S8035 for RC aerobatic 14% thick (s8035-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8035 for RC aerobatic 14% thick (s8035-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.68 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8035-il-1000000-n5.txt Download as CSV file: xf-s8035-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.1843 0.10291 0.09937 -0.0203 1.0000 0.0104
-19.500 -1.2068 0.09577 0.09211 -0.0238 1.0000 0.0104
-19.250 -1.2296 0.08871 0.08493 -0.0271 1.0000 0.0105
-19.000 -1.2503 0.08212 0.07821 -0.0302 1.0000 0.0105
-18.750 -1.2691 0.07596 0.07194 -0.0330 1.0000 0.0106
-18.500 -1.2852 0.07028 0.06615 -0.0355 1.0000 0.0107
-18.250 -1.3008 0.06481 0.06056 -0.0379 1.0000 0.0108
-18.000 -1.3124 0.06004 0.05569 -0.0399 1.0000 0.0110
-17.750 -1.3221 0.05563 0.05118 -0.0416 1.0000 0.0112
-17.500 -1.3296 0.05165 0.04710 -0.0430 1.0000 0.0114
-17.250 -1.3353 0.04801 0.04337 -0.0442 1.0000 0.0115
-17.000 -1.3394 0.04468 0.03993 -0.0451 1.0000 0.0117
-16.750 -1.3415 0.04170 0.03686 -0.0458 1.0000 0.0118
-16.500 -1.3412 0.03906 0.03414 -0.0462 1.0000 0.0120
-16.250 -1.3403 0.03660 0.03159 -0.0464 1.0000 0.0123
-16.000 -1.3402 0.03418 0.02908 -0.0464 1.0000 0.0125
-15.750 -1.3373 0.03212 0.02696 -0.0461 1.0000 0.0128
-15.500 -1.3342 0.03020 0.02498 -0.0457 1.0000 0.0133
-15.250 -1.3292 0.02855 0.02327 -0.0450 1.0000 0.0137
-15.000 -1.3231 0.02708 0.02174 -0.0441 1.0000 0.0141
-14.750 -1.3161 0.02577 0.02036 -0.0430 1.0000 0.0144
-14.500 -1.3083 0.02459 0.01913 -0.0418 1.0000 0.0148
-14.250 -1.2991 0.02360 0.01807 -0.0404 1.0000 0.0153
-14.000 -1.2919 0.02253 0.01695 -0.0387 1.0000 0.0159
-13.750 -1.2838 0.02160 0.01598 -0.0368 1.0000 0.0165
-13.500 -1.2749 0.02078 0.01512 -0.0348 1.0000 0.0171
-13.250 -1.2653 0.02006 0.01437 -0.0327 1.0000 0.0178
-13.000 -1.2549 0.01945 0.01370 -0.0304 1.0000 0.0183
-12.750 -1.2440 0.01890 0.01311 -0.0281 1.0000 0.0187
-12.500 -1.2343 0.01836 0.01253 -0.0254 1.0000 0.0195
-12.250 -1.2265 0.01782 0.01197 -0.0223 1.0000 0.0207
-12.000 -1.2184 0.01738 0.01151 -0.0189 1.0000 0.0215
-11.750 -1.2090 0.01697 0.01107 -0.0158 1.0000 0.0226
-11.500 -1.1957 0.01652 0.01060 -0.0134 1.0000 0.0239
-11.250 -1.1822 0.01606 0.01014 -0.0110 1.0000 0.0256
-11.000 -1.1674 0.01565 0.00971 -0.0088 1.0000 0.0274
-10.750 -1.1517 0.01527 0.00931 -0.0067 1.0000 0.0291
-10.500 -1.1362 0.01485 0.00890 -0.0045 1.0000 0.0316
-10.250 -1.1193 0.01450 0.00854 -0.0026 1.0000 0.0337
-10.000 -1.1025 0.01414 0.00817 -0.0006 1.0000 0.0361
-9.750 -1.0833 0.01377 0.00782 0.0008 0.9998 0.0390
-9.500 -1.0518 0.01341 0.00745 -0.0003 0.9982 0.0422
-9.250 -1.0204 0.01300 0.00706 -0.0014 0.9962 0.0463
-9.000 -0.9871 0.01267 0.00673 -0.0028 0.9942 0.0495
-8.750 -0.9565 0.01230 0.00638 -0.0037 0.9916 0.0536
-8.500 -0.9272 0.01196 0.00605 -0.0042 0.9879 0.0577
