STRAND AIRFOIL (strand-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: STRAND AIRFOIL (strand-il) Reynolds number: 500,000 Max Cl/Cd: 101.56 at α=11.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-strand-il-500000-n5.txt Download as CSV file: xf-strand-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5360 0.08619 0.08170 0.0146 0.3745 0.0237
-9.000 -0.5568 0.07567 0.07110 0.0033 0.3745 0.0237
-8.750 -0.5751 0.06736 0.06266 -0.0090 0.3745 0.0237
-8.500 -0.5773 0.06141 0.05648 -0.0184 0.3745 0.0237
-8.250 -0.5712 0.05712 0.05197 -0.0228 0.3744 0.0237
-8.000 -0.5598 0.05341 0.04803 -0.0258 0.3743 0.0237
-7.750 -0.5445 0.05009 0.04450 -0.0281 0.3742 0.0237
-7.500 -0.5263 0.04707 0.04126 -0.0299 0.3741 0.0237
-7.000 -0.4844 0.04150 0.03583 -0.0312 0.3739 0.0232
-6.750 -0.4628 0.03884 0.03303 -0.0327 0.3737 0.0228
-6.500 -0.4395 0.03625 0.03021 -0.0341 0.3736 0.0224
-6.250 -0.4145 0.03396 0.02768 -0.0352 0.3735 0.0223
-6.000 -0.3884 0.03204 0.02552 -0.0361 0.3733 0.0225
-5.750 -0.3617 0.03023 0.02348 -0.0368 0.3732 0.0224
-5.500 -0.3343 0.02846 0.02150 -0.0374 0.3730 0.0221
-5.250 -0.3064 0.02688 0.01971 -0.0379 0.3729 0.0218
-5.000 -0.2780 0.02551 0.01814 -0.0383 0.3727 0.0217
-4.750 -0.2494 0.02432 0.01678 -0.0386 0.3726 0.0217
-4.500 -0.2206 0.02328 0.01559 -0.0388 0.3724 0.0217
-4.250 -0.1917 0.02236 0.01454 -0.0390 0.3722 0.0218
-4.000 -0.1627 0.02154 0.01360 -0.0392 0.3719 0.0219
-3.750 -0.1336 0.02081 0.01277 -0.0393 0.3716 0.0221
-3.500 -0.1044 0.02015 0.01202 -0.0394 0.3714 0.0222
-3.250 -0.0752 0.01956 0.01137 -0.0395 0.3713 0.0224
-3.000 -0.0460 0.01903 0.01078 -0.0396 0.3711 0.0225
-2.750 -0.0168 0.01855 0.01026 -0.0397 0.3709 0.0226
-2.500 0.0125 0.01812 0.00979 -0.0398 0.3708 0.0228
-2.250 0.0419 0.01779 0.00943 -0.0399 0.3706 0.0231
-2.000 0.0713 0.01757 0.00916 -0.0399 0.3704 0.0235
-1.750 0.1008 0.01735 0.00891 -0.0400 0.3703 0.0236
-1.500 0.1302 0.01706 0.00862 -0.0402 0.3701 0.0237
-1.250 0.1596 0.01666 0.00825 -0.0404 0.3699 0.0238
-1.000 0.1891 0.01631 0.00793 -0.0406 0.3698 0.0240
-0.750 0.2188 0.01607 0.00771 -0.0409 0.3696 0.0243
-0.500 0.2486 0.01590 0.00756 -0.0412 0.3694 0.0245
-0.250 0.2784 0.01577 0.00745 -0.0415 0.3693 0.0249
0.000 0.3082 0.01569 0.00738 -0.0417 0.3691 0.0253
0.250 0.3380 0.01563 0.00734 -0.0420 0.3690 0.0257
0.500 0.3678 0.01561 0.00732 -0.0422 0.3688 0.0262
0.750 0.3976 0.01561 0.00734 -0.0425 0.3687 0.0267
1.000 0.4273 0.01566 0.00739 -0.0427 0.3685 0.0273
1.250 0.4570 0.01567 0.00742 -0.0429 0.3684 0.0283
1.500 0.4866 0.01573 0.00750 -0.0432 0.3682 0.0293
1.750 0.5161 0.01583 0.00761 -0.0434 0.3681 0.0300
2.000 0.5456 0.01596 0.00775 -0.0436 0.3680 0.0308
2.250 0.5749 0.01611 0.00791 -0.0437 0.3678 0.0318
