STRAND AIRFOIL (strand-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: STRAND AIRFOIL (strand-il) Reynolds number: 200,000 Max Cl/Cd: 26.52 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-strand-il-200000-n5.txt Download as CSV file: xf-strand-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: STRAND AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4720 0.12440 0.11887 0.0369 0.4011 0.0403
-9.750 -0.4682 0.12045 0.11493 0.0347 0.4010 0.0412
-9.250 -0.4898 0.10495 0.09949 0.0201 0.4010 0.0432
-9.000 -0.4773 0.10321 0.09776 0.0217 0.4008 0.0436
-8.750 -0.4675 0.10087 0.09543 0.0217 0.4006 0.0439
-8.500 -0.4592 0.09813 0.09270 0.0210 0.4004 0.0444
-8.250 -0.4529 0.09490 0.08948 0.0194 0.4003 0.0450
-8.000 -0.4483 0.09111 0.08572 0.0170 0.4002 0.0457
-7.750 -0.4457 0.08654 0.08117 0.0135 0.4000 0.0467
-7.500 -0.5014 0.06342 0.05731 -0.0253 0.4005 0.0499
-7.250 -0.4875 0.05845 0.05238 -0.0269 0.4003 0.0507
-7.000 -0.4684 0.05581 0.04980 -0.0273 0.4000 0.0514
-6.750 -0.4492 0.05346 0.04745 -0.0284 0.3998 0.0524
-6.500 -0.4340 0.04964 0.04286 -0.0344 0.3996 0.0588
-6.250 -0.4119 0.04688 0.04028 -0.0347 0.3993 0.0601
-6.000 -0.3887 0.04494 0.03834 -0.0355 0.3989 0.0619
-5.500 -0.3311 0.03660 0.02856 -0.0383 0.3981 0.0361
-5.250 -0.3043 0.03463 0.02640 -0.0390 0.3977 0.0350
-4.750 -0.2454 0.03221 0.02303 -0.0398 0.3972 0.0320
-4.500 -0.2175 0.03085 0.02160 -0.0401 0.3969 0.0319
-4.250 -0.1891 0.02975 0.02038 -0.0404 0.3967 0.0317
-4.000 -0.1605 0.02880 0.01933 -0.0407 0.3964 0.0316
-3.750 -0.1317 0.02800 0.01841 -0.0409 0.3962 0.0316
-3.500 -0.1023 0.02761 0.01781 -0.0411 0.3960 0.0320
-3.250 -0.0737 0.02673 0.01689 -0.0414 0.3957 0.0326
-3.000 -0.0453 0.02599 0.01620 -0.0416 0.3955 0.0329
-2.750 -0.0163 0.02550 0.01567 -0.0417 0.3953 0.0330
-2.500 0.0127 0.02511 0.01523 -0.0418 0.3950 0.0328
-2.250 0.0416 0.02474 0.01486 -0.0419 0.3948 0.0328
-2.000 0.0704 0.02441 0.01455 -0.0421 0.3946 0.0328
-1.750 0.0993 0.02411 0.01429 -0.0423 0.3944 0.0329
-1.500 0.1281 0.02387 0.01410 -0.0425 0.3942 0.0331
-1.250 0.1571 0.02368 0.01396 -0.0428 0.3940 0.0333
-1.000 0.1862 0.02355 0.01389 -0.0431 0.3938 0.0336
-0.750 0.2155 0.02347 0.01387 -0.0435 0.3936 0.0339
-0.500 0.2448 0.02346 0.01389 -0.0440 0.3934 0.0344
-0.250 0.2742 0.02347 0.01390 -0.0444 0.3930 0.0350
0.000 0.3036 0.02354 0.01396 -0.0448 0.3926 0.0363
0.250 0.3329 0.02368 0.01408 -0.0451 0.3923 0.0374
0.500 0.3623 0.02382 0.01420 -0.0456 0.3921 0.0383
0.750 0.3915 0.02406 0.01443 -0.0460 0.3918 0.0390
1.000 0.4206 0.02435 0.01471 -0.0463 0.3916 0.0400
1.250 0.4495 0.02469 0.01505 -0.0467 0.3914 0.0412
1.500 0.4783 0.02508 0.01543 -0.0470 0.3912 0.0427
