S8055 (12%) (s8055-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8055 (12%) (s8055-il) Reynolds number: 500,000 Max Cl/Cd: 74.88 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8055-il-500000-n5.txt Download as CSV file: xf-s8055-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8055 (12%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6736 0.05735 0.05469 -0.0583 1.0000 0.0062
-11.750 -0.7201 0.04592 0.04291 -0.0673 1.0000 0.0060
-11.500 -0.7454 0.04078 0.03754 -0.0689 1.0000 0.0060
-11.250 -0.7565 0.03735 0.03390 -0.0693 0.9804 0.0061
-11.000 -0.7496 0.03408 0.03032 -0.0716 0.9477 0.0062
-10.750 -0.7548 0.03183 0.02776 -0.0689 0.9244 0.0062
-10.500 -0.7570 0.02959 0.02519 -0.0661 0.9108 0.0061
-10.250 -0.7499 0.02799 0.02336 -0.0640 0.9015 0.0062
-10.000 -0.7388 0.02663 0.02180 -0.0623 0.8945 0.0064
-9.750 -0.7268 0.02509 0.02001 -0.0607 0.8877 0.0064
-9.250 -0.6951 0.02252 0.01702 -0.0580 0.8777 0.0066
-9.000 -0.6769 0.02140 0.01571 -0.0569 0.8729 0.0068
-8.750 -0.6576 0.02037 0.01450 -0.0558 0.8688 0.0070
-8.500 -0.6371 0.01944 0.01342 -0.0549 0.8652 0.0072
-8.250 -0.6158 0.01855 0.01239 -0.0541 0.8613 0.0073
-8.000 -0.5938 0.01777 0.01147 -0.0534 0.8576 0.0075
-7.750 -0.5713 0.01707 0.01065 -0.0526 0.8542 0.0076
-7.250 -0.5255 0.01572 0.00911 -0.0512 0.8478 0.0079
-7.000 -0.5026 0.01502 0.00835 -0.0506 0.8444 0.0081
-6.750 -0.4786 0.01449 0.00777 -0.0501 0.8411 0.0084
-6.500 -0.4540 0.01407 0.00729 -0.0496 0.8382 0.0088
-6.000 -0.4038 0.01326 0.00636 -0.0488 0.8321 0.0098
-5.750 -0.3782 0.01288 0.00593 -0.0484 0.8287 0.0103
-5.500 -0.3533 0.01241 0.00542 -0.0479 0.8253 0.0108
-5.250 -0.3276 0.01207 0.00503 -0.0475 0.8222 0.0115
-5.000 -0.3017 0.01177 0.00467 -0.0472 0.8194 0.0125
-4.750 -0.2755 0.01144 0.00432 -0.0469 0.8161 0.0141
-4.500 -0.2490 0.01116 0.00403 -0.0467 0.8126 0.0165
-4.250 -0.2229 0.01085 0.00373 -0.0464 0.8092 0.0223
-4.000 -0.1967 0.01057 0.00348 -0.0461 0.8060 0.0329
-3.750 -0.1707 0.01026 0.00324 -0.0458 0.8027 0.0523
-3.500 -0.1444 0.00996 0.00304 -0.0456 0.7987 0.0751
-3.250 -0.1186 0.00962 0.00285 -0.0453 0.7946 0.1116
-3.000 -0.0936 0.00919 0.00265 -0.0450 0.7909 0.1714
-2.750 -0.0682 0.00883 0.00248 -0.0446 0.7874 0.2310
-2.500 -0.0423 0.00849 0.00236 -0.0444 0.7831 0.2873
-2.250 -0.0167 0.00815 0.00223 -0.0441 0.7788 0.3509
-2.000 0.0086 0.00781 0.00210 -0.0437 0.7746 0.4202
-1.750 0.0337 0.00747 0.00199 -0.0433 0.7699 0.4933
-1.500 0.0584 0.00713 0.00192 -0.0427 0.7639 0.5694
-1.250 0.0834 0.00689 0.00188 -0.0420 0.7583 0.6372
-1.000 0.1097 0.00675 0.00188 -0.0416 0.7524 0.6837
-0.750 0.1365 0.00668 0.00187 -0.0412 0.7455 0.7153
-0.500 0.1637 0.00664 0.00184 -0.0409 0.7377 0.7384
-0.250 0.1909 0.00661 0.00182 -0.0406 0.7280 0.7556
0.000 0.2183 0.00660 0.00180 -0.0403 0.7176 0.7709
0.250 0.2456 0.00659 0.00178 -0.0401 0.7057 0.7847
0.500 0.2726 0.00660 0.00176 -0.0397 0.6913 0.7959
0.750 0.2994 0.00662 0.00174 -0.0394 0.6755 0.8067
1.000 0.3262 0.00668 0.00174 -0.0391 0.6583 0.8171
1.250 0.3522 0.00676 0.00175 -0.0386 0.6370 0.8266
1.500 0.3780 0.00686 0.00178 -0.0380 0.6133 0.8364
1.750 0.4033 0.00701 0.00183 -0.0375 0.5888 0.8462
2.000 0.4286 0.00714 0.00190 -0.0369 0.5644 0.8553
2.250 0.4537 0.00729 0.00198 -0.0363 0.5417 0.8655
2.500 0.4785 0.00745 0.00208 -0.0356 0.5175 0.8759
2.750 0.5029 0.00764 0.00218 -0.0349 0.4907 0.8850
3.000 0.5270 0.00786 0.00230 -0.0343 0.4625 0.8938
3.250 0.5515 0.00806 0.00243 -0.0336 0.4367 0.9019
