YS-900 (ys900-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: YS-900 (ys900-il) Reynolds number: 1,000,000 Max Cl/Cd: 22.72 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ys900-il-1000000.txt Download as CSV file: xf-ys900-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: YS-900
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5227 0.08881 0.08723 -0.0486 0.9887 0.0039
-9.500 -0.5243 0.08379 0.08222 -0.0527 0.9880 0.0043
-9.250 -0.5344 0.07846 0.07688 -0.0574 0.9871 0.0042
-9.000 -0.5511 0.07393 0.07231 -0.0586 0.9862 0.0038
-8.750 -0.5584 0.07070 0.06902 -0.0581 0.9853 0.0042
-8.500 -0.5739 0.06749 0.06574 -0.0560 0.9842 0.0040
-8.250 -0.5755 0.06477 0.06293 -0.0538 0.9832 0.0044
-6.750 -0.5935 0.05136 0.04894 -0.0289 0.9741 0.0051
-6.500 -0.5878 0.04836 0.04579 -0.0260 0.9729 0.0051
-6.250 -0.5797 0.04528 0.04252 -0.0232 0.9718 0.0051
-6.000 -0.5670 0.04222 0.03926 -0.0213 0.9709 0.0052
-5.750 -0.5520 0.03927 0.03610 -0.0194 0.9701 0.0052
-5.500 -0.5653 0.03791 0.03462 -0.0110 0.9653 0.0052
-5.250 -0.5577 0.03557 0.03208 -0.0071 0.9628 0.0052
-5.000 -0.5438 0.03307 0.02931 -0.0043 0.9610 0.0052
-4.750 -0.5394 0.02709 0.02285 0.0004 0.9593 0.0057
-4.500 -0.5207 0.02431 0.01981 0.0020 0.9585 0.0063
-4.250 -0.4975 0.02264 0.01796 0.0026 0.9578 0.0071
-4.000 -0.4712 0.02119 0.01632 0.0028 0.9574 0.0083
-3.750 -0.4721 0.02029 0.01530 0.0092 0.9517 0.0090
-3.500 -0.4478 0.01927 0.01413 0.0103 0.9501 0.0110
-3.250 -0.4197 0.01989 0.01466 0.0107 0.9485 0.0132
-2.000 -0.2740 0.01248 0.00667 0.0107 0.9462 0.0117
-1.750 -0.2453 0.01179 0.00579 0.0109 0.9454 0.0068
-1.500 -0.2130 0.01155 0.00551 0.0098 0.9449 0.0054
-1.250 -0.1803 0.01136 0.00519 0.0086 0.9443 0.0050
-1.000 -0.1467 0.01129 0.00507 0.0071 0.9438 0.0050
-0.750 -0.1483 0.01107 0.00485 0.0137 0.9354 0.0056
-0.500 -0.0667 0.01078 0.00789 0.0028 0.9450 0.9358
-0.250 -0.0201 0.01090 0.00800 -0.0016 0.9449 0.9366
0.000 0.0254 0.01093 0.00802 -0.0059 0.9447 0.9372
0.250 0.0728 0.01084 0.00794 -0.0106 0.9443 0.9372
0.500 0.1617 0.00828 0.00436 -0.0219 0.6773 0.9325
0.750 0.1514 0.01108 0.00484 -0.0144 0.0077 0.9356
1.000 0.1820 0.01121 0.00497 -0.0152 0.0049 0.9371
1.250 0.2070 0.01136 0.00518 -0.0147 0.0050 0.9397
1.500 0.2166 0.01155 0.00550 -0.0106 0.0052 0.9450
1.750 0.2488 0.01178 0.00577 -0.0117 0.0063 0.9455
2.000 0.2788 0.01227 0.00641 -0.0119 0.0098 0.9462
3.750 0.4460 0.01993 0.01486 -0.0037 0.0108 0.9571
4.000 0.4753 0.02112 0.01623 -0.0037 0.0086 0.9575
4.250 0.5017 0.02258 0.01789 -0.0034 0.0075 0.9580
4.500 0.5254 0.02418 0.01968 -0.0028 0.0066 0.9586
4.750 0.5466 0.02621 0.02194 -0.0019 0.0061 0.9594
5.750 0.5558 0.03909 0.03589 0.0184 0.0052 0.9702
6.000 0.5708 0.04205 0.03907 0.0203 0.0052 0.9710
6.250 0.5829 0.04515 0.04238 0.0225 0.0052 0.9720
6.500 0.5913 0.04807 0.04549 0.0252 0.0052 0.9730
6.750 0.5983 0.05092 0.04850 0.0281 0.0051 0.9742
7.000 0.6021 0.05382 0.05154 0.0313 0.0051 0.9757
7.250 0.6103 0.05549 0.05332 0.0345 0.0048 0.9769
7.500 0.6117 0.05765 0.05558 0.0383 0.0046 0.9786
7.750 0.6095 0.05932 0.05734 0.0432 0.0042 0.9802
8.250 0.5885 0.06386 0.06202 0.0530 0.0037 0.9831
8.500 0.5837 0.06699 0.06524 0.0551 0.0032 0.9841
8.750 0.5680 0.07022 0.06853 0.0574 0.0038 0.9853
9.000 0.5556 0.07370 0.07207 0.0582 0.0037 0.9863
9.250 0.5444 0.07782 0.07624 0.0571 0.0035 0.9872
9.500 0.5302 0.08326 0.08170 0.0527 0.0041 0.9881
9.750 0.5261 0.08853 0.08695 0.0484 0.0039 0.9889
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Polar data table (+)
Polar graphs
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