STRAND AIRFOIL (strand-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: STRAND AIRFOIL (strand-il) Reynolds number: 500,000 Max Cl/Cd: 92.4 at α=13° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-strand-il-500000.txt Download as CSV file: xf-strand-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4729 0.10358 0.09949 0.0282 0.4013 0.0287
-8.750 -0.4689 0.09979 0.09572 0.0262 0.4012 0.0290
-8.500 -0.4658 0.09571 0.09166 0.0237 0.4012 0.0293
-8.250 -0.4082 0.06978 0.06588 -0.0001 0.4018 0.0319
-8.000 -0.4349 0.05989 0.05593 -0.0091 0.4019 0.0319
-7.750 -0.4523 0.05335 0.04932 -0.0164 0.4019 0.0317
-7.500 -0.4727 0.04518 0.04059 -0.0282 0.4019 0.0320
-7.250 -0.4667 0.04050 0.03541 -0.0320 0.4019 0.0321
-7.000 -0.4530 0.03482 0.02967 -0.0335 0.4019 0.0325
-6.750 -0.4335 0.03184 0.02673 -0.0340 0.4018 0.0328
-6.500 -0.4127 0.02940 0.02427 -0.0348 0.4017 0.0330
-6.250 -0.3908 0.02712 0.02192 -0.0356 0.4016 0.0334
-6.000 -0.3680 0.02499 0.01968 -0.0365 0.4016 0.0339
-5.750 -0.3442 0.02302 0.01757 -0.0373 0.4016 0.0346
-5.500 -0.3188 0.02130 0.01564 -0.0381 0.4015 0.0357
-5.250 -0.2915 0.01930 0.01301 -0.0391 0.4015 0.0377
-5.000 -0.2669 0.01758 0.01137 -0.0396 0.4015 0.0383
-4.750 -0.2410 0.01639 0.01018 -0.0400 0.4015 0.0391
-4.500 -0.2140 0.01542 0.00913 -0.0404 0.4015 0.0402
-4.250 -0.1834 0.01600 0.00932 -0.0403 0.4017 0.0430
-4.000 -0.1586 0.01349 0.00684 -0.0413 0.4017 0.0446
-3.750 -0.1314 0.01278 0.00613 -0.0416 0.4017 0.0461
-3.500 -0.1025 0.01234 0.00542 -0.0420 0.4018 0.0511
-3.250 -0.0757 0.01155 0.00476 -0.0424 0.4019 0.0529
-3.000 -0.0474 0.01116 0.00422 -0.0429 0.4019 0.0598
-2.750 -0.0200 0.01059 0.00379 -0.0432 0.4017 0.0632
-1.250 0.1666 0.02897 0.02255 -0.0531 0.4404 0.0570
-1.000 0.1954 0.02894 0.02248 -0.0529 0.4399 0.0479
-0.750 0.2240 0.02926 0.02270 -0.0528 0.4394 0.0440
-0.500 0.2520 0.02954 0.02301 -0.0530 0.4389 0.0423
-0.250 0.2801 0.02974 0.02322 -0.0532 0.4385 0.0406
0.000 0.3079 0.03026 0.02370 -0.0534 0.4380 0.0392
0.250 0.3347 0.03122 0.02460 -0.0534 0.4374 0.0385
0.500 0.3693 0.03160 0.02531 -0.0580 0.4259 0.0383
0.750 0.3973 0.03178 0.02548 -0.0581 0.4249 0.0385
1.000 0.4251 0.03197 0.02564 -0.0580 0.4241 0.0389
1.250 0.4528 0.03227 0.02592 -0.0580 0.4235 0.0395
1.500 0.4802 0.03271 0.02634 -0.0581 0.4231 0.0402
1.750 0.5074 0.03322 0.02682 -0.0580 0.4226 0.0419
2.000 0.5342 0.03380 0.02736 -0.0579 0.4221 0.0431
2.250 0.5608 0.03446 0.02797 -0.0576 0.4217 0.0447
2.500 0.5867 0.03543 0.02889 -0.0573 0.4212 0.0476
2.750 0.6166 0.03697 0.03114 -0.0640 0.4084 0.2143
3.000 0.6445 0.03687 0.03166 -0.0645 0.4077 0.4184
3.250 0.6712 0.03697 0.03210 -0.0643 0.4072 0.5364