3.500 0.5756 0.00830 0.00258 -0.0330 0.4084 0.9113
3.750 0.5997 0.00857 0.00274 -0.0323 0.3784 0.9212
4.000 0.6249 0.00885 0.00292 -0.0319 0.3509 0.9317
4.250 0.6514 0.00917 0.00313 -0.0319 0.3208 0.9431
4.500 0.6807 0.00954 0.00336 -0.0326 0.2898 0.9538
4.750 0.7119 0.00990 0.00361 -0.0336 0.2639 0.9637
5.000 0.7434 0.01022 0.00384 -0.0348 0.2417 0.9738
5.250 0.7748 0.01053 0.00408 -0.0359 0.2245 0.9839
5.500 0.8068 0.01087 0.00435 -0.0372 0.2071 0.9922
5.750 0.8390 0.01121 0.00461 -0.0385 0.1912 0.9995
6.000 0.8596 0.01148 0.00484 -0.0373 0.1792 1.0000
6.250 0.8794 0.01177 0.00508 -0.0360 0.1676 1.0000
6.500 0.8996 0.01208 0.00534 -0.0347 0.1567 1.0000
6.750 0.9198 0.01241 0.00562 -0.0335 0.1459 1.0000
7.000 0.9411 0.01269 0.00589 -0.0325 0.1371 1.0000
7.250 0.9619 0.01302 0.00619 -0.0314 0.1285 1.0000
7.500 0.9824 0.01337 0.00651 -0.0303 0.1198 1.0000
7.750 1.0034 0.01368 0.00682 -0.0293 0.1125 1.0000
8.000 1.0233 0.01406 0.00717 -0.0281 0.1048 1.0000
8.250 1.0437 0.01440 0.00752 -0.0270 0.0972 1.0000
8.500 1.0628 0.01481 0.00790 -0.0258 0.0896 1.0000
8.750 1.0811 0.01523 0.00830 -0.0244 0.0824 1.0000
9.000 1.0982 0.01564 0.00871 -0.0227 0.0767 1.0000
9.250 1.1143 0.01608 0.00915 -0.0210 0.0715 1.0000
9.500 1.1306 0.01654 0.00963 -0.0193 0.0671 1.0000
9.750 1.1470 0.01701 0.01012 -0.0177 0.0629 1.0000
10.000 1.1620 0.01758 0.01069 -0.0160 0.0585 1.0000
10.250 1.1784 0.01808 0.01123 -0.0146 0.0551 1.0000
10.500 1.1939 0.01866 0.01183 -0.0131 0.0518 1.0000
10.750 1.2080 0.01934 0.01252 -0.0115 0.0485 1.0000
11.000 1.2237 0.01992 0.01316 -0.0101 0.0465 1.0000
11.250 1.2382 0.02059 0.01387 -0.0087 0.0435 1.0000
11.500 1.2513 0.02137 0.01467 -0.0072 0.0412 1.0000
11.750 1.2650 0.02212 0.01548 -0.0058 0.0393 1.0000
12.000 1.2790 0.02287 0.01628 -0.0045 0.0373 1.0000
12.250 1.2917 0.02372 0.01717 -0.0032 0.0355 1.0000
12.500 1.3031 0.02467 0.01816 -0.0018 0.0341 1.0000
12.750 1.3138 0.02570 0.01925 -0.0004 0.0326 1.0000
13.000 1.3265 0.02660 0.02023 0.0007 0.0314 1.0000
13.250 1.3378 0.02762 0.02132 0.0019 0.0300 1.0000
13.500 1.3480 0.02875 0.02250 0.0030 0.0287 1.0000
13.750 1.3563 0.03005 0.02385 0.0042 0.0274 1.0000
14.000 1.3644 0.03139 0.02526 0.0053 0.0264 1.0000
14.250 1.3740 0.03265 0.02662 0.0062 0.0256 1.0000
14.500 1.3820 0.03407 0.02814 0.0071 0.0247 1.0000
14.750 1.3892 0.03559 0.02974 0.0080 0.0234 1.0000
15.000 1.3946 0.03734 0.03156 0.0087 0.0226 1.0000
15.250 1.3986 0.03926 0.03355 0.0094 0.0215 1.0000
15.500 1.4041 0.04110 0.03550 0.0099 0.0206 1.0000
15.750 1.4082 0.04314 0.03762 0.0102 0.0192 1.0000
16.000 1.4104 0.04550 0.04007 0.0104 0.0183 1.0000
16.250 1.4108 0.04814 0.04279 0.0104 0.0172 1.0000
16.500 1.4119 0.05081 0.04558 0.0102 0.0162 1.0000
16.750 1.4108 0.05387 0.04874 0.0098 0.0149 1.0000
17.000 1.4070 0.05740 0.05235 0.0090 0.0135 1.0000
17.250 1.4033 0.06106 0.05614 0.0080 0.0129 1.0000
17.500 1.3968 0.06527 0.06045 0.0067 0.0119 1.0000
17.750 1.3886 0.06988 0.06518 0.0050 0.0113 1.0000
18.000 1.3771 0.07519 0.07061 0.0028 0.0104 1.0000
18.250 1.3646 0.08084 0.07640 0.0003 0.0098 1.0000
18.500 1.3491 0.08721 0.08291 -0.0027 0.0093 1.0000
18.750 1.3331 0.09385 0.08969 -0.0060 0.0091 1.0000
19.000 1.3143 0.10118 0.09716 -0.0097 0.0089 1.0000
19.250 1.2966 0.10853 0.10466 -0.0136 0.0089 1.0000
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Polar data table (+)
Polar graphs
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