
-4.750 -0.2548 0.00879 0.00277 -0.0541 0.8228 0.0214
-4.500 -0.2278 0.00862 0.00256 -0.0538 0.8138 0.0240
-4.250 -0.2010 0.00845 0.00237 -0.0535 0.8046 0.0278
-4.000 -0.1744 0.00824 0.00218 -0.0532 0.7942 0.0381
-3.750 -0.1482 0.00796 0.00197 -0.0528 0.7841 0.0617
-3.500 -0.1223 0.00767 0.00177 -0.0524 0.7736 0.0963
-3.250 -0.0959 0.00746 0.00163 -0.0520 0.7625 0.1253
-3.000 -0.0691 0.00731 0.00152 -0.0518 0.7508 0.1476
-2.750 -0.0423 0.00717 0.00143 -0.0515 0.7393 0.1705
-2.500 -0.0156 0.00710 0.00135 -0.0511 0.7229 0.1878
-2.250 0.0104 0.00703 0.00128 -0.0507 0.7018 0.2143
-2.000 0.0369 0.00699 0.00123 -0.0503 0.6804 0.2354
-1.750 0.0635 0.00698 0.00118 -0.0499 0.6597 0.2497
-1.500 0.0901 0.00698 0.00114 -0.0496 0.6397 0.2671
-1.250 0.1170 0.00697 0.00111 -0.0493 0.6213 0.2811
-1.000 0.1439 0.00699 0.00109 -0.0490 0.6021 0.2939
-0.750 0.1706 0.00701 0.00107 -0.0487 0.5831 0.3089
-0.500 0.1975 0.00702 0.00106 -0.0484 0.5650 0.3252
-0.250 0.2240 0.00706 0.00107 -0.0481 0.5419 0.3437
0.000 0.2504 0.00709 0.00108 -0.0477 0.5187 0.3649
0.250 0.2770 0.00711 0.00109 -0.0474 0.4997 0.3889
0.500 0.3030 0.00713 0.00112 -0.0470 0.4763 0.4203
0.750 0.3285 0.00719 0.00116 -0.0466 0.4453 0.4547
1.000 0.3536 0.00726 0.00122 -0.0461 0.4122 0.4971
1.250 0.3779 0.00737 0.00131 -0.0454 0.3723 0.5454
1.500 0.4015 0.00756 0.00143 -0.0447 0.3225 0.5901
1.750 0.4245 0.00778 0.00157 -0.0438 0.2718 0.6379
2.000 0.4482 0.00788 0.00170 -0.0430 0.2414 0.6912
2.250 0.4717 0.00788 0.00181 -0.0421 0.2231 0.7544
2.500 0.4935 0.00778 0.00193 -0.0407 0.2106 0.8392
2.750 0.5170 0.00777 0.00208 -0.0395 0.2004 0.9092
3.000 0.5454 0.00789 0.00220 -0.0395 0.1911 0.9416
3.250 0.5782 0.00806 0.00233 -0.0405 0.1809 0.9596
3.500 0.6109 0.00823 0.00246 -0.0416 0.1719 0.9703
3.750 0.6455 0.00841 0.00259 -0.0431 0.1630 0.9774
4.000 0.6780 0.00859 0.00273 -0.0442 0.1555 0.9835
4.250 0.7127 0.00876 0.00286 -0.0457 0.1497 0.9875
4.500 0.7475 0.00894 0.00302 -0.0473 0.1435 0.9941
4.750 0.7896 0.00915 0.00319 -0.0505 0.1373 1.0000
5.000 0.8126 0.00930 0.00333 -0.0495 0.1333 1.0000
5.250 0.8352 0.00948 0.00348 -0.0485 0.1285 1.0000
5.500 0.8581 0.00966 0.00364 -0.0475 0.1238 1.0000
5.750 0.8813 0.00983 0.00381 -0.0466 0.1199 1.0000
6.000 0.9044 0.01003 0.00398 -0.0456 0.1158 1.0000
6.250 0.9272 0.01024 0.00417 -0.0447 0.1114 1.0000
6.500 0.9507 0.01041 0.00435 -0.0438 0.1092 1.0000
6.750 0.9741 0.01060 0.00456 -0.0429 0.1063 1.0000
7.000 0.9972 0.01082 0.00477 -0.0421 0.1031 1.0000
7.250 1.0201 0.01106 0.00499 -0.0412 0.0993 1.0000