1.750 0.5070 0.02547 0.01585 -0.0474 0.3909 0.0455
2.000 0.5357 0.02587 0.01631 -0.0478 0.3907 0.0575
2.250 0.5655 0.02540 0.01691 -0.0494 0.3905 0.3827
2.500 0.5936 0.02580 0.01759 -0.0498 0.3902 0.4644
2.750 0.6211 0.02625 0.01830 -0.0501 0.3900 0.5308
3.000 0.6477 0.02662 0.01894 -0.0501 0.3896 0.6063
3.250 0.6737 0.02705 0.01960 -0.0499 0.3891 0.6698
3.500 0.6967 0.02814 0.02114 -0.0503 0.3882 0.7525
3.750 0.7121 0.02935 0.02288 -0.0493 0.3870 0.8913
4.000 0.7379 0.03145 0.02522 -0.0519 0.3836 1.0000
4.250 0.7643 0.03248 0.02626 -0.0529 0.3814 1.0000
4.500 0.7907 0.03339 0.02717 -0.0537 0.3800 1.0000
4.750 0.8171 0.03412 0.02789 -0.0541 0.3790 1.0000
5.000 0.8438 0.03464 0.02839 -0.0543 0.3781 1.0000
5.250 0.8705 0.03509 0.02881 -0.0543 0.3773 1.0000
5.500 0.8970 0.03561 0.02931 -0.0544 0.3767 1.0000
5.750 0.9234 0.03613 0.02982 -0.0544 0.3762 1.0000
6.000 0.9501 0.03652 0.03018 -0.0543 0.3758 1.0000
6.250 0.9769 0.03683 0.03048 -0.0540 0.3753 1.0000
7.250 1.0231 0.05222 0.04652 -0.0707 0.3522 1.0000
7.500 1.0464 0.05271 0.04702 -0.0705 0.3513 1.0000
7.750 1.0707 0.05297 0.04729 -0.0699 0.3507 1.0000
8.000 1.0958 0.05303 0.04737 -0.0692 0.3502 1.0000
9.000 1.0771 0.06823 0.06275 -0.0798 0.3201 1.0000
9.500 1.1209 0.06873 0.06330 -0.0788 0.3176 1.0000
10.000 1.1315 0.07317 0.06782 -0.0799 0.3073 1.0000
10.500 1.1444 0.07741 0.07213 -0.0808 0.2972 1.0000
11.000 1.1617 0.08112 0.07594 -0.0812 0.2879 1.0000
11.250 1.1814 0.08149 0.07635 -0.0809 0.2857 1.0000
11.500 1.2038 0.08148 0.07638 -0.0804 0.2842 1.0000
11.750 1.2275 0.08128 0.07624 -0.0798 0.2830 1.0000
12.000 1.2210 0.08528 0.08029 -0.0808 0.2743 1.0000
12.250 1.2440 0.08514 0.08020 -0.0803 0.2722 1.0000
12.500 1.2744 0.08394 0.07904 -0.0795 0.2703 1.0000
12.750 1.2735 0.08716 0.08230 -0.0802 0.2615 1.0000
13.000 1.3025 0.08615 0.08131 -0.0794 0.2580 1.0000
13.250 1.3268 0.08580 0.08098 -0.0789 0.2530 1.0000
13.500 1.3385 0.08722 0.08243 -0.0789 0.2444 1.0000
13.750 1.3584 0.08746 0.08266 -0.0785 0.2363 1.0000
14.000 1.3808 0.08728 0.08244 -0.0780 0.2269 1.0000
14.250 1.3872 0.08945 0.08461 -0.0782 0.2163 1.0000
14.500 1.4001 0.09058 0.08570 -0.0781 0.2052 1.0000
14.750 1.4101 0.09211 0.08715 -0.0781 0.1930 1.0000
15.000 1.4162 0.09420 0.08915 -0.0782 0.1805 1.0000
15.250 1.4184 0.09686 0.09172 -0.0786 0.1683 1.0000
15.500 1.4173 0.10007 0.09487 -0.0792 0.1567 1.0000
15.750 1.4154 0.10345 0.09821 -0.0799 0.1456 1.0000
16.000 1.4136 0.10685 0.10156 -0.0806 0.1352 1.0000
16.250 1.4107 0.11047 0.10513 -0.0815 0.1253 1.0000
16.500 1.4061 0.11438 0.10899 -0.0825 0.1159 1.0000
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Polar data table (+)
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