DF102 (df102-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: DF102 (df102-il) Reynolds number: 500,000 Max Cl/Cd: 75.39 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-df102-il-500000-n5.txt Download as CSV file: xf-df102-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7242 0.08319 0.08039 -0.0377 1.0000 0.0066
-13.500 -0.7584 0.07308 0.07019 -0.0436 1.0000 0.0065
-13.250 -0.7916 0.06331 0.06030 -0.0498 1.0000 0.0064
-13.000 -0.8169 0.05467 0.05151 -0.0559 1.0000 0.0063
-12.750 -0.8393 0.04601 0.04266 -0.0633 1.0000 0.0063
-12.500 -0.8558 0.03957 0.03601 -0.0692 1.0000 0.0063
-12.250 -0.8726 0.03551 0.03175 -0.0707 1.0000 0.0064
-12.000 -0.8837 0.03319 0.02927 -0.0688 1.0000 0.0064
-11.750 -0.8936 0.03132 0.02725 -0.0653 1.0000 0.0064
-11.500 -0.8941 0.02962 0.02538 -0.0627 1.0000 0.0065
-11.250 -0.8930 0.02801 0.02359 -0.0598 1.0000 0.0066
-11.000 -0.8888 0.02668 0.02211 -0.0570 1.0000 0.0067
-10.750 -0.8845 0.02552 0.02080 -0.0539 1.0000 0.0068
-10.500 -0.8629 0.02380 0.01888 -0.0545 0.9963 0.0070
-10.250 -0.8381 0.02240 0.01733 -0.0554 0.9921 0.0072
-10.000 -0.8112 0.02143 0.01626 -0.0562 0.9880 0.0075
-9.750 -0.7822 0.02055 0.01527 -0.0572 0.9848 0.0078
-9.500 -0.7526 0.01963 0.01424 -0.0583 0.9821 0.0081
-9.250 -0.7257 0.01880 0.01330 -0.0588 0.9774 0.0084
-9.000 -0.6966 0.01807 0.01245 -0.0595 0.9736 0.0089
-8.750 -0.6661 0.01731 0.01157 -0.0605 0.9705 0.0094
-8.500 -0.6397 0.01652 0.01070 -0.0607 0.9652 0.0100
-8.250 -0.6114 0.01596 0.01008 -0.0612 0.9602 0.0105
-8.000 -0.5820 0.01536 0.00941 -0.0618 0.9561 0.0111
-7.750 -0.5564 0.01486 0.00883 -0.0615 0.9496 0.0118
-7.500 -0.5296 0.01434 0.00823 -0.0614 0.9438 0.0125
-7.250 -0.5037 0.01384 0.00764 -0.0611 0.9380 0.0132
-7.000 -0.4789 0.01336 0.00712 -0.0606 0.9312 0.0143
-6.750 -0.4525 0.01298 0.00669 -0.0603 0.9257 0.0153
-6.500 -0.4273 0.01267 0.00631 -0.0597 0.9186 0.0166
-6.250 -0.4020 0.01223 0.00581 -0.0592 0.9123 0.0178
-6.000 -0.3769 0.01185 0.00538 -0.0587 0.9055 0.0192
-5.750 -0.3510 0.01154 0.00502 -0.0582 0.8987 0.0206
-5.500 -0.3249 0.01128 0.00470 -0.0577 0.8921 0.0221
-5.250 -0.2993 0.01093 0.00430 -0.0572 0.8847 0.0246
-5.000 -0.2731 0.01067 0.00400 -0.0568 0.8779 0.0272
-4.750 -0.2470 0.01038 0.00369 -0.0563 0.8700 0.0313
-4.500 -0.2208 0.01010 0.00340 -0.0558 0.8627 0.0388
-4.250 -0.1954 0.00972 0.00310 -0.0553 0.8543 0.0614
-4.000 -0.1702 0.00929 0.00283 -0.0548 0.8462 0.1031
-3.750 -0.1443 0.00901 0.00263 -0.0544 0.8375 0.1352
-3.500 -0.1178 0.00880 0.00248 -0.0541 0.8286 0.1595
-3.250 -0.0911 0.00864 0.00234 -0.0537 0.8195 0.1804
-3.000 -0.0645 0.00847 0.00222 -0.0534 0.8096 0.2057
-2.750 -0.0379 0.00831 0.00212 -0.0530 0.7997 0.2321
-2.500 -0.0111 0.00820 0.00203 -0.0527 0.7897 0.2550
-2.250 0.0158 0.00809 0.00194 -0.0524 0.7786 0.2731
-2.000 0.0427 0.00801 0.00185 -0.0520 0.7672 0.2894
-1.750 0.0693 0.00795 0.00177 -0.0516 0.7515 0.3047
-1.500 0.0955 0.00791 0.00169 -0.0511 0.7326 0.3208
-1.250 0.1217 0.00788 0.00162 -0.0506 0.7127 0.3396
-0.750 0.1737 0.00781 0.00152 -0.0496 0.6738 0.3856
-0.500 0.1996 0.00777 0.00149 -0.0491 0.6558 0.4138
0.000 0.2505 0.00765 0.00148 -0.0480 0.6173 0.4964
0.250 0.2753 0.00758 0.00149 -0.0473 0.5979 0.5467
0.500 0.3000 0.00750 0.00151 -0.0466 0.5784 0.6028
0.750 0.3243 0.00743 0.00155 -0.0458 0.5584 0.6563
1.000 0.3478 0.00734 0.00159 -0.0448 0.5393 0.7180
1.250 0.3701 0.00722 0.00167 -0.0434 0.5183 0.7939
