S8035 for RC aerobatic 14% thick (s8035-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8035 for RC aerobatic 14% thick (s8035-il) Reynolds number: 500,000 Max Cl/Cd: 66.88 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8035-il-500000-n5.txt Download as CSV file: xf-s8035-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8035 for RC aerobatic 14% thick
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
------ -------- --------- --------- -------- -------- --------
-18.750 -1.0837 0.10471 0.10062 -0.0193 1.0000 0.0157
-18.500 -1.0997 0.09836 0.09418 -0.0224 1.0000 0.0159
-18.250 -1.1177 0.09181 0.08752 -0.0256 1.0000 0.0160
-18.000 -1.1331 0.08583 0.08143 -0.0284 1.0000 0.0161
-17.750 -1.1487 0.07990 0.07540 -0.0312 1.0000 0.0163
-17.500 -1.1634 0.07427 0.06965 -0.0338 1.0000 0.0165
-17.250 -1.1770 0.06891 0.06418 -0.0361 1.0000 0.0166
-17.000 -1.1873 0.06415 0.05932 -0.0382 1.0000 0.0170
-16.750 -1.1985 0.05940 0.05445 -0.0401 1.0000 0.0171
-16.500 -1.2050 0.05541 0.05036 -0.0417 1.0000 0.0175
-16.250 -1.2114 0.05157 0.04641 -0.0430 1.0000 0.0178
-16.000 -1.2173 0.04790 0.04262 -0.0441 1.0000 0.0181
-15.750 -1.2197 0.04479 0.03940 -0.0449 1.0000 0.0184
-15.500 -1.2211 0.04190 0.03640 -0.0455 1.0000 0.0187
-15.250 -1.2225 0.03911 0.03353 -0.0459 1.0000 0.0192
-15.000 -1.2243 0.03644 0.03077 -0.0460 1.0000 0.0196
-14.750 -1.2236 0.03414 0.02839 -0.0458 1.0000 0.0202
-14.500 -1.2210 0.03215 0.02633 -0.0453 1.0000 0.0210
-14.250 -1.2176 0.03035 0.02444 -0.0446 1.0000 0.0214
-14.000 -1.2118 0.02885 0.02286 -0.0437 1.0000 0.0222
-13.750 -1.2055 0.02748 0.02141 -0.0426 1.0000 0.0229
-13.500 -1.2001 0.02615 0.02001 -0.0412 1.0000 0.0237
-13.250 -1.1947 0.02490 0.01872 -0.0395 1.0000 0.0247
-13.000 -1.1876 0.02385 0.01763 -0.0377 1.0000 0.0259
-12.750 -1.1793 0.02295 0.01666 -0.0358 1.0000 0.0270
-12.500 -1.1701 0.02216 0.01580 -0.0337 1.0000 0.0281
-12.250 -1.1622 0.02137 0.01497 -0.0313 1.0000 0.0295
-12.000 -1.1539 0.02066 0.01424 -0.0287 1.0000 0.0311
-11.750 -1.1447 0.02006 0.01361 -0.0260 1.0000 0.0328
-11.500 -1.1352 0.01956 0.01305 -0.0232 1.0000 0.0343
-11.250 -1.1281 0.01901 0.01249 -0.0198 1.0000 0.0363
-11.000 -1.1187 0.01851 0.01196 -0.0168 1.0000 0.0385
-10.750 -1.1050 0.01805 0.01147 -0.0145 1.0000 0.0409
-10.500 -1.0917 0.01756 0.01096 -0.0121 1.0000 0.0435
-10.250 -1.0775 0.01709 0.01049 -0.0099 1.0000 0.0465
-10.000 -1.0617 0.01670 0.01006 -0.0078 1.0000 0.0492
-9.750 -1.0462 0.01627 0.00962 -0.0057 1.0000 0.0520
-9.500 -1.0305 0.01585 0.00920 -0.0036 1.0000 0.0554
-9.250 -1.0136 0.01550 0.00882 -0.0017 1.0000 0.0587
-9.000 -0.9973 0.01511 0.00843 0.0003 1.0000 0.0625
-8.750 -0.9807 0.01474 0.00808 0.0023 1.0000 0.0672
-8.500 -0.9637 0.01441 0.00774 0.0043 1.0000 0.0718
-8.250 -0.9310 0.01399 0.00734 0.0029 0.9974 0.0790
