DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Reynolds number: 100,000 Max Cl/Cd: 52.5 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-du84132v-il-100000-n5.txt Download as CSV file: xf-du84132v-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DELFT DU84-132V3 AIRFOIL (MEASURED)
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4206 0.09515 0.08975 -0.0541 1.0000 0.0406
-10.500 -0.4241 0.09189 0.08654 -0.0542 1.0000 0.0403
-10.250 -0.4327 0.08772 0.08243 -0.0548 1.0000 0.0400
-10.000 -0.4457 0.08283 0.07761 -0.0558 1.0000 0.0395
-9.750 -0.4718 0.07551 0.07034 -0.0588 1.0000 0.0389
-9.500 -0.5102 0.06929 0.06413 -0.0607 1.0000 0.0384
-9.250 -0.5500 0.06569 0.06052 -0.0589 1.0000 0.0381
-9.000 -0.5853 0.06239 0.05715 -0.0574 0.9984 0.0379
-8.750 -0.5890 0.05572 0.05008 -0.0636 0.9891 0.0374
-8.500 -0.5820 0.05030 0.04420 -0.0677 0.9816 0.0371
-8.250 -0.5713 0.04625 0.03972 -0.0697 0.9741 0.0369
-8.000 -0.5515 0.04262 0.03563 -0.0721 0.9686 0.0368
-7.750 -0.5327 0.03974 0.03236 -0.0731 0.9622 0.0369
-7.500 -0.5084 0.03720 0.02941 -0.0745 0.9565 0.0370
-7.250 -0.4773 0.03489 0.02673 -0.0767 0.9526 0.0373
-7.000 -0.4550 0.03321 0.02476 -0.0767 0.9447 0.0379
-6.750 -0.4236 0.03155 0.02278 -0.0782 0.9397 0.0390
-6.500 -0.3925 0.03007 0.02097 -0.0794 0.9349 0.0400
-6.250 -0.3660 0.02884 0.01949 -0.0794 0.9279 0.0406
-6.000 -0.3329 0.02747 0.01806 -0.0808 0.9238 0.0413
-5.750 -0.3025 0.02634 0.01689 -0.0816 0.9189 0.0420
-5.500 -0.2763 0.02540 0.01591 -0.0816 0.9121 0.0429
-5.250 -0.2435 0.02444 0.01491 -0.0828 0.9083 0.0441
-5.000 -0.2083 0.02351 0.01391 -0.0843 0.9055 0.0458
-4.750 -0.1880 0.02292 0.01325 -0.0831 0.8969 0.0474
-4.500 -0.1565 0.02204 0.01237 -0.0842 0.8926 0.0497
-4.250 -0.1209 0.02125 0.01153 -0.0860 0.8897 0.0544
-4.000 -0.0990 0.02066 0.01097 -0.0853 0.8813 0.0606
-3.750 -0.0666 0.01993 0.01029 -0.0864 0.8767 0.0734
-3.500 -0.0314 0.01904 0.00963 -0.0882 0.8734 0.1085
-3.250 -0.0096 0.01831 0.00939 -0.0876 0.8653 0.2015
-3.000 0.0205 0.01747 0.00911 -0.0886 0.8603 0.3227
-2.750 0.0523 0.01662 0.00892 -0.0896 0.8569 0.4705
-2.500 0.0687 0.01651 0.00927 -0.0867 0.8478 0.5671
-2.250 0.0945 0.01674 0.00974 -0.0847 0.8428 0.6381
-2.000 0.1186 0.01701 0.00995 -0.0834 0.8346 0.6861
-1.750 0.1490 0.01719 0.01000 -0.0833 0.8279 0.7169
-1.500 0.1750 0.01735 0.01006 -0.0825 0.8195 0.7352
-1.250 0.2035 0.01746 0.01007 -0.0818 0.8121 0.7533
-1.000 0.2264 0.01760 0.01015 -0.0801 0.8027 0.7707
-0.750 0.2559 0.01757 0.01003 -0.0796 0.7954 0.7868
-0.500 0.2756 0.01761 0.01001 -0.0775 0.7843 0.8012
-0.250 0.3003 0.01751 0.00985 -0.0762 0.7753 0.8152
0.000 0.3285 0.01732 0.00957 -0.0756 0.7666 0.8275
0.250 0.3539 0.01712 0.00930 -0.0745 0.7563 0.8361
0.500 0.3835 0.01698 0.00906 -0.0746 0.7455 0.8433
0.750 0.4090 0.01684 0.00887 -0.0739 0.7343 0.8482
1.000 0.4365 0.01673 0.00869 -0.0736 0.7240 0.8537
1.250 0.4634 0.01668 0.00858 -0.0734 0.7143 0.8599
1.500 0.4891 0.01659 0.00845 -0.0727 0.7050 0.8654
1.750 0.5170 0.01653 0.00834 -0.0725 0.6959 0.8726
2.000 0.5371 0.01649 0.00831 -0.0708 0.6843 0.8799
2.250 0.5613 0.01647 0.00827 -0.0700 0.6737 0.8873
2.500 0.5881 0.01643 0.00820 -0.0697 0.6638 0.8924
2.750 0.6173 0.01640 0.00811 -0.0698 0.6538 0.8963
3.000 0.6408 0.01645 0.00818 -0.0691 0.6411 0.9010
