DF102 (df102-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: DF102 (df102-il) Reynolds number: 100,000 Max Cl/Cd: 45.49 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-df102-il-100000-n5.txt Download as CSV file: xf-df102-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4872 0.08854 0.08342 -0.0372 1.0000 0.0267
-10.250 -0.5006 0.08125 0.07619 -0.0408 1.0000 0.0262
-9.750 -0.6200 0.05395 0.04848 -0.0605 1.0000 0.0224
-9.500 -0.6414 0.05034 0.04465 -0.0587 1.0000 0.0223
-9.250 -0.6455 0.04820 0.04245 -0.0568 1.0000 0.0229
-9.000 -0.6490 0.04604 0.04017 -0.0546 1.0000 0.0233
-8.750 -0.6512 0.04384 0.03781 -0.0522 1.0000 0.0238
-8.500 -0.6518 0.04177 0.03555 -0.0496 1.0000 0.0247
-8.250 -0.6521 0.03942 0.03290 -0.0468 1.0000 0.0254
-8.000 -0.6499 0.03703 0.03017 -0.0440 1.0000 0.0259
-7.750 -0.6446 0.03470 0.02746 -0.0414 1.0000 0.0265
-7.500 -0.6361 0.03262 0.02502 -0.0389 1.0000 0.0270
-7.250 -0.6249 0.03075 0.02278 -0.0365 1.0000 0.0278
-7.000 -0.6123 0.02897 0.02081 -0.0345 1.0000 0.0287
-6.750 -0.5952 0.02772 0.01953 -0.0334 0.9991 0.0304
-6.500 -0.5634 0.02638 0.01799 -0.0349 0.9943 0.0333
-6.250 -0.5325 0.02498 0.01634 -0.0358 0.9891 0.0354
-6.000 -0.5016 0.02356 0.01484 -0.0370 0.9842 0.0381
-5.750 -0.4709 0.02262 0.01381 -0.0381 0.9786 0.0426
-5.500 -0.4393 0.02162 0.01265 -0.0391 0.9730 0.0462
-5.250 -0.4070 0.02067 0.01165 -0.0404 0.9680 0.0524
-5.000 -0.3776 0.01980 0.01072 -0.0411 0.9613 0.0611
-4.750 -0.3435 0.01886 0.00981 -0.0426 0.9566 0.0795
-4.500 -0.3156 0.01796 0.00923 -0.0431 0.9496 0.1316
-4.250 -0.2817 0.01750 0.00890 -0.0445 0.9441 0.1865
-4.000 -0.2473 0.01722 0.00870 -0.0460 0.9388 0.2308
-3.750 -0.2171 0.01702 0.00859 -0.0466 0.9314 0.2741
-3.500 -0.1807 0.01677 0.00834 -0.0484 0.9268 0.3052
-3.250 -0.1528 0.01654 0.00808 -0.0483 0.9185 0.3264
-3.000 -0.1183 0.01624 0.00779 -0.0495 0.9129 0.3487
-2.750 -0.0897 0.01600 0.00757 -0.0496 0.9049 0.3718
-2.500 -0.0572 0.01570 0.00732 -0.0503 0.8985 0.3991
-2.250 -0.0287 0.01544 0.00715 -0.0503 0.8905 0.4299
-2.000 0.0023 0.01514 0.00696 -0.0507 0.8835 0.4700
-1.750 0.0296 0.01485 0.00684 -0.0503 0.8749 0.5190
-1.500 0.0602 0.01451 0.00671 -0.0504 0.8679 0.5842
-1.250 0.0858 0.01422 0.00667 -0.0495 0.8587 0.6573
-1.000 0.1180 0.01388 0.00662 -0.0494 0.8522 0.7470
-0.750 0.1610 0.01375 0.00670 -0.0513 0.8447 0.8454
-0.500 0.2121 0.01368 0.00662 -0.0552 0.8385 0.9130
-0.250 0.2574 0.01366 0.00654 -0.0584 0.8300 0.9523
0.000 0.3081 0.01351 0.00628 -0.0625 0.8210 0.9770
0.250 0.3562 0.01331 0.00599 -0.0662 0.8050 0.9976
0.500 0.3812 0.01323 0.00580 -0.0653 0.7858 1.0000
0.750 0.4036 0.01316 0.00562 -0.0638 0.7666 1.0000
1.000 0.4269 0.01310 0.00543 -0.0625 0.7473 1.0000
1.250 0.4488 0.01311 0.00534 -0.0610 0.7265 1.0000
1.500 0.4716 0.01314 0.00528 -0.0596 0.7071 1.0000
1.750 0.4947 0.01320 0.00524 -0.0584 0.6889 1.0000
2.000 0.5175 0.01329 0.00523 -0.0571 0.6694 1.0000
2.250 0.5400 0.01339 0.00527 -0.0558 0.6488 1.0000
