YS-915 (ys915-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: YS-915 (ys915-il) Reynolds number: 200,000 Max Cl/Cd: 54.02 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ys915-il-200000.txt Download as CSV file: xf-ys915-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5490 0.09186 0.08870 -0.0407 1.0000 0.0343
-9.000 -0.5633 0.08780 0.08465 -0.0418 1.0000 0.0343
-8.750 -0.5824 0.08404 0.08090 -0.0428 1.0000 0.0343
-8.500 -0.6015 0.08120 0.07806 -0.0419 1.0000 0.0342
-8.250 -0.6221 0.07883 0.07567 -0.0393 1.0000 0.0341
-8.000 -0.6401 0.07588 0.07263 -0.0378 1.0000 0.0342
-7.750 -0.6544 0.07297 0.06958 -0.0361 1.0000 0.0343
-7.500 -0.6636 0.07010 0.06653 -0.0344 1.0000 0.0344
-7.250 -0.6708 0.06713 0.06333 -0.0325 1.0000 0.0345
-7.000 -0.6833 0.05998 0.05602 -0.0315 1.0000 0.0352
-6.750 -0.6802 0.05480 0.05092 -0.0306 1.0000 0.0366
-6.500 -0.6750 0.05152 0.04758 -0.0292 1.0000 0.0382
-6.250 -0.6685 0.04853 0.04433 -0.0278 1.0000 0.0403
-6.000 -0.6596 0.04584 0.04125 -0.0259 1.0000 0.0447
-4.250 -0.5321 0.02337 0.01574 -0.0127 1.0000 0.0246
-4.000 -0.5089 0.02169 0.01383 -0.0112 1.0000 0.0242
-3.750 -0.4863 0.02058 0.01258 -0.0099 1.0000 0.0236
-3.500 -0.4644 0.01924 0.01117 -0.0085 1.0000 0.0235
-3.250 -0.4438 0.01785 0.00971 -0.0071 1.0000 0.0244
-3.000 -0.4228 0.01682 0.00859 -0.0058 1.0000 0.0271
-2.750 -0.4006 0.01595 0.00751 -0.0045 1.0000 0.0425
-2.500 -0.3851 0.01384 0.00724 -0.0030 1.0000 0.4423
-2.250 -0.3654 0.01375 0.00734 -0.0017 1.0000 0.5088
-2.000 -0.3368 0.01389 0.00760 -0.0021 0.9973 0.5622
-1.750 -0.3027 0.01415 0.00789 -0.0037 0.9939 0.5953
-1.500 -0.2732 0.01413 0.00795 -0.0043 0.9898 0.6290
-1.250 -0.2431 0.01418 0.00812 -0.0051 0.9862 0.6758
-1.000 -0.2118 0.01430 0.00856 -0.0058 0.9832 0.7551
-0.750 -0.1205 0.01420 0.00889 -0.0195 0.9857 1.0000
-0.500 -0.0821 0.01474 0.00928 -0.0223 0.9825 1.0000
-0.250 -0.0562 0.01476 0.00916 -0.0225 0.9769 1.0000
0.000 -0.0222 0.01508 0.00939 -0.0244 0.9727 1.0000
0.250 0.0158 0.01555 0.00979 -0.0270 0.9692 1.0000
0.500 0.0406 0.01559 0.00979 -0.0268 0.9627 1.0000
0.750 0.0775 0.01594 0.01011 -0.0292 0.9586 1.0000
1.000 0.1067 0.01614 0.01029 -0.0299 0.9525 1.0000
1.250 0.1407 0.01637 0.01053 -0.0316 0.9471 1.0000
1.500 0.1805 0.01672 0.01090 -0.0344 0.9430 1.0000
1.750 0.2071 0.01679 0.01100 -0.0345 0.9349 1.0000
2.000 0.2524 0.01707 0.01140 -0.0382 0.9311 1.0000
2.250 0.2785 0.01708 0.01147 -0.0381 0.9216 1.0000
2.500 0.3284 0.01721 0.01173 -0.0426 0.9176 1.0000
2.750 0.3588 0.01710 0.01172 -0.0430 0.9070 1.0000
3.000 0.4024 0.01679 0.01159 -0.0457 0.8963 1.0000
3.250 0.5710 0.01057 0.00598 -0.0656 0.8084 1.0000
3.500 0.5627 0.01328 0.00518 -0.0569 0.1181 1.0000
3.750 0.5672 0.01494 0.00637 -0.0522 0.0421 1.0000
4.000 0.5801 0.01603 0.00749 -0.0491 0.0283 1.0000
4.250 0.5967 0.01699 0.00851 -0.0466 0.0243 1.0000
4.500 0.6162 0.01833 0.00987 -0.0447 0.0216 1.0000
4.750 0.6439 0.02012 0.01181 -0.0441 0.0216 1.0000
5.000 0.6787 0.02253 0.01445 -0.0445 0.0228 1.0000
5.250 0.7122 0.02576 0.01807 -0.0442 0.0264 1.0000
6.750 0.8148 0.04508 0.03978 -0.0262 0.0496 1.0000
16.000 0.5975 0.18326 0.18009 -0.0404 0.0185 1.0000
16.250 0.6009 0.18647 0.18330 -0.0422 0.0184 1.0000
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Polar data table (+)
Polar graphs
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