DF102 (df102-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: DF102 (df102-il) Reynolds number: 500,000 Max Cl/Cd: 82.09 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-df102-il-500000.txt Download as CSV file: xf-df102-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5550 0.07820 0.07584 -0.0416 1.0000 0.0168
-11.000 -0.5622 0.07277 0.07041 -0.0439 1.0000 0.0155
-10.750 -0.5971 0.06059 0.05815 -0.0535 1.0000 0.0150
-10.500 -0.6270 0.05069 0.04807 -0.0641 1.0000 0.0148
-10.250 -0.7444 0.03843 0.03495 -0.0615 1.0000 0.0129
-10.000 -0.7574 0.03614 0.03242 -0.0572 1.0000 0.0128
-9.750 -0.7680 0.03412 0.03025 -0.0527 1.0000 0.0129
-9.500 -0.7753 0.03218 0.02811 -0.0483 1.0000 0.0130
-9.250 -0.7654 0.03004 0.02578 -0.0470 0.9987 0.0132
-9.000 -0.7390 0.02770 0.02319 -0.0488 0.9957 0.0134
-8.750 -0.7095 0.02615 0.02149 -0.0504 0.9931 0.0139
-8.500 -0.6834 0.02403 0.01910 -0.0513 0.9893 0.0142
-8.250 -0.6531 0.02251 0.01737 -0.0526 0.9864 0.0148
-8.000 -0.6206 0.02119 0.01584 -0.0542 0.9842 0.0155
-7.750 -0.5872 0.02054 0.01494 -0.0555 0.9817 0.0162
-7.500 -0.5627 0.01812 0.01238 -0.0557 0.9773 0.0170
-7.250 -0.5306 0.01706 0.01128 -0.0570 0.9745 0.0178
-7.000 -0.4963 0.01617 0.01032 -0.0586 0.9725 0.0188
-6.750 -0.4605 0.01535 0.00942 -0.0604 0.9710 0.0200
-6.500 -0.4297 0.01458 0.00855 -0.0611 0.9674 0.0211
-6.250 -0.4023 0.01359 0.00755 -0.0614 0.9623 0.0231
-6.000 -0.3698 0.01306 0.00697 -0.0624 0.9589 0.0251
-5.750 -0.3369 0.01252 0.00637 -0.0634 0.9559 0.0268
-5.500 -0.3145 0.01179 0.00559 -0.0623 0.9482 0.0295
-5.250 -0.2853 0.01140 0.00516 -0.0625 0.9433 0.0329
-5.000 -0.2602 0.01092 0.00464 -0.0617 0.9368 0.0373
-4.750 -0.2343 0.01052 0.00422 -0.0611 0.9301 0.0442
-4.500 -0.2114 0.00970 0.00370 -0.0602 0.9235 0.1022
-4.250 -0.1876 0.00921 0.00346 -0.0594 0.9158 0.1628
-4.000 -0.1614 0.00897 0.00329 -0.0589 0.9097 0.1941
-3.750 -0.1358 0.00879 0.00315 -0.0583 0.9015 0.2170
-3.500 -0.1090 0.00863 0.00300 -0.0578 0.8950 0.2361
-3.250 -0.0832 0.00848 0.00288 -0.0572 0.8864 0.2548
-3.000 -0.0565 0.00833 0.00275 -0.0568 0.8791 0.2768
-2.750 -0.0304 0.00817 0.00264 -0.0562 0.8702 0.2991
-2.500 -0.0039 0.00802 0.00253 -0.0558 0.8619 0.3248
-2.250 0.0224 0.00785 0.00241 -0.0553 0.8529 0.3473
-1.750 0.0748 0.00753 0.00219 -0.0542 0.8322 0.4017
-1.500 0.1002 0.00733 0.00207 -0.0535 0.8190 0.4410
-1.250 0.1252 0.00711 0.00198 -0.0527 0.8050 0.4932
-1.000 0.1497 0.00688 0.00191 -0.0518 0.7909 0.5585
-0.750 0.1736 0.00665 0.00187 -0.0508 0.7763 0.6282
-0.500 0.1970 0.00642 0.00184 -0.0496 0.7617 0.7006
-0.250 0.2194 0.00617 0.00184 -0.0481 0.7469 0.7856
0.000 0.2440 0.00604 0.00192 -0.0467 0.7315 0.8733
0.250 0.2751 0.00611 0.00198 -0.0468 0.7146 0.9249
0.500 0.3112 0.00621 0.00202 -0.0482 0.6988 0.9497
0.750 0.3484 0.00633 0.00206 -0.0499 0.6816 0.9655
1.000 0.3899 0.00645 0.00209 -0.0526 0.6638 0.9749
1.250 0.4298 0.00659 0.00212 -0.0550 0.6451 0.9836
1.500 0.4732 0.00671 0.00214 -0.0583 0.6239 0.9899
1.750 0.5145 0.00683 0.00215 -0.0611 0.6002 0.9960
2.000 0.5520 0.00697 0.00216 -0.0633 0.5735 1.0000
2.250 0.5739 0.00711 0.00220 -0.0620 0.5490 1.0000
2.500 0.5956 0.00728 0.00225 -0.0608 0.5210 1.0000
