STRAND AIRFOIL (strand-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: STRAND AIRFOIL (strand-il) Reynolds number: 1,000,000 Max Cl/Cd: 141.69 at α=11.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-strand-il-1000000.txt Download as CSV file: xf-strand-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4842 0.09160 0.08807 0.0251 0.3785 0.0218
-8.250 -0.4846 0.08643 0.08292 0.0216 0.3784 0.0221
-8.000 -0.4880 0.08002 0.07652 0.0167 0.3783 0.0224
-7.750 -0.5363 0.05144 0.04731 -0.0242 0.3787 0.0235
-7.500 -0.5235 0.04769 0.04317 -0.0284 0.3785 0.0236
-7.250 -0.5046 0.04493 0.04014 -0.0305 0.3783 0.0237
-7.000 -0.4833 0.04246 0.03743 -0.0321 0.3780 0.0237
-6.750 -0.4603 0.04022 0.03495 -0.0333 0.3777 0.0237
-6.500 -0.4403 0.03464 0.02912 -0.0354 0.3776 0.0240
-6.250 -0.4152 0.03244 0.02689 -0.0361 0.3774 0.0241
-6.000 -0.3892 0.03072 0.02511 -0.0367 0.3772 0.0243
-5.750 -0.3625 0.02925 0.02355 -0.0372 0.3770 0.0244
-5.500 -0.3354 0.02793 0.02214 -0.0378 0.3768 0.0246
-5.250 -0.3078 0.02673 0.02085 -0.0382 0.3766 0.0248
-5.000 -0.2798 0.02564 0.01964 -0.0387 0.3764 0.0250
-4.750 -0.2514 0.02464 0.01853 -0.0391 0.3762 0.0254
-4.500 -0.2227 0.02378 0.01756 -0.0394 0.3760 0.0259
-4.250 -0.1934 0.02316 0.01680 -0.0396 0.3758 0.0267
-4.000 -0.1626 0.02403 0.01736 -0.0396 0.3756 0.0276
-3.750 -0.1330 0.02373 0.01690 -0.0398 0.3755 0.0277
-3.500 -0.1047 0.02096 0.01408 -0.0404 0.3753 0.0283
-3.250 -0.0760 0.02012 0.01330 -0.0406 0.3751 0.0286
-3.000 -0.0470 0.01957 0.01275 -0.0409 0.3750 0.0291
-2.750 -0.0178 0.01918 0.01236 -0.0411 0.3749 0.0298
-2.500 0.0118 0.01898 0.01209 -0.0412 0.3748 0.0311
-2.250 0.0418 0.01858 0.01155 -0.0413 0.3748 0.0329
-2.000 0.0706 0.01786 0.01094 -0.0415 0.3748 0.0337
-1.750 0.0999 0.01752 0.01062 -0.0416 0.3747 0.0349
-1.500 0.1298 0.01746 0.01045 -0.0418 0.3747 0.0381
-1.250 0.1587 0.01684 0.00998 -0.0420 0.3747 0.0395
-1.000 0.1883 0.01674 0.00989 -0.0421 0.3747 0.0416
-0.750 0.2176 0.01628 0.00950 -0.0425 0.3746 0.0461
-0.500 0.2473 0.01621 0.00946 -0.0426 0.3746 0.0485
0.000 0.3077 0.01612 0.00928 -0.0425 0.3746 0.0314
0.250 0.3378 0.01591 0.00909 -0.0428 0.3746 0.0299
0.500 0.3678 0.01586 0.00905 -0.0431 0.3745 0.0294
0.750 0.3978 0.01579 0.00899 -0.0433 0.3744 0.0295
1.000 0.4277 0.01573 0.00894 -0.0435 0.3743 0.0299
1.250 0.4575 0.01576 0.00898 -0.0438 0.3742 0.0304
1.500 0.4871 0.01587 0.00911 -0.0440 0.3742 0.0309
1.750 0.5167 0.01600 0.00926 -0.0442 0.3741 0.0314
2.000 0.5461 0.01616 0.00944 -0.0444 0.3741 0.0319
2.250 0.5756 0.01630 0.00960 -0.0446 0.3740 0.0331
2.500 0.6050 0.01648 0.00981 -0.0449 0.3739 0.0345
2.750 0.6343 0.01671 0.01005 -0.0451 0.3738 0.0360
3.000 0.6634 0.01695 0.01033 -0.0453 0.3738 0.0378
