YS-930 (ys930-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-930 (ys930-il) Reynolds number: 50,000 Max Cl/Cd: 28.44 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys930-il-50000-n5.txt Download as CSV file: xf-ys930-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: YS-930
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4513 0.10134 0.09474 -0.0459 1.0000 0.0378
-9.250 -0.4600 0.09788 0.09140 -0.0456 1.0000 0.0374
-9.000 -0.4697 0.09474 0.08837 -0.0449 1.0000 0.0370
-8.750 -0.4823 0.09154 0.08528 -0.0441 1.0000 0.0367
-8.500 -0.4967 0.08849 0.08235 -0.0431 1.0000 0.0362
-8.250 -0.5140 0.08543 0.07941 -0.0419 1.0000 0.0359
-8.000 -0.5327 0.08252 0.07661 -0.0406 1.0000 0.0353
-7.750 -0.5500 0.07830 0.07248 -0.0411 1.0000 0.0347
-7.500 -0.5654 0.07270 0.06689 -0.0433 1.0000 0.0336
-7.250 -0.5801 0.06699 0.06108 -0.0452 1.0000 0.0327
-7.000 -0.5901 0.06134 0.05519 -0.0469 1.0000 0.0321
-6.750 -0.5925 0.05649 0.05004 -0.0478 1.0000 0.0325
-6.500 -0.5893 0.05169 0.04479 -0.0486 1.0000 0.0323
-6.250 -0.5807 0.04739 0.04001 -0.0488 1.0000 0.0328
-6.000 -0.5675 0.04347 0.03553 -0.0488 1.0000 0.0333
-5.750 -0.5508 0.04000 0.03150 -0.0485 1.0000 0.0343
-5.500 -0.5318 0.03718 0.02815 -0.0478 1.0000 0.0356
-5.250 -0.5112 0.03468 0.02514 -0.0469 1.0000 0.0378
-5.000 -0.4910 0.03262 0.02262 -0.0462 1.0000 0.0436
-4.750 -0.4701 0.03094 0.02063 -0.0454 1.0000 0.0511
-4.500 -0.4485 0.02914 0.01862 -0.0444 1.0000 0.0568
-4.250 -0.4259 0.02756 0.01682 -0.0437 1.0000 0.0681
-4.000 -0.4017 0.02567 0.01532 -0.0440 1.0000 0.1139
-3.750 -0.3796 0.02536 0.01526 -0.0434 1.0000 0.2286
-3.500 -0.3563 0.02590 0.01576 -0.0434 0.9978 0.2970
-3.250 -0.3298 0.02600 0.01562 -0.0435 0.9953 0.3312
-3.000 -0.3022 0.02580 0.01514 -0.0438 0.9932 0.3478
-2.750 -0.2742 0.02559 0.01453 -0.0441 0.9908 0.3617
-2.500 -0.2455 0.02542 0.01413 -0.0447 0.9883 0.3755
-2.250 -0.2163 0.02531 0.01382 -0.0453 0.9860 0.3898
-2.000 -0.1865 0.02525 0.01362 -0.0461 0.9836 0.4064
-1.750 -0.1576 0.02519 0.01344 -0.0467 0.9811 0.4264
-1.500 -0.1308 0.02506 0.01330 -0.0470 0.9783 0.4486
-1.250 -0.1030 0.02497 0.01317 -0.0474 0.9753 0.4802
-1.000 -0.0750 0.02487 0.01323 -0.0479 0.9725 0.5255
-0.750 -0.0470 0.02473 0.01340 -0.0481 0.9699 0.5986
-0.500 -0.0254 0.02424 0.01349 -0.0465 0.9667 0.7407
-0.250 0.0136 0.02403 0.01337 -0.0492 0.9626 1.0000
0.000 0.0444 0.02447 0.01349 -0.0505 0.9590 1.0000
0.250 0.0732 0.02487 0.01369 -0.0514 0.9551 1.0000
0.500 0.0996 0.02522 0.01389 -0.0518 0.9504 1.0000
0.750 0.1302 0.02570 0.01423 -0.0530 0.9463 1.0000
1.000 0.1582 0.02613 0.01457 -0.0537 0.9417 1.0000
1.250 0.1850 0.02653 0.01489 -0.0541 0.9363 1.0000
1.500 0.2174 0.02707 0.01538 -0.0556 0.9320 1.0000
1.750 0.2418 0.02746 0.01575 -0.0556 0.9258 1.0000
2.000 0.2725 0.02797 0.01626 -0.0567 0.9204 1.0000
2.250 0.3000 0.02843 0.01679 -0.0573 0.9142 1.0000
2.500 0.3293 0.02892 0.01733 -0.0581 0.9078 1.0000
2.750 0.3572 0.02940 0.01788 -0.0587 0.9010 1.0000
3.000 0.3875 0.02989 0.01847 -0.0597 0.8939 1.0000
3.250 0.4138 0.03035 0.01905 -0.0599 0.8857 1.0000
3.500 0.4488 0.03085 0.01982 -0.0616 0.8789 1.0000
3.750 0.4733 0.03127 0.02040 -0.0614 0.8688 1.0000
4.000 0.5017 0.03170 0.02105 -0.0618 0.8591 1.0000
4.250 0.5358 0.03208 0.02169 -0.0631 0.8499 1.0000
4.500 0.5691 0.03236 0.02228 -0.0641 0.8392 1.0000
4.750 0.6000 0.03254 0.02291 -0.0644 0.8262 1.0000
5.000 0.6355 0.03249 0.02327 -0.0651 0.8121 1.0000
5.750 0.7364 0.02589 0.01482 -0.0512 0.1920 1.0000
6.000 0.7380 0.02877 0.01662 -0.0478 0.0873 1.0000
6.250 0.7519 0.03071 0.01842 -0.0456 0.0638 1.0000
6.500 0.7712 0.03255 0.02033 -0.0440 0.0522 1.0000
6.750 0.8008 0.03438 0.02240 -0.0440 0.0406 1.0000
7.000 0.8676 0.03745 0.02594 -0.0484 0.0351 1.0000
7.250 0.9142 0.04086 0.02969 -0.0504 0.0326 1.0000
7.500 0.9435 0.04486 0.03388 -0.0510 0.0296 1.0000
7.750 0.9617 0.04744 0.03704 -0.0490 0.0276 1.0000
8.000 0.9763 0.05049 0.04063 -0.0467 0.0260 1.0000
8.250 0.9864 0.05386 0.04447 -0.0441 0.0254 1.0000
8.500 0.9917 0.05734 0.04840 -0.0412 0.0252 1.0000
8.750 0.9926 0.06084 0.05229 -0.0380 0.0252 1.0000
9.000 0.9897 0.06428 0.05608 -0.0347 0.0253 1.0000
9.250 0.9823 0.06776 0.05986 -0.0313 0.0253 1.0000
9.500 0.9717 0.07092 0.06327 -0.0278 0.0255 1.0000
9.750 0.9574 0.07437 0.06695 -0.0246 0.0256 1.0000
10.000 0.9427 0.07788 0.07065 -0.0222 0.0258 1.0000
10.250 0.9260 0.08174 0.07468 -0.0205 0.0260 1.0000
10.500 0.9082 0.08602 0.07912 -0.0199 0.0261 1.0000
10.750 0.8906 0.09068 0.08391 -0.0202 0.0263 1.0000
11.000 0.8728 0.09597 0.08930 -0.0217 0.0266 1.0000
11.250 0.8570 0.10175 0.09515 -0.0242 0.0268 1.0000
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Polar data table (+)
Polar graphs
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