S8052 (11.88%) (s8052-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8052 (11.88%) (s8052-il) Reynolds number: 500,000 Max Cl/Cd: 81.56 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8052-il-500000.txt Download as CSV file: xf-s8052-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5209 0.08351 0.08129 -0.0315 1.0000 0.0259
-10.000 -0.5441 0.07115 0.06896 -0.0415 1.0000 0.0262
-9.750 -0.5800 0.06134 0.05904 -0.0497 1.0000 0.0257
-9.500 -0.6080 0.05622 0.05381 -0.0516 1.0000 0.0256
-9.250 -0.6297 0.05286 0.05032 -0.0499 1.0000 0.0258
-9.000 -0.6431 0.04908 0.04633 -0.0485 1.0000 0.0269
-8.750 -0.6495 0.04835 0.04517 -0.0456 1.0000 0.0283
-8.500 -0.6571 0.03949 0.03580 -0.0476 0.9790 0.0293
-8.250 -0.6480 0.02781 0.02287 -0.0471 0.9586 0.0176
-8.000 -0.6259 0.02406 0.01891 -0.0473 0.9427 0.0165
-7.750 -0.6070 0.02180 0.01632 -0.0460 0.9265 0.0160
-7.500 -0.5873 0.02013 0.01439 -0.0447 0.9126 0.0158
-7.250 -0.5662 0.01874 0.01279 -0.0435 0.9006 0.0158
-7.000 -0.5441 0.01762 0.01152 -0.0424 0.8903 0.0160
-6.500 -0.4987 0.01583 0.00947 -0.0405 0.8723 0.0165
-6.250 -0.4755 0.01514 0.00866 -0.0396 0.8650 0.0168
-6.000 -0.4514 0.01453 0.00797 -0.0389 0.8573 0.0172
-5.750 -0.4282 0.01390 0.00724 -0.0381 0.8511 0.0175
-5.500 -0.4059 0.01303 0.00632 -0.0372 0.8442 0.0182
-5.250 -0.3815 0.01255 0.00580 -0.0366 0.8384 0.0194
-5.000 -0.3560 0.01219 0.00539 -0.0362 0.8329 0.0207
-4.750 -0.3303 0.01182 0.00496 -0.0358 0.8270 0.0221
-4.500 -0.3055 0.01132 0.00440 -0.0352 0.8221 0.0250
-4.250 -0.2799 0.01087 0.00395 -0.0347 0.8168 0.0339
-4.000 -0.2568 0.01008 0.00350 -0.0341 0.8114 0.1016
-3.750 -0.2320 0.00962 0.00325 -0.0337 0.8067 0.1587
-3.500 -0.2070 0.00915 0.00304 -0.0334 0.8015 0.2266
-3.250 -0.1827 0.00859 0.00283 -0.0330 0.7963 0.3170
-3.000 -0.1590 0.00803 0.00264 -0.0324 0.7917 0.4196
-2.750 -0.1354 0.00752 0.00253 -0.0318 0.7870 0.5277
-2.500 -0.1103 0.00726 0.00252 -0.0311 0.7819 0.6091
-2.250 -0.0838 0.00719 0.00252 -0.0307 0.7773 0.6534
-2.000 -0.0564 0.00717 0.00251 -0.0304 0.7724 0.6787
-1.750 -0.0287 0.00715 0.00249 -0.0301 0.7668 0.6979
-1.500 -0.0011 0.00714 0.00246 -0.0299 0.7619 0.7142
-1.250 0.0267 0.00715 0.00246 -0.0297 0.7568 0.7288
-1.000 0.0545 0.00714 0.00244 -0.0295 0.7508 0.7417
-0.750 0.0821 0.00714 0.00241 -0.0292 0.7453 0.7529
-0.500 0.1098 0.00712 0.00241 -0.0290 0.7387 0.7639
-0.250 0.1376 0.00712 0.00237 -0.0288 0.7319 0.7749
0.000 0.1652 0.00710 0.00236 -0.0285 0.7249 0.7847
0.250 0.1928 0.00708 0.00234 -0.0283 0.7176 0.7941
0.500 0.2206 0.00708 0.00232 -0.0281 0.7102 0.8039
0.750 0.2480 0.00705 0.00230 -0.0278 0.7022 0.8125
1.000 0.2756 0.00704 0.00229 -0.0276 0.6942 0.8219
1.250 0.3029 0.00702 0.00227 -0.0273 0.6852 0.8313
1.500 0.3301 0.00698 0.00227 -0.0270 0.6747 0.8406
1.750 0.3573 0.00699 0.00227 -0.0267 0.6652 0.8510
2.000 0.3841 0.00697 0.00227 -0.0263 0.6548 0.8610
2.250 0.4109 0.00694 0.00228 -0.0259 0.6422 0.8710
2.500 0.4378 0.00694 0.00229 -0.0255 0.6289 0.8816
2.750 0.4641 0.00694 0.00231 -0.0251 0.6138 0.8918
3.000 0.4899 0.00697 0.00232 -0.0245 0.5950 0.9029
3.250 0.5155 0.00703 0.00235 -0.0238 0.5724 0.9154
3.500 0.5410 0.00714 0.00241 -0.0232 0.5490 0.9294
