S2055 (s2055-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2055 (s2055-il) Reynolds number: 200,000 Max Cl/Cd: 70.13 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2055-il-200000.txt Download as CSV file: xf-s2055-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S2055
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4823 0.08647 0.08302 -0.0336 1.0000 0.0431
-8.250 -0.4935 0.08247 0.07908 -0.0373 1.0000 0.0432
-8.000 -0.5013 0.07866 0.07524 -0.0396 1.0000 0.0434
-7.750 -0.5079 0.07511 0.07160 -0.0405 1.0000 0.0436
-7.500 -0.5122 0.07187 0.06825 -0.0403 1.0000 0.0437
-7.250 -0.5190 0.06504 0.06153 -0.0396 1.0000 0.0448
-7.000 -0.5148 0.06238 0.05893 -0.0376 1.0000 0.0458
-6.750 -0.5121 0.05978 0.05633 -0.0360 1.0000 0.0470
-6.500 -0.5098 0.05692 0.05341 -0.0347 1.0000 0.0485
-6.250 -0.5068 0.05384 0.05024 -0.0335 1.0000 0.0505
-6.000 -0.5012 0.05217 0.04795 -0.0323 1.0000 0.0561
-5.750 -0.5015 0.04644 0.04205 -0.0311 1.0000 0.0574
-5.500 -0.4921 0.04319 0.03890 -0.0297 1.0000 0.0589
-5.250 -0.4814 0.04084 0.03650 -0.0281 1.0000 0.0610
-5.000 -0.4692 0.03840 0.03387 -0.0265 1.0000 0.0647
-4.750 -0.4570 0.03533 0.03030 -0.0251 1.0000 0.0719
-4.500 -0.4297 0.02604 0.01978 -0.0217 1.0000 0.0311
-4.250 -0.4094 0.02323 0.01653 -0.0203 1.0000 0.0307
-4.000 -0.3876 0.02132 0.01416 -0.0191 1.0000 0.0329
-3.750 -0.3638 0.01912 0.01165 -0.0182 1.0000 0.0335
-3.500 -0.3407 0.01760 0.00998 -0.0172 1.0000 0.0347
-3.250 -0.3139 0.01654 0.00884 -0.0170 0.9990 0.0380
-3.000 -0.2775 0.01574 0.00793 -0.0187 0.9956 0.0447
-2.750 -0.2426 0.01483 0.00701 -0.0203 0.9919 0.0547
-2.500 -0.2080 0.01395 0.00619 -0.0219 0.9877 0.0735
-2.250 -0.1728 0.01277 0.00562 -0.0241 0.9842 0.1933
-2.000 -0.1472 0.01116 0.00554 -0.0247 0.9795 0.5533
-1.750 -0.1297 0.01057 0.00605 -0.0209 0.9738 0.8690
-1.500 -0.0755 0.01077 0.00621 -0.0249 0.9740 0.9682
-1.250 -0.0018 0.01091 0.00613 -0.0342 0.9780 1.0000
-1.000 0.0400 0.01097 0.00604 -0.0375 0.9726 1.0000
-0.750 0.0792 0.01099 0.00595 -0.0402 0.9662 1.0000
-0.500 0.1224 0.01097 0.00583 -0.0435 0.9597 1.0000
-0.250 0.1687 0.01090 0.00567 -0.0473 0.9535 1.0000
0.000 0.2171 0.01071 0.00543 -0.0514 0.9459 1.0000
0.250 0.2707 0.01045 0.00512 -0.0563 0.9399 1.0000
0.500 0.3128 0.01018 0.00484 -0.0590 0.9314 1.0000
0.750 0.3471 0.00998 0.00463 -0.0601 0.9217 1.0000
1.000 0.3848 0.00971 0.00438 -0.0618 0.9138 1.0000
1.250 0.4134 0.00952 0.00419 -0.0617 0.9022 1.0000
1.500 0.4394 0.00936 0.00404 -0.0610 0.8895 1.0000
1.750 0.4649 0.00921 0.00390 -0.0601 0.8759 1.0000
2.000 0.4896 0.00909 0.00378 -0.0591 0.8614 1.0000
2.250 0.5141 0.00899 0.00370 -0.0580 0.8458 1.0000
2.500 0.5359 0.00896 0.00368 -0.0564 0.8269 1.0000
2.750 0.5587 0.00893 0.00365 -0.0549 0.8068 1.0000
3.000 0.5809 0.00895 0.00365 -0.0533 0.7838 1.0000
3.250 0.6030 0.00898 0.00368 -0.0517 0.7573 1.0000
3.500 0.6242 0.00906 0.00371 -0.0499 0.7243 1.0000
3.750 0.6445 0.00919 0.00372 -0.0479 0.6784 1.0000
4.000 0.6626 0.00947 0.00374 -0.0455 0.6082 1.0000
4.250 0.6784 0.01002 0.00387 -0.0429 0.5187 1.0000
4.500 0.6941 0.01071 0.00418 -0.0405 0.4391 1.0000
4.750 0.7122 0.01136 0.00454 -0.0388 0.3787 1.0000
5.000 0.7320 0.01194 0.00494 -0.0374 0.3341 1.0000
5.250 0.7526 0.01250 0.00535 -0.0362 0.2957 1.0000
5.500 0.7735 0.01305 0.00580 -0.0352 0.2590 1.0000
5.750 0.7947 0.01359 0.00622 -0.0342 0.2185 1.0000
6.000 0.8153 0.01424 0.00669 -0.0331 0.1671 1.0000
6.250 0.8328 0.01536 0.00742 -0.0316 0.1033 1.0000
6.500 0.8500 0.01661 0.00849 -0.0299 0.0731 1.0000
6.750 0.8674 0.01786 0.00966 -0.0283 0.0576 1.0000
7.000 0.8864 0.01904 0.01095 -0.0268 0.0501 1.0000
7.250 0.9031 0.02097 0.01283 -0.0251 0.0443 1.0000
7.500 0.9255 0.02185 0.01388 -0.0241 0.0401 1.0000
7.750 0.9469 0.02317 0.01529 -0.0230 0.0366 1.0000
8.000 0.9679 0.02587 0.01804 -0.0222 0.0336 1.0000
8.250 0.9887 0.02734 0.01980 -0.0210 0.0309 1.0000
8.500 1.0089 0.02937 0.02214 -0.0197 0.0289 1.0000
8.750 1.0270 0.03183 0.02495 -0.0182 0.0274 1.0000
9.000 1.0427 0.03377 0.02709 -0.0168 0.0255 1.0000
9.250 1.0493 0.03852 0.03214 -0.0151 0.0236 1.0000
9.500 1.0526 0.04196 0.03605 -0.0124 0.0231 1.0000
9.750 1.0541 0.04529 0.03980 -0.0096 0.0229 1.0000
10.000 1.0492 0.04937 0.04426 -0.0068 0.0229 1.0000
10.250 1.0386 0.05366 0.04888 -0.0038 0.0230 1.0000
10.500 1.0323 0.05775 0.05317 -0.0015 0.0236 1.0000
10.750 1.0198 0.06044 0.05608 0.0015 0.0238 1.0000
11.000 1.0088 0.06266 0.05851 0.0037 0.0242 1.0000
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Polar data table (+)
Polar graphs
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