S8052 (11.88%) (s8052-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8052 (11.88%) (s8052-il) Reynolds number: 500,000 Max Cl/Cd: 73.47 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8052-il-500000-n5.txt Download as CSV file: xf-s8052-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8052 (11.88%)
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6647 0.08878 0.08633 -0.0240 1.0000 0.0079
-12.500 -0.6467 0.08897 0.08657 -0.0241 1.0000 0.0081
-12.250 -0.7861 0.05182 0.04862 -0.0502 1.0000 0.0074
-11.750 -0.8137 0.04316 0.03961 -0.0543 1.0000 0.0075
-11.500 -0.8297 0.03952 0.03575 -0.0543 1.0000 0.0075
-11.250 -0.8407 0.03680 0.03285 -0.0529 1.0000 0.0075
-11.000 -0.8512 0.03442 0.03027 -0.0502 1.0000 0.0075
-10.750 -0.8579 0.03199 0.02762 -0.0473 1.0000 0.0076
-10.500 -0.8530 0.03008 0.02552 -0.0454 1.0000 0.0076
-10.250 -0.8458 0.02817 0.02340 -0.0436 1.0000 0.0077
-10.000 -0.8316 0.02650 0.02153 -0.0427 0.9887 0.0077
-9.750 -0.8037 0.02464 0.01947 -0.0446 0.9598 0.0079
-9.500 -0.7773 0.02318 0.01782 -0.0456 0.9376 0.0080
-9.250 -0.7570 0.02206 0.01651 -0.0449 0.9158 0.0081
-9.000 -0.7383 0.02108 0.01536 -0.0437 0.8980 0.0082
-8.750 -0.7190 0.02020 0.01430 -0.0426 0.8838 0.0084
-8.500 -0.6988 0.01934 0.01330 -0.0416 0.8719 0.0085
-8.250 -0.6779 0.01855 0.01237 -0.0406 0.8615 0.0087
-7.750 -0.6343 0.01710 0.01067 -0.0389 0.8427 0.0091
-7.500 -0.6118 0.01645 0.00991 -0.0381 0.8348 0.0092
-7.250 -0.5886 0.01583 0.00918 -0.0375 0.8273 0.0095
-7.000 -0.5652 0.01527 0.00852 -0.0368 0.8204 0.0097
-6.750 -0.5412 0.01473 0.00790 -0.0362 0.8134 0.0099
-6.500 -0.5170 0.01425 0.00733 -0.0357 0.8070 0.0101
-6.250 -0.4927 0.01373 0.00673 -0.0351 0.8010 0.0103
-6.000 -0.4684 0.01320 0.00614 -0.0346 0.7950 0.0107
-5.750 -0.4432 0.01282 0.00570 -0.0342 0.7899 0.0112
-5.500 -0.4173 0.01246 0.00531 -0.0339 0.7846 0.0119
-5.250 -0.3913 0.01215 0.00493 -0.0336 0.7795 0.0127
-4.750 -0.3389 0.01152 0.00420 -0.0330 0.7704 0.0144
-4.500 -0.3124 0.01123 0.00388 -0.0327 0.7656 0.0163
-4.250 -0.2860 0.01096 0.00358 -0.0324 0.7613 0.0203
-4.000 -0.2596 0.01064 0.00331 -0.0322 0.7569 0.0328
-3.750 -0.2333 0.01031 0.00307 -0.0320 0.7521 0.0535
-3.500 -0.2071 0.00999 0.00284 -0.0317 0.7474 0.0822
-3.250 -0.1815 0.00959 0.00262 -0.0315 0.7431 0.1291
-3.000 -0.1557 0.00916 0.00244 -0.0313 0.7382 0.1878
-2.750 -0.1301 0.00875 0.00226 -0.0311 0.7336 0.2549
-2.500 -0.1049 0.00831 0.00209 -0.0308 0.7295 0.3359
-2.250 -0.0796 0.00785 0.00195 -0.0305 0.7247 0.4216
-2.000 -0.0539 0.00750 0.00184 -0.0302 0.7194 0.4931
-1.750 -0.0280 0.00726 0.00178 -0.0298 0.7145 0.5589
-1.500 -0.0009 0.00712 0.00176 -0.0296 0.7092 0.6029
-1.250 0.0266 0.00705 0.00174 -0.0294 0.7036 0.6324
-1.000 0.0543 0.00702 0.00172 -0.0292 0.6981 0.6540
-0.750 0.0823 0.00698 0.00170 -0.0291 0.6912 0.6716
-0.500 0.1101 0.00697 0.00168 -0.0289 0.6842 0.6871
-0.250 0.1381 0.00695 0.00167 -0.0289 0.6759 0.7008
0.000 0.1661 0.00696 0.00165 -0.0287 0.6675 0.7130
0.250 0.1940 0.00695 0.00165 -0.0286 0.6578 0.7241
0.500 0.2219 0.00695 0.00165 -0.0285 0.6473 0.7340
0.750 0.2498 0.00697 0.00164 -0.0284 0.6358 0.7439
1.000 0.2775 0.00698 0.00165 -0.0283 0.6226 0.7534
1.250 0.3050 0.00701 0.00165 -0.0281 0.6046 0.7626
1.500 0.3320 0.00708 0.00166 -0.0278 0.5824 0.7726
1.750 0.3588 0.00717 0.00170 -0.0275 0.5612 0.7821
2.000 0.3855 0.00728 0.00175 -0.0273 0.5391 0.7917
2.250 0.4118 0.00742 0.00182 -0.0269 0.5131 0.8008
2.500 0.4381 0.00758 0.00190 -0.0266 0.4878 0.8086
2.750 0.4643 0.00775 0.00201 -0.0263 0.4619 0.8166