-8.000 -0.8973 0.01358 0.00697 0.0013 0.9942 0.0867
-7.500 -0.8343 0.01283 0.00626 -0.0008 0.9857 0.1045
-7.250 -0.8025 0.01245 0.00593 -0.0019 0.9812 0.1146
-7.000 -0.7750 0.01211 0.00562 -0.0020 0.9725 0.1243
-6.750 -0.7468 0.01178 0.00531 -0.0022 0.9633 0.1346
-6.500 -0.7142 0.01144 0.00501 -0.0034 0.9562 0.1454
-6.250 -0.6809 0.01111 0.00472 -0.0046 0.9478 0.1568
-6.000 -0.6426 0.01078 0.00443 -0.0070 0.9405 0.1703
-5.750 -0.6052 0.01048 0.00415 -0.0091 0.9292 0.1827
-5.500 -0.5687 0.01018 0.00388 -0.0110 0.9166 0.1973
-5.250 -0.5355 0.00991 0.00363 -0.0122 0.9016 0.2128
-5.000 -0.5062 0.00971 0.00343 -0.0125 0.8849 0.2278
-4.750 -0.4797 0.00951 0.00324 -0.0122 0.8685 0.2450
-4.500 -0.4542 0.00934 0.00307 -0.0117 0.8525 0.2611
-4.250 -0.4290 0.00920 0.00292 -0.0110 0.8364 0.2759
-4.000 -0.4040 0.00907 0.00279 -0.0104 0.8196 0.2902
-3.750 -0.3789 0.00896 0.00265 -0.0097 0.8029 0.3046
-3.500 -0.3540 0.00884 0.00253 -0.0090 0.7868 0.3209
-3.250 -0.3288 0.00873 0.00242 -0.0083 0.7719 0.3357
-3.000 -0.3035 0.00864 0.00232 -0.0077 0.7572 0.3503
-2.750 -0.2783 0.00854 0.00222 -0.0070 0.7425 0.3672
-2.500 -0.2532 0.00844 0.00214 -0.0064 0.7275 0.3844
-2.250 -0.2282 0.00835 0.00205 -0.0057 0.7110 0.4034
-2.000 -0.2032 0.00828 0.00198 -0.0050 0.6931 0.4225
-1.750 -0.1781 0.00822 0.00192 -0.0043 0.6753 0.4401
-1.500 -0.1526 0.00817 0.00186 -0.0037 0.6589 0.4561
-1.250 -0.1270 0.00813 0.00182 -0.0031 0.6430 0.4710
-1.000 -0.1014 0.00810 0.00178 -0.0025 0.6274 0.4875
-0.750 -0.0760 0.00806 0.00175 -0.0019 0.6111 0.5055
-0.250 -0.0252 0.00801 0.00172 -0.0007 0.5786 0.5423
0.000 0.0000 0.00801 0.00172 0.0000 0.5605 0.5606
0.250 0.0252 0.00801 0.00172 0.0007 0.5423 0.5786
0.500 0.0504 0.00804 0.00173 0.0013 0.5238 0.5953
0.750 0.0760 0.00806 0.00175 0.0019 0.5057 0.6111
1.000 0.1014 0.00810 0.00178 0.0025 0.4874 0.6273
1.250 0.1270 0.00813 0.00182 0.0031 0.4710 0.6429
1.500 0.1526 0.00817 0.00186 0.0037 0.4561 0.6590
1.750 0.1780 0.00822 0.00192 0.0043 0.4401 0.6754
2.000 0.2032 0.00828 0.00198 0.0050 0.4225 0.6932
2.250 0.2282 0.00835 0.00205 0.0057 0.4036 0.7111
2.500 0.2532 0.00844 0.00214 0.0064 0.3845 0.7276
2.750 0.2783 0.00854 0.00222 0.0071 0.3667 0.7427
3.000 0.3035 0.00864 0.00232 0.0077 0.3506 0.7572
3.250 0.3288 0.00873 0.00242 0.0083 0.3358 0.7717
3.500 0.3540 0.00884 0.00253 0.0090 0.3208 0.7868
3.750 0.3790 0.00895 0.00265 0.0097 0.3050 0.8030
4.000 0.4040 0.00907 0.00279 0.0103 0.2903 0.8194
4.250 0.4290 0.00919 0.00292 0.0110 0.2761 0.8364
4.500 0.4542 0.00934 0.00307 0.0117 0.2613 0.8524
4.750 0.4796 0.00951 0.00324 0.0122 0.2447 0.8686
5.000 0.5061 0.00971 0.00343 0.0125 0.2275 0.8850
5.250 0.5354 0.00992 0.00363 0.0122 0.2124 0.9015
5.500 0.5686 0.01019 0.00388 0.0110 0.1967 0.9166
