S5020 (s5020-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S5020 (s5020-il) Reynolds number: 50,000 Max Cl/Cd: 25.26 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s5020-il-50000.txt Download as CSV file: xf-s5020-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S5020
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5295 0.11603 0.11008 0.0240 1.0000 0.1725
-8.500 -0.5117 0.11073 0.10480 0.0249 1.0000 0.1825
-8.250 -0.5277 0.10972 0.10394 0.0202 1.0000 0.1875
-8.000 -0.5122 0.10498 0.09922 0.0211 1.0000 0.2009
-7.750 -0.5019 0.10094 0.09524 0.0211 1.0000 0.2141
-7.500 -0.4944 0.09726 0.09162 0.0207 1.0000 0.2274
-7.250 -0.4887 0.09382 0.08826 0.0201 1.0000 0.2412
-7.000 -0.4846 0.09055 0.08509 0.0194 1.0000 0.2562
-6.750 -0.4850 0.08769 0.08233 0.0179 1.0000 0.2728
-6.500 -0.4756 0.08391 0.07861 0.0182 1.0000 0.2923
-6.250 -0.4753 0.08143 0.07621 0.0167 1.0000 0.3177
-6.000 -0.4683 0.07837 0.07323 0.0173 1.0000 0.3472
-5.750 -0.4409 0.07404 0.06896 0.0229 1.0000 0.3851
-5.500 -0.4292 0.07115 0.06614 0.0260 1.0000 0.4313
-5.250 -0.4173 0.06860 0.06368 0.0309 1.0000 0.4919
-5.000 -0.3568 0.06404 0.05899 0.0400 1.0000 0.6225
-4.250 -0.2129 0.04972 0.04457 0.0358 1.0000 0.8296
-4.000 -0.2727 0.05028 0.04547 0.0373 1.0000 0.7276
-3.750 -0.3260 0.04965 0.04521 0.0363 1.0000 0.6560
-3.500 -0.3327 0.04138 0.03502 -0.0146 1.0000 0.2333
-3.250 -0.3056 0.03787 0.03064 -0.0159 1.0000 0.1763
-3.000 -0.2852 0.03555 0.02776 -0.0153 1.0000 0.1543
-2.750 -0.2649 0.03355 0.02522 -0.0145 1.0000 0.1405
-2.500 -0.2431 0.03216 0.02307 -0.0134 1.0000 0.1299
-2.250 -0.1966 0.02964 0.02027 -0.0172 0.9888 0.1250
-2.000 -0.1457 0.02785 0.01802 -0.0212 0.9761 0.1246
-1.750 -0.0936 0.02664 0.01631 -0.0253 0.9631 0.1299
-1.500 -0.0373 0.02511 0.01474 -0.0299 0.9511 0.1376
-1.250 0.0178 0.02402 0.01355 -0.0344 0.9386 0.1566
-1.000 0.1351 0.01947 0.01136 -0.0483 0.9328 1.0000
-0.750 0.1857 0.01990 0.01129 -0.0528 0.9167 1.0000
-0.500 0.2283 0.02038 0.01142 -0.0557 0.9006 1.0000
-0.250 0.2589 0.02097 0.01177 -0.0564 0.8838 1.0000
0.000 0.2854 0.02161 0.01222 -0.0563 0.8670 1.0000
0.250 0.3109 0.02227 0.01270 -0.0560 0.8508 1.0000
0.500 0.3349 0.02293 0.01321 -0.0553 0.8348 1.0000
0.750 0.3578 0.02361 0.01376 -0.0543 0.8192 1.0000
1.000 0.3800 0.02429 0.01433 -0.0531 0.8038 1.0000
1.250 0.4015 0.02497 0.01492 -0.0518 0.7886 1.0000
1.500 0.4227 0.02565 0.01551 -0.0503 0.7735 1.0000
1.750 0.4437 0.02632 0.01612 -0.0488 0.7586 1.0000
2.000 0.4646 0.02699 0.01672 -0.0472 0.7437 1.0000
2.250 0.4842 0.02778 0.01748 -0.0458 0.7275 1.0000
2.500 0.5042 0.02854 0.01824 -0.0445 0.7116 1.0000
2.750 0.5244 0.02929 0.01897 -0.0430 0.6957 1.0000
3.000 0.5449 0.03002 0.01969 -0.0415 0.6798 1.0000
3.250 0.5657 0.03072 0.02039 -0.0400 0.6641 1.0000
3.500 0.5866 0.03136 0.02108 -0.0383 0.6483 1.0000
3.750 0.6079 0.03197 0.02171 -0.0366 0.6327 1.0000
4.000 0.6294 0.03250 0.02226 -0.0348 0.6172 1.0000
4.250 0.6512 0.03297 0.02275 -0.0328 0.6017 1.0000
4.500 0.6733 0.03336 0.02318 -0.0308 0.5864 1.0000
4.750 0.6933 0.03424 0.02417 -0.0296 0.5686 1.0000
5.000 0.7136 0.03502 0.02505 -0.0283 0.5509 1.0000
5.250 0.7355 0.03546 0.02555 -0.0265 0.5343 1.0000
5.500 0.7581 0.03576 0.02592 -0.0245 0.5181 1.0000
5.750 0.7817 0.03583 0.02609 -0.0222 0.5021 1.0000
6.000 0.8058 0.03579 0.02611 -0.0199 0.4864 1.0000
6.250 0.8244 0.03701 0.02748 -0.0191 0.4666 1.0000
6.500 0.8465 0.03744 0.02801 -0.0174 0.4489 1.0000
6.750 0.8715 0.03723 0.02786 -0.0150 0.4318 1.0000
7.000 0.8978 0.03683 0.02752 -0.0125 0.4153 1.0000
7.250 0.9146 0.03844 0.02934 -0.0119 0.3949 1.0000
7.500 0.9382 0.03865 0.02964 -0.0100 0.3766 1.0000
7.750 0.9656 0.03823 0.02917 -0.0076 0.3589 1.0000
8.000 0.9814 0.04005 0.03128 -0.0070 0.3395 1.0000
8.250 1.0022 0.04095 0.03230 -0.0055 0.3209 1.0000
8.500 1.0298 0.04077 0.03203 -0.0034 0.3025 1.0000
8.750 1.0440 0.04290 0.03441 -0.0027 0.2851 1.0000
9.000 1.0574 0.04513 0.03687 -0.0019 0.2688 1.0000
9.250 1.0720 0.04702 0.03896 -0.0008 0.2525 1.0000
9.500 1.0819 0.04986 0.04203 -0.0001 0.2396 1.0000
9.750 1.0912 0.05246 0.04481 0.0007 0.2265 1.0000
10.000 1.1003 0.05499 0.04749 0.0017 0.2140 1.0000
10.250 1.0257 0.06775 0.06055 -0.0035 0.2228 1.0000
10.500 1.0047 0.07392 0.06671 -0.0054 0.2194 1.0000
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Polar data table (+)
Polar graphs
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