DF102 (df102-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: DF102 (df102-il) Reynolds number: 100,000 Max Cl/Cd: 49.07 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-df102-il-100000.txt Download as CSV file: xf-df102-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4091 0.09766 0.09274 -0.0280 1.0000 0.1384
-9.000 -0.4424 0.09503 0.09027 -0.0337 1.0000 0.1454
-8.750 -0.4411 0.09050 0.08581 -0.0337 1.0000 0.1470
-8.500 -0.4264 0.08699 0.08231 -0.0318 1.0000 0.1489
-8.250 -0.4250 0.08375 0.07911 -0.0315 1.0000 0.1508
-8.000 -0.5702 0.05932 0.05439 -0.0482 1.0000 0.0765
-7.750 -0.5666 0.05580 0.05096 -0.0461 1.0000 0.0742
-7.500 -0.6058 0.04839 0.04252 -0.0428 1.0000 0.0646
-7.250 -0.6034 0.04418 0.03823 -0.0407 1.0000 0.0633
-7.000 -0.6008 0.04058 0.03435 -0.0383 1.0000 0.0621
-6.750 -0.5958 0.03718 0.03055 -0.0359 1.0000 0.0611
-6.500 -0.5871 0.03411 0.02703 -0.0336 1.0000 0.0607
-6.250 -0.5747 0.03157 0.02404 -0.0315 1.0000 0.0610
-6.000 -0.5598 0.02969 0.02170 -0.0295 1.0000 0.0630
-5.750 -0.5430 0.02801 0.01957 -0.0277 1.0000 0.0651
-5.500 -0.5244 0.02578 0.01727 -0.0264 1.0000 0.0673
-5.250 -0.5048 0.02443 0.01584 -0.0250 1.0000 0.0705
-5.000 -0.4850 0.02348 0.01468 -0.0235 1.0000 0.0759
-4.750 -0.4656 0.02216 0.01341 -0.0222 1.0000 0.0814
-4.500 -0.4461 0.02127 0.01244 -0.0208 1.0000 0.0888
-4.250 -0.4275 0.02037 0.01162 -0.0194 1.0000 0.1017
-4.000 -0.4091 0.01935 0.01081 -0.0179 1.0000 0.1268
-3.750 -0.3916 0.01843 0.01046 -0.0166 1.0000 0.2236
-3.500 -0.3739 0.01847 0.01053 -0.0153 1.0000 0.2730
-3.250 -0.3454 0.01864 0.01066 -0.0162 0.9965 0.3122
-3.000 -0.3065 0.01892 0.01101 -0.0190 0.9883 0.3591
-2.750 -0.2672 0.01900 0.01118 -0.0216 0.9807 0.3992
-2.500 -0.2285 0.01889 0.01112 -0.0241 0.9724 0.4339
-2.250 -0.1926 0.01871 0.01111 -0.0259 0.9639 0.4700
-2.000 -0.1518 0.01854 0.01116 -0.0286 0.9566 0.5195
-1.750 -0.1204 0.01822 0.01116 -0.0293 0.9470 0.5856
-1.500 -0.0802 0.01777 0.01135 -0.0309 0.9412 0.7216
-1.250 0.0383 0.01765 0.01158 -0.0471 0.9446 1.0000
-1.000 0.0758 0.01781 0.01150 -0.0497 0.9343 1.0000
-0.750 0.1249 0.01795 0.01144 -0.0541 0.9270 1.0000
-0.500 0.1567 0.01810 0.01145 -0.0552 0.9154 1.0000
-0.250 0.1960 0.01822 0.01145 -0.0577 0.9060 1.0000
0.000 0.2443 0.01822 0.01136 -0.0616 0.8982 1.0000
0.250 0.2864 0.01811 0.01117 -0.0640 0.8862 1.0000
0.500 0.3351 0.01767 0.01067 -0.0670 0.8736 1.0000
0.750 0.3803 0.01711 0.01005 -0.0690 0.8600 1.0000
1.000 0.4175 0.01662 0.00952 -0.0696 0.8459 1.0000
1.250 0.4495 0.01624 0.00910 -0.0693 0.8319 1.0000
1.500 0.4793 0.01594 0.00876 -0.0686 0.8187 1.0000
1.750 0.5072 0.01568 0.00846 -0.0676 0.8051 1.0000