-8.250 -0.8964 0.01164 0.00574 -0.0050 0.9844 0.0623
-8.000 -0.8687 0.01131 0.00544 -0.0052 0.9790 0.0681
-7.750 -0.8424 0.01098 0.00515 -0.0050 0.9698 0.0748
-7.500 -0.8133 0.01068 0.00486 -0.0054 0.9601 0.0810
-7.250 -0.7761 0.01032 0.00455 -0.0076 0.9528 0.0907
-7.000 -0.7349 0.00995 0.00423 -0.0107 0.9431 0.1019
-6.500 -0.6637 0.00942 0.00367 -0.0141 0.9025 0.1214
-6.250 -0.6384 0.00923 0.00346 -0.0136 0.8817 0.1307
-6.000 -0.6136 0.00909 0.00328 -0.0129 0.8643 0.1388
-5.750 -0.5891 0.00895 0.00312 -0.0122 0.8481 0.1488
-5.500 -0.5647 0.00878 0.00295 -0.0115 0.8325 0.1595
-5.250 -0.5397 0.00866 0.00280 -0.0108 0.8172 0.1682
-5.000 -0.5148 0.00854 0.00265 -0.0102 0.8008 0.1780
-4.750 -0.4903 0.00840 0.00251 -0.0094 0.7831 0.1902
-4.500 -0.4655 0.00828 0.00237 -0.0087 0.7660 0.2029
-4.250 -0.4406 0.00814 0.00224 -0.0081 0.7506 0.2180
-4.000 -0.4154 0.00800 0.00212 -0.0075 0.7364 0.2341
-3.750 -0.3899 0.00788 0.00201 -0.0070 0.7224 0.2489
-3.500 -0.3642 0.00778 0.00191 -0.0064 0.7082 0.2620
-3.250 -0.3382 0.00770 0.00182 -0.0060 0.6934 0.2732
-3.000 -0.3124 0.00763 0.00173 -0.0055 0.6774 0.2862
-2.750 -0.2868 0.00756 0.00165 -0.0049 0.6585 0.3019
-2.500 -0.2611 0.00750 0.00158 -0.0044 0.6401 0.3165
-2.250 -0.2351 0.00744 0.00152 -0.0040 0.6243 0.3295
-2.000 -0.2090 0.00737 0.00146 -0.0035 0.6092 0.3456
-1.750 -0.1830 0.00731 0.00141 -0.0031 0.5938 0.3619
-1.500 -0.1570 0.00725 0.00136 -0.0026 0.5780 0.3804
-1.250 -0.1310 0.00719 0.00132 -0.0021 0.5637 0.3992
-1.000 -0.1048 0.00715 0.00129 -0.0017 0.5479 0.4157
-0.750 -0.0784 0.00715 0.00127 -0.0013 0.5306 0.4296
-0.500 -0.0522 0.00715 0.00125 -0.0009 0.5117 0.4429
-0.250 -0.0260 0.00716 0.00124 -0.0005 0.4935 0.4576
0.000 0.0000 0.00716 0.00124 0.0000 0.4751 0.4749
0.250 0.0260 0.00716 0.00124 0.0005 0.4578 0.4937
0.500 0.0521 0.00715 0.00125 0.0009 0.4429 0.5124
0.750 0.0784 0.00715 0.00127 0.0013 0.4296 0.5306
1.000 0.1048 0.00715 0.00129 0.0017 0.4155 0.5480
1.250 0.1310 0.00719 0.00132 0.0021 0.3994 0.5638
1.500 0.1570 0.00725 0.00136 0.0026 0.3807 0.5778
1.750 0.1830 0.00731 0.00141 0.0031 0.3614 0.5932
2.000 0.2090 0.00737 0.00146 0.0035 0.3449 0.6091
2.250 0.2351 0.00743 0.00152 0.0040 0.3299 0.6245
2.500 0.2611 0.00750 0.00158 0.0044 0.3165 0.6402
2.750 0.2869 0.00755 0.00165 0.0049 0.3026 0.6585
3.000 0.3124 0.00763 0.00173 0.0055 0.2863 0.6770
3.250 0.3382 0.00770 0.00182 0.0060 0.2733 0.6936
3.500 0.3642 0.00778 0.00191 0.0064 0.2619 0.7083
3.750 0.3898 0.00788 0.00201 0.0070 0.2481 0.7225
4.000 0.4154 0.00800 0.00212 0.0075 0.2345 0.7368
4.250 0.4405 0.00814 0.00224 0.0081 0.2176 0.7508
4.500 0.4655 0.00828 0.00237 0.0087 0.2027 0.7661
4.750 0.4903 0.00841 0.00251 0.0094 0.1899 0.7830
5.000 0.5148 0.00854 0.00265 0.0101 0.1779 0.8006
5.250 0.5397 0.00866 0.00280 0.0108 0.1683 0.8173
5.500 0.5647 0.00879 0.00295 0.0115 0.1594 0.8324