3.750 0.5685 0.00730 0.00251 -0.0231 0.5206 0.9442
4.000 0.5996 0.00755 0.00263 -0.0239 0.4853 0.9582
4.250 0.6330 0.00789 0.00280 -0.0253 0.4433 0.9710
4.500 0.6679 0.00828 0.00302 -0.0271 0.4001 0.9825
4.750 0.7049 0.00867 0.00324 -0.0295 0.3594 0.9911
5.000 0.7422 0.00910 0.00349 -0.0320 0.3197 0.9992
5.250 0.7620 0.00947 0.00371 -0.0308 0.2906 1.0000
5.750 0.8030 0.01019 0.00420 -0.0285 0.2428 1.0000
6.000 0.8247 0.01058 0.00448 -0.0276 0.2224 1.0000
6.250 0.8472 0.01093 0.00476 -0.0268 0.2050 1.0000
6.500 0.8700 0.01129 0.00505 -0.0261 0.1896 1.0000
6.750 0.8929 0.01165 0.00535 -0.0254 0.1759 1.0000
7.250 0.9390 0.01235 0.00598 -0.0240 0.1526 1.0000
7.500 0.9621 0.01270 0.00631 -0.0234 0.1421 1.0000
7.750 0.9846 0.01309 0.00667 -0.0227 0.1324 1.0000
8.000 1.0066 0.01351 0.00706 -0.0219 0.1223 1.0000
8.250 1.0293 0.01387 0.00743 -0.0212 0.1131 1.0000
8.500 1.0510 0.01430 0.00784 -0.0204 0.1038 1.0000
8.750 1.0716 0.01480 0.00830 -0.0195 0.0940 1.0000
9.000 1.0925 0.01526 0.00875 -0.0186 0.0857 1.0000
9.250 1.1125 0.01578 0.00927 -0.0176 0.0786 1.0000
9.500 1.1301 0.01642 0.00987 -0.0162 0.0715 1.0000
9.750 1.1493 0.01693 0.01044 -0.0151 0.0667 1.0000
10.000 1.1658 0.01759 0.01107 -0.0136 0.0615 1.0000
10.250 1.1805 0.01826 0.01178 -0.0119 0.0576 1.0000
10.500 1.1963 0.01876 0.01233 -0.0102 0.0542 1.0000
10.750 1.2084 0.01945 0.01303 -0.0081 0.0511 1.0000
11.000 1.2155 0.02046 0.01407 -0.0056 0.0482 1.0000
11.250 1.2314 0.02100 0.01469 -0.0042 0.0466 1.0000
11.500 1.2444 0.02174 0.01550 -0.0027 0.0448 1.0000
11.750 1.2571 0.02252 0.01633 -0.0012 0.0427 1.0000
12.000 1.2646 0.02369 0.01751 0.0006 0.0404 1.0000
12.250 1.2715 0.02495 0.01885 0.0023 0.0389 1.0000
12.500 1.2850 0.02580 0.01978 0.0034 0.0379 1.0000
12.750 1.2968 0.02679 0.02086 0.0044 0.0366 1.0000
13.000 1.3070 0.02792 0.02207 0.0055 0.0355 1.0000
13.250 1.3165 0.02915 0.02336 0.0065 0.0344 1.0000
13.500 1.3235 0.03061 0.02485 0.0075 0.0330 1.0000
13.750 1.3238 0.03269 0.02702 0.0087 0.0317 1.0000
14.000 1.3307 0.03429 0.02871 0.0095 0.0308 1.0000
14.250 1.3406 0.03565 0.03018 0.0100 0.0300 1.0000
14.500 1.3482 0.03727 0.03190 0.0105 0.0291 1.0000
14.750 1.3560 0.03890 0.03363 0.0108 0.0281 1.0000
15.000 1.3626 0.04069 0.03547 0.0110 0.0269 1.0000
15.250 1.3643 0.04304 0.03788 0.0111 0.0259 1.0000
15.500 1.3589 0.04621 0.04114 0.0111 0.0249 1.0000
15.750 1.3655 0.04824 0.04329 0.0109 0.0238 1.0000
16.000 1.3694 0.05064 0.04580 0.0105 0.0229 1.0000
16.250 1.3749 0.05295 0.04822 0.0100 0.0216 1.0000
16.500 1.3739 0.05619 0.05151 0.0090 0.0201 1.0000
16.750 1.3686 0.06013 0.05555 0.0078 0.0188 1.0000
17.000 1.3690 0.06346 0.05901 0.0066 0.0175 1.0000
17.250 1.3645 0.06762 0.06324 0.0049 0.0157 1.0000
17.500 1.3488 0.07370 0.06942 0.0021 0.0147 1.0000
17.750 1.3377 0.07925 0.07513 -0.0005 0.0142 1.0000
18.000 1.3230 0.08559 0.08162 -0.0036 0.0135 1.0000
18.250 1.3071 0.09236 0.08852 -0.0071 0.0130 1.0000
18.500 1.2883 0.09987 0.09616 -0.0111 0.0125 1.0000
18.750 1.2684 0.10774 0.10417 -0.0154 0.0125 1.0000
19.000 1.2474 0.11602 0.11258 -0.0200 0.0122 1.0000
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Polar data table (+)
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