3.000 0.4900 0.00796 0.00213 -0.0260 0.4328 0.8246
3.250 0.5156 0.00820 0.00226 -0.0256 0.4023 0.8333
3.500 0.5410 0.00841 0.00242 -0.0252 0.3759 0.8420
3.750 0.5662 0.00865 0.00258 -0.0247 0.3486 0.8520
4.000 0.5908 0.00892 0.00275 -0.0242 0.3194 0.8631
4.250 0.6149 0.00920 0.00295 -0.0236 0.2901 0.8748
4.500 0.6389 0.00948 0.00316 -0.0229 0.2637 0.8887
4.750 0.6632 0.00971 0.00336 -0.0223 0.2430 0.9055
5.000 0.6888 0.00994 0.00357 -0.0219 0.2262 0.9251
5.250 0.7186 0.01023 0.00382 -0.0225 0.2078 0.9454
5.500 0.7530 0.01054 0.00407 -0.0242 0.1913 0.9660
5.750 0.7872 0.01085 0.00433 -0.0259 0.1764 0.9878
6.000 0.8172 0.01118 0.00460 -0.0267 0.1623 1.0000
6.250 0.8405 0.01148 0.00485 -0.0261 0.1508 1.0000
6.500 0.8641 0.01177 0.00511 -0.0255 0.1406 1.0000
6.750 0.8875 0.01208 0.00539 -0.0248 0.1311 1.0000
7.000 0.9107 0.01242 0.00569 -0.0242 0.1223 1.0000
7.250 0.9343 0.01272 0.00599 -0.0236 0.1139 1.0000
7.500 0.9573 0.01308 0.00631 -0.0230 0.1051 1.0000
7.750 0.9801 0.01344 0.00665 -0.0223 0.0967 1.0000
8.000 1.0030 0.01379 0.00701 -0.0217 0.0895 1.0000
8.250 1.0249 0.01421 0.00739 -0.0209 0.0819 1.0000
8.500 1.0471 0.01460 0.00778 -0.0202 0.0754 1.0000
8.750 1.0682 0.01506 0.00822 -0.0194 0.0689 1.0000
9.000 1.0894 0.01549 0.00866 -0.0185 0.0634 1.0000
9.250 1.1096 0.01598 0.00915 -0.0175 0.0586 1.0000
9.500 1.1303 0.01640 0.00961 -0.0166 0.0551 1.0000
9.750 1.1495 0.01691 0.01012 -0.0155 0.0511 1.0000
10.000 1.1679 0.01744 0.01067 -0.0143 0.0476 1.0000
10.250 1.1863 0.01793 0.01121 -0.0131 0.0446 1.0000
10.500 1.2014 0.01851 0.01179 -0.0114 0.0413 1.0000
10.750 1.2151 0.01911 0.01241 -0.0095 0.0388 1.0000
11.000 1.2298 0.01966 0.01302 -0.0078 0.0370 1.0000
11.250 1.2436 0.02029 0.01369 -0.0062 0.0351 1.0000
11.500 1.2564 0.02101 0.01445 -0.0045 0.0334 1.0000
11.750 1.2675 0.02187 0.01535 -0.0028 0.0315 1.0000
12.000 1.2810 0.02261 0.01616 -0.0014 0.0303 1.0000
12.250 1.2938 0.02341 0.01703 -0.0001 0.0291 1.0000
12.500 1.3057 0.02430 0.01798 0.0012 0.0278 1.0000
12.750 1.3166 0.02531 0.01904 0.0024 0.0266 1.0000
13.000 1.3261 0.02645 0.02023 0.0037 0.0255 1.0000
13.250 1.3346 0.02771 0.02155 0.0049 0.0245 1.0000
13.500 1.3455 0.02881 0.02276 0.0058 0.0237 1.0000
13.750 1.3549 0.03006 0.02410 0.0067 0.0228 1.0000
14.000 1.3639 0.03139 0.02550 0.0076 0.0216 1.0000
14.250 1.3712 0.03291 0.02707 0.0083 0.0205 1.0000
14.500 1.3770 0.03460 0.02883 0.0091 0.0197 1.0000
14.750 1.3823 0.03638 0.03070 0.0096 0.0188 1.0000
15.000 1.3886 0.03813 0.03254 0.0101 0.0178 1.0000
15.250 1.3928 0.04012 0.03463 0.0104 0.0168 1.0000
15.500 1.3954 0.04235 0.03693 0.0106 0.0157 1.0000
15.750 1.3962 0.04486 0.03951 0.0107 0.0143 1.0000
16.000 1.3967 0.04747 0.04225 0.0105 0.0135 1.0000
16.250 1.3951 0.05046 0.04532 0.0101 0.0121 1.0000
16.500 1.3908 0.05395 0.04889 0.0094 0.0109 1.0000
16.750 1.3852 0.05778 0.05283 0.0083 0.0094 1.0000
17.000 1.3784 0.06199 0.05715 0.0069 0.0088 1.0000
17.250 1.3683 0.06687 0.06214 0.0049 0.0080 1.0000
17.500 1.3565 0.07225 0.06764 0.0026 0.0073 1.0000
17.750 1.3454 0.07776 0.07330 0.0000 0.0072 1.0000
18.000 1.3303 0.08412 0.07980 -0.0031 0.0070 1.0000
18.250 1.3134 0.09102 0.08684 -0.0067 0.0068 1.0000
18.500 1.2924 0.09890 0.09487 -0.0109 0.0065 1.0000
18.750 1.2738 0.10654 0.10267 -0.0150 0.0066 1.0000
19.000 1.2517 0.11505 0.11133 -0.0198 0.0065 1.0000
19.250 1.2294 0.12375 0.12018 -0.0247 0.0065 1.0000
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Polar data table (+)
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