2.500 0.6042 0.01628 0.00809 -0.0439 0.3677 0.0331
2.750 0.6335 0.01646 0.00830 -0.0441 0.3675 0.0354
3.250 0.6940 0.01602 0.00878 -0.0456 0.3672 0.3755
3.500 0.7234 0.01601 0.00908 -0.0461 0.3669 0.4720
3.750 0.7525 0.01613 0.00939 -0.0463 0.3666 0.5283
4.000 0.7814 0.01625 0.00975 -0.0466 0.3664 0.5980
4.250 0.8100 0.01642 0.01012 -0.0468 0.3663 0.6494
4.500 0.8375 0.01647 0.01053 -0.0467 0.3661 0.7526
4.750 0.8627 0.01654 0.01089 -0.0461 0.3659 0.8372
5.000 0.8859 0.01659 0.01116 -0.0448 0.3657 1.0000
5.250 0.9147 0.01692 0.01151 -0.0451 0.3655 1.0000
5.500 0.9437 0.01711 0.01169 -0.0453 0.3650 1.0000
5.750 0.9727 0.01724 0.01182 -0.0454 0.3645 1.0000
6.000 1.0017 0.01740 0.01196 -0.0455 0.3640 1.0000
6.250 1.0303 0.01767 0.01224 -0.0457 0.3637 1.0000
6.500 1.0588 0.01797 0.01256 -0.0459 0.3634 1.0000
6.750 1.0873 0.01823 0.01284 -0.0461 0.3631 1.0000
7.000 1.1158 0.01851 0.01313 -0.0462 0.3627 1.0000
7.250 1.1440 0.01884 0.01348 -0.0464 0.3623 1.0000
7.500 1.1720 0.01923 0.01389 -0.0466 0.3619 1.0000
7.750 1.1995 0.01965 0.01443 -0.0469 0.3610 1.0000
8.000 1.2265 0.02021 0.01513 -0.0473 0.3599 1.0000
8.250 1.2533 0.02078 0.01582 -0.0476 0.3587 1.0000
8.500 1.2802 0.02131 0.01644 -0.0479 0.3576 1.0000
8.750 1.3081 0.02147 0.01667 -0.0481 0.3562 1.0000
9.000 1.3375 0.02111 0.01633 -0.0480 0.3547 1.0000
9.250 1.3681 0.02041 0.01559 -0.0479 0.3532 1.0000
9.500 1.3985 0.01978 0.01493 -0.0477 0.3521 1.0000
9.750 1.4293 0.01907 0.01416 -0.0476 0.3510 1.0000
10.000 1.4582 0.01876 0.01395 -0.0477 0.3479 1.0000
10.250 1.4881 0.01818 0.01346 -0.0478 0.3425 1.0000
10.500 1.5205 0.01701 0.01224 -0.0477 0.3392 1.0000
10.750 1.5458 0.01788 0.01336 -0.0482 0.3325 1.0000
11.000 1.5722 0.01841 0.01405 -0.0485 0.3255 1.0000
11.250 1.6017 0.01814 0.01383 -0.0487 0.3081 1.0000
11.500 1.6362 0.01611 0.01110 -0.0487 0.2607 1.0000
11.750 1.6543 0.01822 0.01313 -0.0497 0.2323 1.0000
12.000 1.6673 0.02132 0.01620 -0.0514 0.2026 1.0000
12.250 1.6559 0.03140 0.02653 -0.0602 0.1807 1.0000
12.500 1.5874 0.04617 0.04162 -0.0722 0.1857 1.0000
12.750 1.5470 0.05335 0.04884 -0.0743 0.1818 1.0000
13.000 1.5199 0.05897 0.05445 -0.0756 0.1736 1.0000
13.250 1.5012 0.06397 0.05941 -0.0766 0.1647 1.0000
13.500 1.4874 0.06846 0.06385 -0.0775 0.1550 1.0000
13.750 1.4792 0.07238 0.06772 -0.0782 0.1446 1.0000
14.000 1.4713 0.07630 0.07160 -0.0789 0.1349 1.0000
14.250 1.4642 0.08018 0.07544 -0.0796 0.1256 1.0000
14.750 1.4552 0.08734 0.08251 -0.0807 0.1066 1.0000
15.000 1.4512 0.09094 0.08608 -0.0814 0.0981 1.0000
15.250 1.4466 0.09464 0.08974 -0.0820 0.0900 1.0000
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Polar data table (+)
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