2.750 0.6165 0.00751 0.00232 -0.0594 0.4849 1.0000
3.000 0.6363 0.00782 0.00243 -0.0578 0.4383 1.0000
3.250 0.6545 0.00827 0.00259 -0.0560 0.3787 1.0000
3.500 0.6717 0.00882 0.00282 -0.0541 0.3138 1.0000
3.750 0.6901 0.00932 0.00306 -0.0524 0.2684 1.0000
4.000 0.7103 0.00968 0.00330 -0.0510 0.2433 1.0000
4.250 0.7313 0.01000 0.00352 -0.0497 0.2260 1.0000
4.500 0.7527 0.01029 0.00374 -0.0485 0.2126 1.0000
4.750 0.7745 0.01057 0.00396 -0.0473 0.2011 1.0000
5.000 0.7960 0.01087 0.00420 -0.0461 0.1912 1.0000
5.250 0.8185 0.01110 0.00442 -0.0450 0.1830 1.0000
5.500 0.8402 0.01140 0.00468 -0.0439 0.1755 1.0000
5.750 0.8627 0.01164 0.00492 -0.0429 0.1686 1.0000
6.000 0.8841 0.01199 0.00522 -0.0417 0.1620 1.0000
6.250 0.9073 0.01221 0.00546 -0.0408 0.1565 1.0000
6.500 0.9287 0.01256 0.00577 -0.0396 0.1505 1.0000
6.750 0.9513 0.01284 0.00608 -0.0387 0.1455 1.0000
7.000 0.9739 0.01311 0.00636 -0.0378 0.1406 1.0000
7.250 0.9943 0.01356 0.00676 -0.0365 0.1356 1.0000
7.500 1.0168 0.01385 0.00710 -0.0355 0.1322 1.0000
7.750 1.0393 0.01414 0.00744 -0.0346 0.1287 1.0000
8.000 1.0605 0.01451 0.00781 -0.0335 0.1251 1.0000
8.250 1.0790 0.01510 0.00837 -0.0320 0.1209 1.0000
8.500 1.1017 0.01535 0.00870 -0.0312 0.1186 1.0000
8.750 1.1233 0.01567 0.00908 -0.0302 0.1158 1.0000
9.000 1.1440 0.01605 0.00950 -0.0290 0.1132 1.0000
9.250 1.1631 0.01654 0.00999 -0.0277 0.1105 1.0000
9.500 1.1803 0.01720 0.01066 -0.0261 0.1073 1.0000
9.750 1.2024 0.01736 0.01091 -0.0252 0.1045 1.0000
10.000 1.2228 0.01761 0.01123 -0.0241 0.1012 1.0000
10.250 1.2399 0.01799 0.01160 -0.0224 0.0978 1.0000
10.500 1.2542 0.01857 0.01219 -0.0204 0.0942 1.0000
10.750 1.2751 0.01869 0.01241 -0.0193 0.0909 1.0000
11.000 1.2931 0.01900 0.01276 -0.0179 0.0873 1.0000
11.250 1.3071 0.01957 0.01333 -0.0160 0.0837 1.0000
11.500 1.3239 0.02002 0.01385 -0.0146 0.0811 1.0000
11.750 1.3427 0.02034 0.01426 -0.0134 0.0777 1.0000
12.000 1.3588 0.02082 0.01477 -0.0120 0.0740 1.0000
12.250 1.3725 0.02147 0.01544 -0.0104 0.0702 1.0000
12.500 1.3908 0.02187 0.01591 -0.0093 0.0647 1.0000
12.750 1.4047 0.02255 0.01660 -0.0078 0.0575 1.0000
13.000 1.4138 0.02361 0.01757 -0.0060 0.0429 1.0000
13.250 1.4097 0.02568 0.01947 -0.0031 0.0254 1.0000
13.500 1.4087 0.02758 0.02139 -0.0007 0.0192 1.0000
13.750 1.4065 0.02967 0.02353 0.0014 0.0157 1.0000
14.000 1.4085 0.03148 0.02545 0.0031 0.0142 1.0000
14.250 1.4062 0.03375 0.02782 0.0046 0.0130 1.0000
14.500 1.4015 0.03637 0.03057 0.0059 0.0120 1.0000
14.750 1.4008 0.03875 0.03308 0.0066 0.0116 1.0000
15.000 1.3968 0.04160 0.03607 0.0071 0.0109 1.0000
15.250 1.3921 0.04469 0.03929 0.0073 0.0105 1.0000
15.500 1.3835 0.04842 0.04314 0.0069 0.0101 1.0000
15.750 1.3698 0.05305 0.04792 0.0059 0.0098 1.0000
16.000 1.3541 0.05829 0.05331 0.0043 0.0096 1.0000
16.250 1.3405 0.06361 0.05878 0.0023 0.0096 1.0000
16.500 1.3206 0.07026 0.06560 -0.0006 0.0095 1.0000
16.750 1.2995 0.07756 0.07307 -0.0041 0.0095 1.0000
17.000 1.2779 0.08534 0.08101 -0.0081 0.0095 1.0000
17.250 1.2542 0.09387 0.08971 -0.0125 0.0095 1.0000
17.500 1.2311 0.10258 0.09859 -0.0170 0.0096 1.0000
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