5.750 0.6053 0.01048 0.00415 0.0091 0.1827 0.9292
6.000 0.6426 0.01078 0.00443 0.0070 0.1701 0.9405
6.250 0.6808 0.01111 0.00472 0.0047 0.1569 0.9477
6.500 0.7142 0.01144 0.00501 0.0034 0.1454 0.9562
6.750 0.7469 0.01178 0.00531 0.0022 0.1345 0.9632
7.000 0.7751 0.01211 0.00562 0.0020 0.1243 0.9725
7.250 0.8026 0.01245 0.00593 0.0019 0.1148 0.9812
7.500 0.8344 0.01282 0.00626 0.0008 0.1046 0.9857
8.000 0.8973 0.01359 0.00697 -0.0013 0.0866 0.9942
8.250 0.9311 0.01399 0.00734 -0.0029 0.0787 0.9974
8.500 0.9637 0.01441 0.00774 -0.0043 0.0718 1.0000
8.750 0.9807 0.01474 0.00807 -0.0023 0.0674 1.0000
9.000 0.9974 0.01510 0.00843 -0.0003 0.0628 1.0000
9.250 1.0136 0.01550 0.00882 0.0017 0.0586 1.0000
9.500 1.0305 0.01585 0.00920 0.0036 0.0555 1.0000
9.750 1.0463 0.01627 0.00962 0.0057 0.0521 1.0000
10.000 1.0617 0.01670 0.01006 0.0078 0.0491 1.0000
10.250 1.0775 0.01709 0.01049 0.0098 0.0466 1.0000
10.500 1.0918 0.01756 0.01096 0.0121 0.0436 1.0000
10.750 1.1051 0.01805 0.01147 0.0145 0.0410 1.0000
11.000 1.1188 0.01851 0.01196 0.0168 0.0386 1.0000
11.250 1.1284 0.01900 0.01248 0.0198 0.0363 1.0000
11.500 1.1354 0.01955 0.01304 0.0231 0.0343 1.0000
11.750 1.1451 0.02006 0.01360 0.0259 0.0329 1.0000
12.000 1.1543 0.02065 0.01423 0.0286 0.0312 1.0000
12.250 1.1626 0.02136 0.01497 0.0312 0.0295 1.0000
12.500 1.1706 0.02215 0.01579 0.0336 0.0281 1.0000
12.750 1.1799 0.02293 0.01664 0.0357 0.0269 1.0000
13.000 1.1881 0.02384 0.01760 0.0376 0.0256 1.0000
13.250 1.1951 0.02490 0.01872 0.0394 0.0246 1.0000
13.500 1.2006 0.02614 0.02000 0.0411 0.0237 1.0000
13.750 1.2065 0.02745 0.02138 0.0425 0.0229 1.0000
14.000 1.2130 0.02880 0.02281 0.0436 0.0221 1.0000
14.250 1.2180 0.03037 0.02446 0.0445 0.0215 1.0000
14.500 1.2223 0.03209 0.02626 0.0452 0.0208 1.0000
14.750 1.2249 0.03408 0.02833 0.0457 0.0203 1.0000
15.000 1.2253 0.03641 0.03074 0.0459 0.0197 1.0000
15.250 1.2237 0.03907 0.03348 0.0457 0.0191 1.0000
15.500 1.2223 0.04186 0.03636 0.0453 0.0188 1.0000
15.750 1.2217 0.04467 0.03928 0.0448 0.0184 1.0000
16.000 1.2181 0.04793 0.04265 0.0439 0.0181 1.0000
16.250 1.2151 0.05124 0.04607 0.0429 0.0176 1.0000
16.500 1.2070 0.05530 0.05024 0.0415 0.0174 1.0000
16.750 1.2006 0.05928 0.05433 0.0400 0.0171 1.0000
17.000 1.1906 0.06386 0.05902 0.0381 0.0168 1.0000
17.250 1.1780 0.06895 0.06422 0.0359 0.0167 1.0000
17.500 1.1656 0.07416 0.06954 0.0336 0.0164 1.0000
17.750 1.1509 0.07979 0.07529 0.0310 0.0164 1.0000
18.000 1.1357 0.08566 0.08126 0.0283 0.0162 1.0000
18.250 1.1193 0.09182 0.08753 0.0253 0.0160 1.0000
18.500 1.1025 0.09817 0.09398 0.0223 0.0159 1.0000
18.750 1.0862 0.10454 0.10046 0.0192 0.0157 1.0000
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Polar data table (+)
Polar graphs
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