2.000 0.5317 0.01549 0.00825 -0.0661 0.7897 1.0000
2.250 0.5552 0.01535 0.00809 -0.0644 0.7733 1.0000
2.500 0.5784 0.01522 0.00792 -0.0627 0.7555 1.0000
2.750 0.6023 0.01506 0.00774 -0.0610 0.7368 1.0000
3.000 0.6271 0.01489 0.00751 -0.0594 0.7174 1.0000
3.250 0.6490 0.01482 0.00742 -0.0575 0.6940 1.0000
3.500 0.6723 0.01473 0.00725 -0.0557 0.6689 1.0000
3.750 0.6935 0.01471 0.00716 -0.0536 0.6383 1.0000
4.000 0.7133 0.01476 0.00712 -0.0512 0.5998 1.0000
4.250 0.7316 0.01491 0.00706 -0.0487 0.5495 1.0000
4.500 0.7462 0.01532 0.00712 -0.0456 0.4778 1.0000
4.750 0.7592 0.01610 0.00737 -0.0426 0.4037 1.0000
5.000 0.7745 0.01701 0.00784 -0.0403 0.3560 1.0000
5.250 0.7929 0.01788 0.00840 -0.0386 0.3257 1.0000
5.500 0.8133 0.01868 0.00903 -0.0373 0.3027 1.0000
5.750 0.8347 0.01951 0.00968 -0.0362 0.2850 1.0000
6.000 0.8575 0.02035 0.01041 -0.0354 0.2704 1.0000
6.250 0.8812 0.02123 0.01123 -0.0347 0.2583 1.0000
6.500 0.9058 0.02217 0.01209 -0.0342 0.2480 1.0000
6.750 0.9306 0.02311 0.01293 -0.0338 0.2381 1.0000
7.000 0.9536 0.02399 0.01395 -0.0330 0.2290 1.0000
7.250 0.9804 0.02516 0.01495 -0.0330 0.2215 1.0000
7.500 1.0026 0.02607 0.01611 -0.0321 0.2146 1.0000
7.750 1.0283 0.02719 0.01721 -0.0318 0.2087 1.0000
8.000 1.0507 0.02839 0.01858 -0.0311 0.2030 1.0000
8.250 1.0726 0.02943 0.01977 -0.0302 0.1970 1.0000
8.500 1.0989 0.03091 0.02115 -0.0303 0.1921 1.0000
8.750 1.1163 0.03217 0.02282 -0.0288 0.1880 1.0000
9.000 1.1365 0.03355 0.02446 -0.0277 0.1839 1.0000
9.250 1.1590 0.03489 0.02586 -0.0272 0.1798 1.0000
9.500 1.1776 0.03669 0.02784 -0.0262 0.1760 1.0000
9.750 1.1897 0.03837 0.02994 -0.0242 0.1721 1.0000
10.000 1.2052 0.04016 0.03200 -0.0228 0.1689 1.0000
10.250 1.2258 0.04177 0.03371 -0.0222 0.1655 1.0000
10.500 1.2420 0.04409 0.03617 -0.0212 0.1623 1.0000
10.750 1.2403 0.04649 0.03911 -0.0180 0.1593 1.0000
11.000 1.2411 0.04905 0.04204 -0.0153 0.1564 1.0000
11.250 1.2477 0.05127 0.04450 -0.0134 0.1534 1.0000
11.500 1.2828 0.05274 0.04574 -0.0147 0.1486 1.0000
11.750 1.2606 0.05595 0.04950 -0.0101 0.1469 1.0000
12.000 1.2352 0.05960 0.05353 -0.0059 0.1453 1.0000
12.250 1.2028 0.06341 0.05761 -0.0016 0.1447 1.0000
12.500 1.1632 0.06833 0.06274 0.0013 0.1449 1.0000
12.750 1.1150 0.07519 0.06976 0.0017 0.1459 1.0000
13.000 1.0635 0.08444 0.07911 -0.0010 0.1474 1.0000
13.250 1.0189 0.09538 0.09010 -0.0058 0.1485 1.0000
13.750 1.2745 0.06419 0.05846 0.0063 0.1074 1.0000
14.000 1.2388 0.06942 0.06395 0.0074 0.1073 1.0000
14.250 1.2027 0.07578 0.07053 0.0069 0.1076 1.0000
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Polar data table (+)
Polar graphs
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