DF102 (df102-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: DF102 (df102-il) Reynolds number: 200,000 Max Cl/Cd: 56.27 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-df102-il-200000-n5.txt Download as CSV file: xf-df102-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6299 0.06251 0.05850 -0.0531 1.0000 0.0129
-11.000 -0.6479 0.05514 0.05103 -0.0597 1.0000 0.0127
-10.750 -0.6679 0.04920 0.04492 -0.0649 1.0000 0.0127
-10.500 -0.6949 0.04509 0.04054 -0.0653 1.0000 0.0129
-10.250 -0.7090 0.04267 0.03802 -0.0626 1.0000 0.0127
-10.000 -0.7243 0.03983 0.03484 -0.0596 1.0000 0.0129
-9.750 -0.7309 0.03745 0.03226 -0.0565 1.0000 0.0131
-9.500 -0.7327 0.03549 0.03013 -0.0535 1.0000 0.0133
-9.250 -0.7317 0.03385 0.02834 -0.0505 1.0000 0.0135
-9.000 -0.7288 0.03230 0.02662 -0.0474 1.0000 0.0137
-8.750 -0.7202 0.03066 0.02478 -0.0454 0.9992 0.0140
-8.500 -0.6938 0.02864 0.02248 -0.0467 0.9948 0.0146
-8.250 -0.6677 0.02676 0.02031 -0.0476 0.9902 0.0153
-8.000 -0.6398 0.02500 0.01827 -0.0485 0.9858 0.0160
-7.750 -0.6085 0.02368 0.01661 -0.0498 0.9825 0.0171
-7.500 -0.5830 0.02231 0.01522 -0.0502 0.9772 0.0181
-7.250 -0.5525 0.02136 0.01418 -0.0513 0.9731 0.0196
-7.000 -0.5201 0.02024 0.01290 -0.0527 0.9701 0.0209
-6.750 -0.4922 0.01934 0.01186 -0.0529 0.9648 0.0220
-6.500 -0.4631 0.01826 0.01076 -0.0537 0.9602 0.0239
-6.250 -0.4302 0.01757 0.00999 -0.0551 0.9568 0.0265
-6.000 -0.4021 0.01688 0.00919 -0.0552 0.9511 0.0286
-5.750 -0.3734 0.01614 0.00843 -0.0557 0.9456 0.0316
-5.500 -0.3407 0.01560 0.00777 -0.0567 0.9418 0.0354
-5.250 -0.3146 0.01500 0.00713 -0.0564 0.9348 0.0395
-5.000 -0.2848 0.01446 0.00656 -0.0568 0.9293 0.0475
-4.750 -0.2561 0.01381 0.00599 -0.0571 0.9239 0.0685
-4.500 -0.2309 0.01318 0.00557 -0.0567 0.9164 0.1148
-4.250 -0.2010 0.01273 0.00527 -0.0572 0.9114 0.1599
-4.000 -0.1757 0.01247 0.00508 -0.0566 0.9029 0.1899
-3.750 -0.1464 0.01221 0.00486 -0.0568 0.8970 0.2168
-3.500 -0.1207 0.01199 0.00472 -0.0563 0.8885 0.2499
-3.250 -0.0925 0.01176 0.00455 -0.0562 0.8819 0.2790
-3.000 -0.0665 0.01159 0.00439 -0.0557 0.8729 0.2974
-2.750 -0.0381 0.01139 0.00417 -0.0556 0.8661 0.3146
-2.500 -0.0126 0.01122 0.00403 -0.0549 0.8563 0.3324
-2.250 0.0146 0.01103 0.00387 -0.0546 0.8482 0.3527
-2.000 0.0410 0.01085 0.00372 -0.0541 0.8389 0.3760
-1.750 0.0670 0.01067 0.00360 -0.0536 0.8294 0.4033
-1.500 0.0937 0.01046 0.00347 -0.0531 0.8207 0.4369
-1.250 0.1187 0.01025 0.00339 -0.0524 0.8101 0.4786
-1.000 0.1437 0.01003 0.00333 -0.0516 0.7999 0.5306
-0.750 0.1683 0.00978 0.00326 -0.0506 0.7879 0.5911
-0.500 0.1921 0.00953 0.00318 -0.0493 0.7728 0.6555
-0.250 0.2158 0.00929 0.00314 -0.0478 0.7555 0.7262
0.000 0.2430 0.00912 0.00316 -0.0469 0.7380 0.8096
0.250 0.2822 0.00911 0.00318 -0.0485 0.7191 0.8845
0.500 0.3197 0.00918 0.00316 -0.0500 0.6991 0.9253
0.750 0.3573 0.00927 0.00313 -0.0517 0.6766 0.9498
1.000 0.3936 0.00938 0.00311 -0.0532 0.6551 0.9675
1.250 0.4325 0.00948 0.00311 -0.0553 0.6345 0.9806
1.500 0.4719 0.00960 0.00309 -0.0577 0.6122 0.9914
1.750 0.5090 0.00972 0.00310 -0.0597 0.5870 1.0000
2.000 0.5308 0.00988 0.00314 -0.0584 0.5642 1.0000