2.500 0.5626 0.01352 0.00528 -0.0545 0.6269 1.0000
2.750 0.5845 0.01367 0.00536 -0.0531 0.6025 1.0000
3.000 0.6062 0.01385 0.00543 -0.0516 0.5755 1.0000
3.250 0.6273 0.01407 0.00554 -0.0501 0.5443 1.0000
3.500 0.6479 0.01433 0.00564 -0.0484 0.5085 1.0000
3.750 0.6674 0.01467 0.00579 -0.0467 0.4644 1.0000
4.000 0.6857 0.01512 0.00599 -0.0448 0.4118 1.0000
4.250 0.7027 0.01571 0.00625 -0.0428 0.3580 1.0000
4.500 0.7199 0.01635 0.00661 -0.0410 0.3139 1.0000
4.750 0.7380 0.01698 0.00702 -0.0394 0.2830 1.0000
5.000 0.7571 0.01757 0.00748 -0.0380 0.2616 1.0000
5.250 0.7766 0.01814 0.00795 -0.0366 0.2455 1.0000
5.500 0.7965 0.01869 0.00843 -0.0353 0.2323 1.0000
5.750 0.8166 0.01925 0.00893 -0.0341 0.2211 1.0000
6.000 0.8365 0.01983 0.00947 -0.0328 0.2117 1.0000
6.250 0.8577 0.02035 0.01002 -0.0317 0.2032 1.0000
6.750 0.8992 0.02151 0.01117 -0.0296 0.1885 1.0000
7.000 0.9194 0.02215 0.01178 -0.0284 0.1821 1.0000
7.250 0.9409 0.02273 0.01243 -0.0275 0.1754 1.0000
7.500 0.9617 0.02335 0.01308 -0.0265 0.1699 1.0000
7.750 0.9829 0.02407 0.01378 -0.0256 0.1654 1.0000
8.000 1.0046 0.02473 0.01457 -0.0247 0.1605 1.0000
8.250 1.0257 0.02542 0.01532 -0.0238 0.1560 1.0000
8.500 1.0466 0.02621 0.01609 -0.0229 0.1520 1.0000
8.750 1.0675 0.02693 0.01699 -0.0220 0.1473 1.0000
9.000 1.0881 0.02769 0.01785 -0.0211 0.1433 1.0000
9.250 1.1090 0.02852 0.01872 -0.0202 0.1402 1.0000
9.500 1.1305 0.02947 0.01975 -0.0195 0.1373 1.0000
9.750 1.1502 0.03040 0.02091 -0.0185 0.1339 1.0000
10.000 1.1691 0.03130 0.02196 -0.0175 0.1304 1.0000
10.250 1.1878 0.03217 0.02290 -0.0165 0.1273 1.0000
10.500 1.2085 0.03320 0.02396 -0.0158 0.1247 1.0000
10.750 1.2246 0.03439 0.02547 -0.0145 0.1221 1.0000
11.000 1.2395 0.03556 0.02690 -0.0130 0.1191 1.0000
11.250 1.2538 0.03663 0.02814 -0.0115 0.1162 1.0000
11.500 1.2688 0.03759 0.02920 -0.0102 0.1136 1.0000
11.750 1.2863 0.03873 0.03034 -0.0093 0.1112 1.0000
12.000 1.2890 0.04017 0.03220 -0.0065 0.1086 1.0000
12.250 1.2903 0.04137 0.03367 -0.0036 0.1052 1.0000
12.500 1.2939 0.04199 0.03436 -0.0012 0.1013 1.0000
12.750 1.2972 0.04271 0.03508 0.0008 0.0975 1.0000
13.000 1.2914 0.04443 0.03715 0.0032 0.0936 1.0000
13.250 1.2899 0.04567 0.03854 0.0050 0.0895 1.0000
13.500 1.2913 0.04681 0.03965 0.0062 0.0861 1.0000
13.750 1.2859 0.04931 0.04249 0.0073 0.0828 1.0000
14.000 1.2810 0.05184 0.04528 0.0079 0.0794 1.0000
14.250 1.2775 0.05420 0.04777 0.0082 0.0762 1.0000
14.500 1.2729 0.05685 0.05049 0.0080 0.0733 1.0000
14.750 1.2602 0.06113 0.05513 0.0072 0.0700 1.0000
15.000 1.2475 0.06559 0.05981 0.0058 0.0670 1.0000
15.250 1.2347 0.07027 0.06464 0.0039 0.0644 1.0000
15.500 1.2205 0.07551 0.06996 0.0014 0.0625 1.0000
15.750 1.1944 0.08339 0.07811 -0.0025 0.0616 1.0000
16.000 1.1635 0.09278 0.08769 -0.0077 0.0617 1.0000
16.250 1.1267 0.10404 0.09910 -0.0141 0.0623 1.0000
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Polar data table (+)
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