3.250 0.6664 0.01650 0.00822 -0.0687 0.6289 0.9053
3.500 0.6932 0.01653 0.00823 -0.0685 0.6169 0.9084
3.750 0.7200 0.01660 0.00829 -0.0683 0.6042 0.9111
4.000 0.7452 0.01670 0.00839 -0.0679 0.5902 0.9145
4.250 0.7714 0.01680 0.00846 -0.0677 0.5761 0.9179
4.500 0.7977 0.01691 0.00853 -0.0674 0.5608 0.9209
4.750 0.8225 0.01706 0.00867 -0.0669 0.5442 0.9238
5.000 0.8461 0.01724 0.00884 -0.0663 0.5262 0.9273
5.250 0.8697 0.01744 0.00901 -0.0656 0.5074 0.9311
5.750 0.9151 0.01792 0.00950 -0.0642 0.4655 0.9419
6.000 0.9387 0.01820 0.00977 -0.0637 0.4438 0.9488
6.250 0.9644 0.01853 0.01006 -0.0637 0.4258 0.9578
6.500 0.9896 0.01885 0.01039 -0.0637 0.4082 0.9944
6.750 1.0106 0.01931 0.01077 -0.0629 0.3931 1.0000
7.000 1.0315 0.01981 0.01121 -0.0621 0.3780 1.0000
7.250 1.0514 0.02034 0.01170 -0.0612 0.3623 1.0000
7.500 1.0701 0.02087 0.01224 -0.0601 0.3466 1.0000
7.750 1.0888 0.02141 0.01279 -0.0590 0.3323 1.0000
8.000 1.1064 0.02199 0.01336 -0.0578 0.3182 1.0000
8.250 1.1230 0.02262 0.01396 -0.0564 0.3045 1.0000
8.500 1.1395 0.02326 0.01464 -0.0551 0.2904 1.0000
8.750 1.1559 0.02391 0.01536 -0.0538 0.2764 1.0000
9.000 1.1707 0.02464 0.01610 -0.0523 0.2628 1.0000
9.250 1.1846 0.02544 0.01691 -0.0508 0.2494 1.0000
9.500 1.1983 0.02626 0.01781 -0.0493 0.2347 1.0000
9.750 1.2109 0.02713 0.01876 -0.0478 0.2158 1.0000
10.000 1.2196 0.02822 0.01980 -0.0459 0.1967 1.0000
10.250 1.2266 0.02947 0.02099 -0.0440 0.1796 1.0000
10.500 1.2348 0.03076 0.02227 -0.0423 0.1633 1.0000
10.750 1.2398 0.03229 0.02375 -0.0405 0.1519 1.0000
11.000 1.2445 0.03393 0.02536 -0.0388 0.1430 1.0000
11.250 1.2487 0.03567 0.02709 -0.0372 0.1352 1.0000
11.500 1.2545 0.03737 0.02887 -0.0359 0.1270 1.0000
11.750 1.2613 0.03905 0.03065 -0.0348 0.1190 1.0000
12.000 1.2654 0.04097 0.03261 -0.0337 0.1118 1.0000
12.250 1.2709 0.04284 0.03459 -0.0328 0.1053 1.0000
12.500 1.2724 0.04510 0.03686 -0.0319 0.1004 1.0000
12.750 1.2753 0.04734 0.03918 -0.0311 0.0958 1.0000
13.000 1.2772 0.04974 0.04169 -0.0306 0.0912 1.0000
13.250 1.2759 0.05251 0.04447 -0.0301 0.0874 1.0000
13.500 1.2776 0.05511 0.04717 -0.0297 0.0835 1.0000
13.750 1.2796 0.05777 0.04998 -0.0295 0.0795 1.0000
14.000 1.2795 0.06070 0.05302 -0.0295 0.0761 1.0000
14.250 1.2786 0.06376 0.05606 -0.0295 0.0732 1.0000
14.500 1.2813 0.06663 0.05918 -0.0297 0.0698 1.0000
14.750 1.2821 0.06976 0.06247 -0.0300 0.0666 1.0000
15.000 1.2814 0.07312 0.06592 -0.0306 0.0640 1.0000
15.250 1.2803 0.07655 0.06938 -0.0313 0.0617 1.0000
15.500 1.2801 0.08014 0.07322 -0.0321 0.0588 1.0000
15.750 1.2784 0.08393 0.07717 -0.0331 0.0563 1.0000
16.000 1.2759 0.08789 0.08124 -0.0344 0.0543 1.0000
16.250 1.2731 0.09192 0.08534 -0.0359 0.0527 1.0000
16.500 1.2712 0.09602 0.08963 -0.0372 0.0509 1.0000
16.750 1.2684 0.10030 0.09409 -0.0388 0.0493 1.0000
17.000 1.2647 0.10480 0.09873 -0.0407 0.0479 1.0000
17.250 1.2612 0.10929 0.10333 -0.0427 0.0466 1.0000
17.500 1.2587 0.11363 0.10774 -0.0448 0.0455 1.0000
17.750 1.2558 0.11807 0.11224 -0.0470 0.0444 1.0000
18.000 1.2470 0.12391 0.11831 -0.0500 0.0434 1.0000
18.250 1.2373 0.13002 0.12462 -0.0534 0.0424 1.0000
18.500 1.2267 0.13643 0.13120 -0.0572 0.0416 1.0000
18.750 1.2157 0.14308 0.13801 -0.0613 0.0408 1.0000
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