1.500 0.3936 0.00722 0.00180 -0.0420 0.4917 0.8784
1.750 0.4239 0.00740 0.00193 -0.0423 0.4591 0.9251
2.000 0.4570 0.00771 0.00205 -0.0435 0.4157 0.9483
2.250 0.4892 0.00813 0.00221 -0.0446 0.3584 0.9633
2.500 0.5210 0.00862 0.00240 -0.0457 0.2975 0.9738
2.750 0.5523 0.00905 0.00260 -0.0466 0.2544 0.9825
3.000 0.5875 0.00935 0.00277 -0.0484 0.2298 0.9881
3.250 0.6206 0.00960 0.00294 -0.0496 0.2144 0.9940
3.500 0.6559 0.00983 0.00309 -0.0514 0.2017 0.9992
3.750 0.6811 0.01003 0.00324 -0.0509 0.1924 1.0000
4.000 0.7034 0.01024 0.00341 -0.0498 0.1832 1.0000
4.250 0.7259 0.01044 0.00357 -0.0488 0.1754 1.0000
4.750 0.7710 0.01085 0.00392 -0.0467 0.1613 1.0000
5.000 0.7936 0.01107 0.00411 -0.0457 0.1552 1.0000
5.250 0.8163 0.01128 0.00431 -0.0447 0.1502 1.0000
5.500 0.8391 0.01149 0.00451 -0.0437 0.1450 1.0000
5.750 0.8615 0.01174 0.00474 -0.0427 0.1399 1.0000
6.000 0.8846 0.01196 0.00496 -0.0418 0.1358 1.0000
6.250 0.9074 0.01220 0.00520 -0.0409 0.1308 1.0000
6.500 0.9298 0.01248 0.00545 -0.0399 0.1257 1.0000
6.750 0.9528 0.01272 0.00572 -0.0390 0.1224 1.0000
7.000 0.9757 0.01297 0.00599 -0.0381 0.1189 1.0000
7.250 0.9982 0.01326 0.00628 -0.0372 0.1152 1.0000
7.500 1.0201 0.01359 0.00660 -0.0362 0.1115 1.0000
7.750 1.0428 0.01385 0.00691 -0.0353 0.1093 1.0000
8.000 1.0652 0.01413 0.00723 -0.0344 0.1064 1.0000
8.250 1.0871 0.01445 0.00756 -0.0334 0.1034 1.0000
8.500 1.1082 0.01481 0.00793 -0.0324 0.1002 1.0000
8.750 1.1289 0.01519 0.00834 -0.0312 0.0979 1.0000
9.000 1.1505 0.01550 0.00872 -0.0302 0.0963 1.0000
9.250 1.1716 0.01582 0.00910 -0.0292 0.0939 1.0000
9.500 1.1920 0.01618 0.00948 -0.0280 0.0909 1.0000
9.750 1.2112 0.01660 0.00990 -0.0267 0.0874 1.0000
10.000 1.2303 0.01700 0.01036 -0.0254 0.0848 1.0000
10.250 1.2498 0.01732 0.01073 -0.0241 0.0816 1.0000
10.500 1.2669 0.01772 0.01113 -0.0225 0.0770 1.0000
10.750 1.2830 0.01817 0.01160 -0.0208 0.0728 1.0000
11.000 1.3000 0.01858 0.01204 -0.0192 0.0678 1.0000
11.250 1.3149 0.01913 0.01258 -0.0174 0.0630 1.0000
11.500 1.3307 0.01963 0.01314 -0.0158 0.0589 1.0000
11.750 1.3446 0.02027 0.01378 -0.0140 0.0532 1.0000
12.000 1.3565 0.02105 0.01453 -0.0121 0.0444 1.0000
12.250 1.3654 0.02206 0.01550 -0.0100 0.0349 1.0000
12.500 1.3697 0.02342 0.01680 -0.0075 0.0237 1.0000
12.750 1.3739 0.02483 0.01821 -0.0051 0.0173 1.0000
13.000 1.3806 0.02608 0.01952 -0.0032 0.0141 1.0000
13.250 1.3869 0.02741 0.02091 -0.0014 0.0120 1.0000
13.500 1.3923 0.02885 0.02243 0.0003 0.0103 1.0000
13.750 1.3980 0.03031 0.02398 0.0018 0.0093 1.0000
14.000 1.4033 0.03185 0.02562 0.0031 0.0085 1.0000
14.250 1.4069 0.03361 0.02748 0.0044 0.0078 1.0000
14.500 1.4072 0.03574 0.02971 0.0055 0.0070 1.0000
14.750 1.4101 0.03773 0.03181 0.0062 0.0067 1.0000
15.000 1.4110 0.04001 0.03421 0.0068 0.0063 1.0000
15.250 1.4098 0.04263 0.03695 0.0072 0.0059 1.0000
15.500 1.4072 0.04551 0.03995 0.0072 0.0057 1.0000
15.750 1.4006 0.04902 0.04359 0.0069 0.0054 1.0000
16.000 1.3927 0.05292 0.04762 0.0061 0.0052 1.0000
16.250 1.3834 0.05723 0.05206 0.0049 0.0050 1.0000
16.500 1.3730 0.06195 0.05694 0.0033 0.0048 1.0000
16.750 1.3589 0.06750 0.06266 0.0010 0.0048 1.0000
17.000 1.3410 0.07402 0.06934 -0.0020 0.0048 1.0000
17.250 1.3210 0.08127 0.07677 -0.0056 0.0047 1.0000
17.500 1.2919 0.09061 0.08630 -0.0105 0.0049 1.0000
17.750 1.2567 0.10165 0.09755 -0.0164 0.0050 1.0000
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