STRAND AIRFOIL (strand-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: STRAND AIRFOIL (strand-il) Reynolds number: 1,000,000 Max Cl/Cd: 147.13 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-strand-il-1000000-n5.txt Download as CSV file: xf-strand-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5336 0.09236 0.08867 0.0268 0.3626 0.0167
-9.000 -0.5805 0.07220 0.06851 0.0126 0.3629 0.0167
-8.750 -0.6205 0.05405 0.05015 -0.0131 0.3631 0.0166
-8.500 -0.6197 0.04681 0.04259 -0.0234 0.3630 0.0166
-8.250 -0.6084 0.04219 0.03768 -0.0276 0.3628 0.0167
-8.000 -0.5914 0.03861 0.03385 -0.0301 0.3626 0.0167
-7.750 -0.5713 0.03556 0.03055 -0.0320 0.3624 0.0167
-7.500 -0.5490 0.03287 0.02761 -0.0334 0.3621 0.0167
-7.250 -0.5247 0.03042 0.02489 -0.0344 0.3619 0.0169
-7.000 -0.4996 0.02830 0.02255 -0.0353 0.3618 0.0169
-6.750 -0.4735 0.02638 0.02041 -0.0360 0.3617 0.0170
-6.500 -0.4466 0.02474 0.01856 -0.0365 0.3616 0.0170
-6.250 -0.4199 0.02275 0.01637 -0.0372 0.3616 0.0171
-6.000 -0.3921 0.02166 0.01517 -0.0376 0.3615 0.0172
-5.750 -0.3639 0.02082 0.01424 -0.0379 0.3614 0.0173
-5.500 -0.3355 0.02010 0.01343 -0.0381 0.3613 0.0174
-5.250 -0.3069 0.01943 0.01269 -0.0383 0.3612 0.0175
-5.000 -0.2781 0.01881 0.01200 -0.0385 0.3611 0.0176
-4.750 -0.2493 0.01824 0.01137 -0.0386 0.3610 0.0178
-4.500 -0.2203 0.01768 0.01075 -0.0388 0.3610 0.0179
-4.250 -0.1912 0.01714 0.01015 -0.0389 0.3609 0.0180
-4.000 -0.1621 0.01660 0.00956 -0.0390 0.3608 0.0182
-3.750 -0.1328 0.01608 0.00899 -0.0391 0.3607 0.0184
-3.500 -0.1036 0.01559 0.00846 -0.0392 0.3606 0.0185
-3.250 -0.0742 0.01512 0.00795 -0.0393 0.3605 0.0187
-3.000 -0.0449 0.01467 0.00747 -0.0394 0.3604 0.0188
-2.750 -0.0154 0.01426 0.00703 -0.0396 0.3603 0.0190
-2.500 0.0141 0.01388 0.00663 -0.0397 0.3602 0.0191
-2.250 0.0437 0.01352 0.00626 -0.0398 0.3601 0.0192
-2.000 0.0734 0.01322 0.00594 -0.0400 0.3599 0.0194
-1.750 0.1032 0.01298 0.00568 -0.0401 0.3597 0.0197
-1.500 0.1330 0.01276 0.00545 -0.0403 0.3596 0.0199
-1.250 0.1628 0.01254 0.00522 -0.0405 0.3594 0.0200
-1.000 0.1927 0.01237 0.00504 -0.0407 0.3593 0.0201
-0.750 0.2228 0.01210 0.00476 -0.0409 0.3592 0.0204
-0.500 0.2528 0.01193 0.00459 -0.0412 0.3591 0.0206
-0.250 0.2828 0.01182 0.00449 -0.0414 0.3590 0.0209
0.000 0.3127 0.01175 0.00442 -0.0416 0.3589 0.0213
0.250 0.3425 0.01168 0.00436 -0.0417 0.3588 0.0216
0.500 0.3724 0.01164 0.00431 -0.0419 0.3587 0.0220
0.750 0.4023 0.01160 0.00428 -0.0421 0.3585 0.0225
1.000 0.4321 0.01158 0.00426 -0.0422 0.3584 0.0229
1.250 0.4619 0.01157 0.00427 -0.0424 0.3583 0.0232
1.500 0.4917 0.01158 0.00429 -0.0425 0.3582 0.0236
1.750 0.5215 0.01157 0.00429 -0.0427 0.3581 0.0244
2.000 0.5512 0.01159 0.00433 -0.0429 0.3580 0.0253
