YS-915 (ys915-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-915 (ys915-il) Reynolds number: 200,000 Max Cl/Cd: 51.63 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys915-il-200000-n5.txt Download as CSV file: xf-ys915-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: YS-915
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4923 0.10645 0.10290 -0.0366 1.0000 0.0074
-10.250 -0.4997 0.10327 0.09976 -0.0360 1.0000 0.0072
-10.000 -0.5082 0.10009 0.09663 -0.0353 1.0000 0.0071
-9.750 -0.5097 0.09524 0.09181 -0.0378 0.9987 0.0069
-9.500 -0.5069 0.08982 0.08640 -0.0419 0.9965 0.0068
-9.250 -0.5065 0.08356 0.08017 -0.0468 0.9941 0.0066
-9.000 -0.5070 0.07736 0.07399 -0.0519 0.9910 0.0064
-8.750 -0.5103 0.06875 0.06537 -0.0606 0.9869 0.0064
-8.500 -0.5155 0.06199 0.05847 -0.0697 0.9825 0.0063
-8.250 -0.5299 0.05774 0.05407 -0.0708 0.9759 0.0063
-8.000 -0.5326 0.05312 0.04922 -0.0726 0.9715 0.0061
-7.750 -0.5293 0.04857 0.04439 -0.0739 0.9685 0.0059
-7.500 -0.5327 0.04549 0.04106 -0.0715 0.9635 0.0057
-7.250 -0.5283 0.04162 0.03686 -0.0702 0.9603 0.0055
-7.000 -0.5181 0.03781 0.03265 -0.0693 0.9581 0.0053
-6.750 -0.5027 0.03430 0.02871 -0.0685 0.9564 0.0051
-6.500 -0.4973 0.03164 0.02568 -0.0649 0.9527 0.0049
-6.250 -0.4848 0.02918 0.02282 -0.0624 0.9502 0.0048
-6.000 -0.4674 0.02665 0.01988 -0.0606 0.9483 0.0047
-5.750 -0.4460 0.02446 0.01731 -0.0594 0.9467 0.0047
-5.500 -0.4232 0.02262 0.01518 -0.0584 0.9456 0.0047
-5.250 -0.3999 0.02108 0.01342 -0.0576 0.9447 0.0048
-5.000 -0.3761 0.01968 0.01184 -0.0569 0.9437 0.0052
-4.750 -0.3611 0.01869 0.01072 -0.0544 0.9412 0.0055
-4.500 -0.3465 0.01787 0.00968 -0.0518 0.9388 0.0064
-4.250 -0.3254 0.01731 0.00898 -0.0507 0.9368 0.0080
-4.000 -0.3034 0.01656 0.00812 -0.0498 0.9351 0.0144
-3.750 -0.2795 0.01580 0.00720 -0.0489 0.9337 0.0278
-3.500 -0.2635 0.01387 0.00669 -0.0480 0.9322 0.3275
-3.250 -0.2366 0.01366 0.00656 -0.0480 0.9311 0.3886
-3.000 -0.2098 0.01349 0.00653 -0.0481 0.9302 0.4481
-2.750 -0.1966 0.01348 0.00651 -0.0452 0.9265 0.4666
-2.500 -0.1734 0.01343 0.00633 -0.0444 0.9243 0.4814
-2.250 -0.1475 0.01337 0.00624 -0.0442 0.9224 0.4968
-2.000 -0.1201 0.01331 0.00617 -0.0443 0.9209 0.5132
-1.750 -0.0915 0.01324 0.00611 -0.0447 0.9196 0.5318
-1.500 -0.0621 0.01316 0.00607 -0.0452 0.9184 0.5541
-1.250 -0.0320 0.01307 0.00605 -0.0458 0.9173 0.5794
-1.000 -0.0194 0.01311 0.00617 -0.0428 0.9126 0.6040