3.250 0.6925 0.01720 0.01064 -0.0455 0.3737 0.0480
3.500 0.7241 0.01657 0.01101 -0.0470 0.3736 0.4418
3.750 0.7533 0.01668 0.01143 -0.0474 0.3734 0.5397
4.000 0.7826 0.01669 0.01164 -0.0477 0.3730 0.6007
4.250 0.8118 0.01662 0.01179 -0.0479 0.3723 0.6692
4.500 0.8403 0.01658 0.01204 -0.0480 0.3717 0.7629
4.750 0.8654 0.01661 0.01243 -0.0474 0.3713 0.8726
5.000 0.8897 0.01677 0.01278 -0.0465 0.3709 1.0000
5.250 0.9186 0.01702 0.01305 -0.0468 0.3703 1.0000
5.500 0.9474 0.01727 0.01331 -0.0470 0.3696 1.0000
5.750 0.9761 0.01756 0.01362 -0.0472 0.3690 1.0000
6.000 1.0047 0.01782 0.01390 -0.0474 0.3685 1.0000
6.250 1.0332 0.01810 0.01421 -0.0476 0.3680 1.0000
6.500 1.0615 0.01845 0.01458 -0.0478 0.3676 1.0000
6.750 1.0901 0.01866 0.01480 -0.0479 0.3671 1.0000
7.000 1.1189 0.01875 0.01489 -0.0480 0.3666 1.0000
7.250 1.1477 0.01882 0.01496 -0.0481 0.3661 1.0000
7.500 1.1761 0.01901 0.01517 -0.0482 0.3657 1.0000
7.750 1.2047 0.01913 0.01530 -0.0483 0.3653 1.0000
8.000 1.2343 0.01886 0.01500 -0.0482 0.3647 1.0000
8.250 1.2646 0.01832 0.01438 -0.0481 0.3638 1.0000
8.500 1.2916 0.01898 0.01499 -0.0482 0.3618 1.0000
8.750 1.3220 0.01822 0.01428 -0.0482 0.3608 1.0000
9.000 1.3514 0.01791 0.01403 -0.0483 0.3594 1.0000
9.250 1.3818 0.01726 0.01338 -0.0482 0.3574 1.0000
9.500 1.4142 0.01597 0.01199 -0.0480 0.3550 1.0000
9.750 1.4464 0.01474 0.01066 -0.0479 0.3529 1.0000
10.000 1.4772 0.01404 0.00989 -0.0479 0.3514 1.0000
10.250 1.5065 0.01385 0.00967 -0.0479 0.3498 1.0000
10.500 1.5357 0.01358 0.00951 -0.0481 0.3480 1.0000
10.750 1.5652 0.01326 0.00928 -0.0483 0.3454 1.0000
11.000 1.5952 0.01284 0.00889 -0.0484 0.3428 1.0000
11.250 1.6259 0.01224 0.00829 -0.0485 0.3399 1.0000
11.500 1.6550 0.01214 0.00828 -0.0487 0.3347 1.0000
11.750 1.6847 0.01189 0.00810 -0.0489 0.3240 1.0000
12.000 1.7073 0.01307 0.00878 -0.0496 0.2524 1.0000
12.250 1.7264 0.01509 0.01067 -0.0503 0.2167 1.0000
12.500 1.7408 0.01791 0.01333 -0.0514 0.1786 1.0000
12.750 1.7525 0.02116 0.01651 -0.0531 0.1516 1.0000
13.000 1.7450 0.03013 0.02569 -0.0602 0.1359 1.0000
13.250 1.6523 0.04819 0.04425 -0.0740 0.1537 1.0000
13.500 1.6163 0.05475 0.05088 -0.0756 0.1511 1.0000
13.750 1.5873 0.06069 0.05683 -0.0769 0.1453 1.0000
14.000 1.5718 0.06528 0.06140 -0.0778 0.1368 1.0000
14.250 1.5581 0.06971 0.06577 -0.0785 0.1272 1.0000
14.500 1.5469 0.07397 0.07000 -0.0793 0.1181 1.0000
14.750 1.5393 0.07781 0.07379 -0.0799 0.1092 1.0000
15.000 1.5338 0.08142 0.07735 -0.0805 0.1002 1.0000
15.250 1.5283 0.08504 0.08092 -0.0810 0.0913 1.0000
15.500 1.5227 0.08876 0.08459 -0.0817 0.0830 1.0000
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Polar data table (+)
Polar graphs
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