2.250 0.5809 0.01163 0.00438 -0.0430 0.3579 0.0260
2.500 0.6105 0.01168 0.00445 -0.0432 0.3578 0.0268
2.750 0.6401 0.01175 0.00453 -0.0433 0.3576 0.0276
3.000 0.6697 0.01182 0.00462 -0.0435 0.3575 0.0289
3.250 0.6991 0.01190 0.00472 -0.0436 0.3574 0.0306
3.500 0.7286 0.01199 0.00485 -0.0437 0.3573 0.0349
3.750 0.7601 0.01143 0.00498 -0.0448 0.3572 0.3381
4.000 0.7899 0.01133 0.00517 -0.0453 0.3571 0.4390
4.250 0.8195 0.01137 0.00537 -0.0455 0.3570 0.4899
4.500 0.8489 0.01142 0.00557 -0.0458 0.3569 0.5412
4.750 0.8783 0.01148 0.00578 -0.0460 0.3568 0.5896
5.000 0.9076 0.01149 0.00597 -0.0463 0.3566 0.6428
5.250 0.9368 0.01142 0.00614 -0.0464 0.3562 0.7244
5.500 0.9659 0.01141 0.00626 -0.0465 0.3557 0.7665
5.750 0.9945 0.01140 0.00637 -0.0465 0.3553 0.8074
6.000 1.0206 0.01130 0.00651 -0.0459 0.3550 0.8839
6.250 1.0465 0.01125 0.00660 -0.0453 0.3547 1.0000
6.500 1.0757 0.01139 0.00675 -0.0454 0.3544 1.0000
6.750 1.1048 0.01156 0.00694 -0.0456 0.3542 1.0000
7.000 1.1338 0.01174 0.00715 -0.0458 0.3540 1.0000
7.250 1.1628 0.01189 0.00732 -0.0460 0.3538 1.0000
7.500 1.1919 0.01200 0.00744 -0.0461 0.3534 1.0000
7.750 1.2209 0.01209 0.00755 -0.0463 0.3530 1.0000
8.000 1.2500 0.01216 0.00764 -0.0464 0.3526 1.0000
8.250 1.2794 0.01207 0.00754 -0.0466 0.3518 1.0000
8.500 1.3089 0.01191 0.00735 -0.0467 0.3504 1.0000
8.750 1.3382 0.01177 0.00727 -0.0468 0.3488 1.0000
9.000 1.3676 0.01165 0.00721 -0.0470 0.3471 1.0000
9.250 1.3974 0.01138 0.00699 -0.0472 0.3443 1.0000
9.500 1.4281 0.01083 0.00641 -0.0473 0.3403 1.0000
9.750 1.4576 0.01070 0.00634 -0.0475 0.3354 1.0000
10.000 1.4870 0.01061 0.00630 -0.0477 0.3290 1.0000
10.250 1.5169 0.01031 0.00581 -0.0480 0.2927 1.0000
10.500 1.5397 0.01190 0.00716 -0.0486 0.2501 1.0000
10.750 1.5634 0.01320 0.00837 -0.0491 0.2240 1.0000
11.000 1.5856 0.01475 0.00981 -0.0498 0.1944 1.0000
11.250 1.6060 0.01665 0.01159 -0.0506 0.1655 1.0000
11.500 1.6248 0.01875 0.01361 -0.0518 0.1418 1.0000
11.750 1.6420 0.02117 0.01600 -0.0533 0.1223 1.0000
12.000 1.6503 0.02633 0.02123 -0.0573 0.1062 1.0000
12.250 1.5762 0.04543 0.04090 -0.0747 0.1186 1.0000
12.500 1.5406 0.05206 0.04761 -0.0766 0.1179 1.0000
12.750 1.5174 0.05731 0.05289 -0.0778 0.1141 1.0000
13.000 1.5037 0.06168 0.05726 -0.0786 0.1075 1.0000
13.250 1.4957 0.06545 0.06100 -0.0792 0.1003 1.0000
13.500 1.4880 0.06922 0.06472 -0.0798 0.0920 1.0000
13.750 1.4815 0.07295 0.06843 -0.0804 0.0840 1.0000
14.000 1.4766 0.07648 0.07193 -0.0810 0.0765 1.0000
14.250 1.4733 0.07985 0.07525 -0.0814 0.0690 1.0000
14.750 1.4719 0.08600 0.08134 -0.0823 0.0568 1.0000
15.000 1.4701 0.08930 0.08463 -0.0828 0.0524 1.0000
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