7.500 1.0436 0.01127 0.00522 -0.0404 0.0970 1.0000
7.750 1.0671 0.01148 0.00545 -0.0396 0.0947 1.0000
8.000 1.0902 0.01172 0.00570 -0.0388 0.0924 1.0000
8.250 1.1131 0.01198 0.00596 -0.0379 0.0899 1.0000
8.500 1.1352 0.01228 0.00626 -0.0370 0.0858 1.0000
8.750 1.1585 0.01250 0.00652 -0.0362 0.0845 1.0000
9.000 1.1811 0.01277 0.00679 -0.0353 0.0809 1.0000
9.250 1.2027 0.01310 0.00709 -0.0344 0.0765 1.0000
9.500 1.2243 0.01341 0.00742 -0.0334 0.0736 1.0000
9.750 1.2465 0.01368 0.00772 -0.0325 0.0706 1.0000
10.000 1.2667 0.01406 0.00807 -0.0313 0.0651 1.0000
10.250 1.2869 0.01444 0.00844 -0.0302 0.0598 1.0000
10.500 1.3053 0.01491 0.00887 -0.0288 0.0531 1.0000
10.750 1.3235 0.01537 0.00932 -0.0273 0.0468 1.0000
11.000 1.3371 0.01604 0.00992 -0.0252 0.0371 1.0000
11.250 1.3468 0.01682 0.01065 -0.0224 0.0277 1.0000
11.500 1.3549 0.01770 0.01149 -0.0195 0.0187 1.0000
11.750 1.3652 0.01848 0.01228 -0.0170 0.0141 1.0000
12.000 1.3768 0.01921 0.01303 -0.0148 0.0115 1.0000
12.250 1.3881 0.01998 0.01382 -0.0126 0.0096 1.0000
12.500 1.4005 0.02069 0.01458 -0.0107 0.0085 1.0000
12.750 1.4108 0.02155 0.01548 -0.0087 0.0072 1.0000
13.000 1.4226 0.02233 0.01632 -0.0070 0.0064 1.0000
13.250 1.4319 0.02330 0.01734 -0.0051 0.0054 1.0000
13.500 1.4419 0.02424 0.01834 -0.0033 0.0049 1.0000
13.750 1.4514 0.02526 0.01942 -0.0017 0.0043 1.0000
14.000 1.4595 0.02640 0.02062 -0.0001 0.0040 1.0000
14.250 1.4666 0.02766 0.02194 0.0015 0.0036 1.0000
14.500 1.4732 0.02901 0.02337 0.0029 0.0033 1.0000
14.750 1.4796 0.03042 0.02486 0.0041 0.0031 1.0000
15.000 1.4847 0.03201 0.02652 0.0053 0.0030 1.0000
15.250 1.4883 0.03379 0.02839 0.0063 0.0028 1.0000
15.500 1.4920 0.03564 0.03033 0.0071 0.0028 1.0000
15.750 1.4914 0.03799 0.03277 0.0078 0.0025 1.0000
16.000 1.4923 0.04032 0.03520 0.0082 0.0025 1.0000
16.250 1.4888 0.04323 0.03821 0.0084 0.0023 1.0000
16.500 1.4843 0.04638 0.04147 0.0082 0.0022 1.0000
16.750 1.4797 0.04975 0.04496 0.0078 0.0022 1.0000
17.000 1.4727 0.05358 0.04890 0.0069 0.0022 1.0000
17.250 1.4643 0.05780 0.05324 0.0057 0.0022 1.0000
17.500 1.4526 0.06272 0.05830 0.0039 0.0022 1.0000
17.750 1.4372 0.06842 0.06414 0.0016 0.0022 1.0000
18.000 1.4195 0.07483 0.07069 -0.0013 0.0021 1.0000
18.250 1.3966 0.08244 0.07847 -0.0050 0.0021 1.0000
18.500 1.3615 0.09268 0.08891 -0.0103 0.0021 1.0000
18.750 1.3189 0.10495 0.10139 -0.0169 0.0022 1.0000
19.000 1.2658 0.11963 0.11630 -0.0248 0.0022 1.0000
|
Polar data table (+)
Polar graphs
<< Back to DF102 (df102-il)