2.250 0.5522 0.01007 0.00319 -0.0571 0.5377 1.0000
2.500 0.5732 0.01029 0.00327 -0.0556 0.5067 1.0000
2.750 0.5936 0.01055 0.00336 -0.0542 0.4704 1.0000
3.000 0.6129 0.01090 0.00349 -0.0525 0.4257 1.0000
3.250 0.6308 0.01135 0.00367 -0.0507 0.3729 1.0000
3.500 0.6484 0.01187 0.00390 -0.0488 0.3192 1.0000
3.750 0.6667 0.01238 0.00417 -0.0472 0.2795 1.0000
4.000 0.6861 0.01282 0.00446 -0.0457 0.2540 1.0000
4.250 0.7065 0.01321 0.00474 -0.0444 0.2355 1.0000
4.500 0.7274 0.01358 0.00503 -0.0431 0.2216 1.0000
4.750 0.7483 0.01395 0.00533 -0.0419 0.2106 1.0000
5.000 0.7702 0.01426 0.00564 -0.0408 0.2009 1.0000
5.250 0.7917 0.01461 0.00596 -0.0397 0.1926 1.0000
5.500 0.8132 0.01497 0.00628 -0.0386 0.1841 1.0000
5.750 0.8350 0.01532 0.00662 -0.0375 0.1767 1.0000
6.000 0.8564 0.01569 0.00698 -0.0365 0.1696 1.0000
6.250 0.8780 0.01606 0.00736 -0.0354 0.1639 1.0000
6.500 0.8998 0.01642 0.00774 -0.0344 0.1583 1.0000
6.750 0.9204 0.01687 0.00816 -0.0332 0.1534 1.0000
7.000 0.9421 0.01725 0.00860 -0.0322 0.1488 1.0000
7.250 0.9634 0.01765 0.00904 -0.0312 0.1441 1.0000
7.500 0.9834 0.01813 0.00950 -0.0300 0.1396 1.0000
7.750 1.0044 0.01856 0.00998 -0.0289 0.1356 1.0000
8.000 1.0253 0.01899 0.01049 -0.0278 0.1316 1.0000
8.250 1.0453 0.01947 0.01101 -0.0267 0.1283 1.0000
8.500 1.0639 0.02007 0.01159 -0.0253 0.1252 1.0000
8.750 1.0841 0.02057 0.01217 -0.0242 0.1225 1.0000
9.000 1.1041 0.02107 0.01277 -0.0230 0.1194 1.0000
9.250 1.1232 0.02158 0.01337 -0.0218 0.1163 1.0000
9.500 1.1409 0.02216 0.01397 -0.0204 0.1135 1.0000
9.750 1.1574 0.02286 0.01468 -0.0189 0.1112 1.0000
10.000 1.1755 0.02343 0.01539 -0.0175 0.1092 1.0000
10.250 1.1928 0.02404 0.01612 -0.0160 0.1069 1.0000
10.500 1.2091 0.02466 0.01686 -0.0145 0.1044 1.0000
10.750 1.2242 0.02527 0.01755 -0.0128 0.1019 1.0000
11.000 1.2376 0.02600 0.01829 -0.0110 0.0992 1.0000
11.250 1.2523 0.02669 0.01912 -0.0095 0.0964 1.0000
11.500 1.2659 0.02723 0.01981 -0.0079 0.0922 1.0000
11.750 1.2772 0.02785 0.02049 -0.0062 0.0880 1.0000
12.000 1.2887 0.02865 0.02138 -0.0046 0.0842 1.0000
12.250 1.3022 0.02937 0.02228 -0.0033 0.0801 1.0000
12.500 1.3129 0.03025 0.02323 -0.0018 0.0761 1.0000
12.750 1.3229 0.03125 0.02433 -0.0004 0.0723 1.0000
13.000 1.3351 0.03217 0.02540 0.0007 0.0666 1.0000
13.250 1.3438 0.03335 0.02665 0.0019 0.0610 1.0000
13.500 1.3519 0.03467 0.02803 0.0029 0.0531 1.0000
13.750 1.3575 0.03629 0.02971 0.0040 0.0449 1.0000
14.000 1.3575 0.03847 0.03192 0.0051 0.0359 1.0000
14.250 1.3539 0.04112 0.03459 0.0060 0.0290 1.0000
14.500 1.3471 0.04423 0.03777 0.0065 0.0240 1.0000
14.750 1.3390 0.04767 0.04132 0.0067 0.0213 1.0000
15.000 1.3309 0.05131 0.04511 0.0065 0.0194 1.0000
15.250 1.3194 0.05559 0.04954 0.0057 0.0180 1.0000
15.500 1.3060 0.06040 0.05451 0.0043 0.0173 1.0000
15.750 1.2895 0.06604 0.06032 0.0022 0.0165 1.0000
16.000 1.2728 0.07212 0.06660 -0.0005 0.0162 1.0000
16.250 1.2520 0.07934 0.07402 -0.0041 0.0161 1.0000
16.500 1.2270 0.08783 0.08273 -0.0087 0.0162 1.0000
16.750 1.1942 0.09852 0.09365 -0.0146 0.0168 1.0000
17.000 1.1646 0.10897 0.10433 -0.0204 0.0176 1.0000
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