5.750 0.5891 0.00895 0.00312 0.0122 0.1485 0.8477
6.000 0.6136 0.00910 0.00328 0.0129 0.1387 0.8643
6.250 0.6384 0.00923 0.00346 0.0136 0.1307 0.8819
6.500 0.6637 0.00942 0.00367 0.0141 0.1215 0.9025
7.000 0.7348 0.00995 0.00423 0.0107 0.1018 0.9431
7.250 0.7762 0.01032 0.00455 0.0076 0.0903 0.9528
7.500 0.8133 0.01068 0.00486 0.0054 0.0810 0.9599
8.000 0.8688 0.01130 0.00544 0.0052 0.0683 0.9790
8.250 0.8965 0.01164 0.00574 0.0050 0.0624 0.9844
8.500 0.9273 0.01196 0.00605 0.0042 0.0578 0.9880
8.750 0.9566 0.01230 0.00638 0.0036 0.0537 0.9916
9.000 0.9871 0.01267 0.00673 0.0028 0.0495 0.9941
9.250 1.0204 0.01299 0.00705 0.0014 0.0464 0.9962
9.500 1.0519 0.01341 0.00745 0.0002 0.0422 0.9982
9.750 1.0834 0.01377 0.00782 -0.0009 0.0390 0.9998
10.000 1.1025 0.01414 0.00817 0.0006 0.0361 1.0000
10.250 1.1194 0.01450 0.00854 0.0026 0.0338 1.0000
10.500 1.1363 0.01485 0.00890 0.0045 0.0317 1.0000
10.750 1.1519 0.01526 0.00930 0.0066 0.0293 1.0000
11.000 1.1674 0.01565 0.00971 0.0087 0.0274 1.0000
11.250 1.1823 0.01606 0.01013 0.0110 0.0256 1.0000
11.500 1.1956 0.01653 0.01060 0.0134 0.0238 1.0000
11.750 1.2092 0.01696 0.01106 0.0157 0.0226 1.0000
12.000 1.2188 0.01737 0.01150 0.0189 0.0216 1.0000
12.250 1.2267 0.01782 0.01197 0.0222 0.0207 1.0000
12.500 1.2351 0.01833 0.01251 0.0253 0.0197 1.0000
12.750 1.2443 0.01890 0.01311 0.0280 0.0189 1.0000
13.000 1.2552 0.01944 0.01370 0.0304 0.0183 1.0000
13.250 1.2654 0.02007 0.01437 0.0326 0.0175 1.0000
13.500 1.2753 0.02078 0.01512 0.0347 0.0171 1.0000
13.750 1.2839 0.02161 0.01598 0.0368 0.0163 1.0000
14.000 1.2921 0.02254 0.01695 0.0386 0.0157 1.0000
14.250 1.2999 0.02357 0.01804 0.0403 0.0152 1.0000
14.500 1.3088 0.02459 0.01913 0.0417 0.0149 1.0000
14.750 1.3170 0.02574 0.02034 0.0429 0.0146 1.0000
15.000 1.3241 0.02704 0.02169 0.0440 0.0138 1.0000
15.250 1.3303 0.02851 0.02323 0.0448 0.0138 1.0000
15.500 1.3354 0.03016 0.02494 0.0455 0.0133 1.0000
15.750 1.3389 0.03204 0.02687 0.0460 0.0129 1.0000
16.000 1.3410 0.03417 0.02907 0.0462 0.0125 1.0000
16.250 1.3413 0.03659 0.03157 0.0462 0.0122 1.0000
16.500 1.3419 0.03908 0.03416 0.0460 0.0120 1.0000
16.750 1.3430 0.04165 0.03681 0.0456 0.0119 1.0000
17.000 1.3416 0.04454 0.03979 0.0449 0.0117 1.0000
17.250 1.3375 0.04788 0.04323 0.0440 0.0115 1.0000
17.500 1.3325 0.05144 0.04689 0.0429 0.0113 1.0000
17.750 1.3245 0.05548 0.05102 0.0414 0.0110 1.0000
18.000 1.3155 0.05981 0.05546 0.0397 0.0109 1.0000
18.250 1.3031 0.06469 0.06044 0.0377 0.0107 1.0000
18.500 1.2884 0.07004 0.06590 0.0354 0.0107 1.0000
18.750 1.2718 0.07580 0.07177 0.0328 0.0106 1.0000
19.000 1.2523 0.08206 0.07816 0.0299 0.0104 1.0000
19.250 1.2327 0.08850 0.08472 0.0269 0.0104 1.0000
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Polar data table (+)
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