3.500 0.6977 0.03707 0.03241 -0.0637 0.4067 0.6110
3.750 0.7235 0.03711 0.03272 -0.0628 0.4063 0.7008
4.000 0.7474 0.03720 0.03306 -0.0614 0.4058 0.7958
4.250 0.7646 0.03723 0.03338 -0.0584 0.4054 1.0000
4.500 0.7941 0.03627 0.03249 -0.0600 0.3920 1.0000
4.750 0.8259 0.03410 0.03015 -0.0569 0.3913 1.0000
5.000 0.8563 0.03289 0.02879 -0.0550 0.3907 1.0000
5.250 0.8856 0.03238 0.02816 -0.0538 0.3902 1.0000
5.500 0.8987 0.03809 0.03429 -0.0613 0.3787 1.0000
5.750 0.9268 0.03773 0.03389 -0.0603 0.3782 1.0000
6.000 0.9550 0.03734 0.03345 -0.0593 0.3777 1.0000
6.250 0.9834 0.03697 0.03304 -0.0584 0.3773 1.0000
6.500 1.0117 0.03664 0.03268 -0.0576 0.3769 1.0000
6.750 1.0399 0.03645 0.03245 -0.0568 0.3765 1.0000
7.000 1.0679 0.03634 0.03232 -0.0562 0.3762 1.0000
7.250 1.0960 0.03626 0.03221 -0.0556 0.3759 1.0000
7.500 1.1239 0.03629 0.03221 -0.0550 0.3756 1.0000
7.750 1.1112 0.04606 0.04247 -0.0673 0.3548 1.0000
8.000 1.1385 0.04568 0.04210 -0.0663 0.3540 1.0000
8.250 1.1670 0.04500 0.04141 -0.0651 0.3536 1.0000
8.500 1.1957 0.04427 0.04069 -0.0638 0.3532 1.0000
8.750 1.2244 0.04358 0.04001 -0.0627 0.3529 1.0000
9.000 1.2538 0.04274 0.03917 -0.0615 0.3527 1.0000
9.250 1.2844 0.04169 0.03813 -0.0602 0.3526 1.0000
9.500 1.3160 0.04047 0.03691 -0.0588 0.3525 1.0000
9.750 1.3478 0.03928 0.03571 -0.0576 0.3524 1.0000
10.000 1.3816 0.03771 0.03414 -0.0562 0.3524 1.0000
10.250 1.4228 0.03467 0.03101 -0.0541 0.3527 1.0000
10.500 1.4682 0.03072 0.02692 -0.0518 0.3528 1.0000
10.750 1.5078 0.02799 0.02406 -0.0506 0.3523 1.0000
11.000 1.5430 0.02626 0.02226 -0.0499 0.3516 1.0000
11.250 1.5782 0.02456 0.02047 -0.0493 0.3508 1.0000
11.500 1.6010 0.02520 0.02134 -0.0498 0.3463 1.0000
11.750 1.6319 0.02428 0.02047 -0.0497 0.3430 1.0000
12.000 1.6676 0.02244 0.01859 -0.0493 0.3409 1.0000
12.250 1.6980 0.02170 0.01794 -0.0493 0.3363 1.0000
12.500 1.6501 0.03726 0.03438 -0.0596 0.3056 1.0000
12.750 1.7609 0.02020 0.01661 -0.0498 0.3005 1.0000
13.000 1.7889 0.01936 0.01504 -0.0502 0.2503 1.0000
13.250 1.7921 0.02374 0.01941 -0.0527 0.2187 1.0000
13.500 1.7241 0.04194 0.03811 -0.0686 0.2173 1.0000
13.750 1.6660 0.05117 0.04742 -0.0716 0.2160 1.0000
14.000 1.6240 0.05837 0.05461 -0.0734 0.2092 1.0000
14.250 1.5955 0.06427 0.06045 -0.0746 0.1978 1.0000
14.500 1.5736 0.06969 0.06580 -0.0758 0.1854 1.0000
14.750 1.5579 0.07446 0.07049 -0.0767 0.1728 1.0000
15.000 1.5447 0.07901 0.07497 -0.0776 0.1609 1.0000
15.250 1.5326 0.08350 0.07939 -0.0785 0.1496 1.0000
15.500 1.5229 0.08773 0.08355 -0.0793 0.1382 1.0000
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Polar data table (+)
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