-0.750 0.0048 0.01304 0.00618 -0.0422 0.9099 0.6368
-0.500 0.0318 0.01294 0.00622 -0.0421 0.9079 0.6765
-0.250 0.0605 0.01279 0.00627 -0.0423 0.9064 0.7262
0.000 0.0923 0.01265 0.00636 -0.0430 0.9052 0.7862
0.250 0.1362 0.01261 0.00655 -0.0465 0.9050 0.8586
0.500 0.2020 0.01273 0.00683 -0.0550 0.9061 0.9242
0.750 0.2553 0.01281 0.00697 -0.0608 0.9061 0.9642
1.000 0.3001 0.01285 0.00708 -0.0646 0.9054 0.9844
1.250 0.3464 0.01284 0.00714 -0.0688 0.9047 0.9957
1.750 0.4018 0.01282 0.00733 -0.0690 0.8946 1.0000
2.000 0.4479 0.01250 0.00715 -0.0726 0.8920 1.0000
2.250 0.4706 0.01232 0.00707 -0.0712 0.8824 1.0000
2.500 0.5319 0.01057 0.00546 -0.0758 0.8528 1.0000
2.750 0.5271 0.01021 0.00509 -0.0679 0.7998 1.0000
3.000 0.5511 0.01116 0.00410 -0.0655 0.3864 1.0000
3.250 0.5498 0.01252 0.00462 -0.0601 0.2055 1.0000
3.500 0.5550 0.01384 0.00522 -0.0561 0.0570 1.0000
3.750 0.5700 0.01459 0.00582 -0.0536 0.0283 1.0000
4.000 0.5865 0.01529 0.00665 -0.0512 0.0211 1.0000
4.250 0.6014 0.01617 0.00757 -0.0487 0.0129 1.0000
4.500 0.6176 0.01709 0.00861 -0.0462 0.0113 1.0000
4.750 0.6352 0.01824 0.00985 -0.0440 0.0103 1.0000
5.000 0.6573 0.01973 0.01145 -0.0426 0.0096 1.0000
5.250 0.6848 0.02158 0.01347 -0.0421 0.0092 1.0000
5.500 0.7137 0.02378 0.01593 -0.0417 0.0090 1.0000
5.750 0.7395 0.02613 0.01861 -0.0407 0.0087 1.0000
6.000 0.7553 0.02681 0.01948 -0.0391 0.0065 1.0000
6.250 0.7707 0.02993 0.02303 -0.0368 0.0052 1.0000
6.500 0.7887 0.03202 0.02548 -0.0345 0.0045 1.0000
6.750 0.8015 0.03514 0.02901 -0.0313 0.0044 1.0000
7.000 0.8106 0.03851 0.03278 -0.0277 0.0043 1.0000
7.250 0.8169 0.04190 0.03651 -0.0240 0.0043 1.0000
7.500 0.8202 0.04558 0.04052 -0.0201 0.0042 1.0000
7.750 0.8206 0.04921 0.04444 -0.0162 0.0042 1.0000
8.000 0.8184 0.05284 0.04833 -0.0124 0.0043 1.0000
8.250 0.8139 0.05635 0.05205 -0.0087 0.0043 1.0000
8.500 0.8060 0.05982 0.05572 -0.0050 0.0044 1.0000
8.750 0.7935 0.06298 0.05903 -0.0010 0.0044 1.0000
9.000 0.7792 0.06611 0.06227 0.0025 0.0045 1.0000
9.250 0.7634 0.06970 0.06598 0.0049 0.0045 1.0000
9.500 0.7487 0.07332 0.06970 0.0061 0.0046 1.0000
9.750 0.7326 0.07783 0.07430 0.0059 0.0046 1.0000
10.000 0.7169 0.08337 0.07991 0.0038 0.0046 1.0000
10.250 0.7049 0.09002 0.08661 -0.0007 0.0047 1.0000
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Polar data table (+)
Polar graphs
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