S8035 for RC aerobatic 14% thick (s8035-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8035 for RC aerobatic 14% thick (s8035-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.72 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8035-il-1000000.txt Download as CSV file: xf-s8035-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.250 -1.1778 0.09694 0.09346 -0.0230 1.0000 0.0145
-19.000 -1.1976 0.09035 0.08676 -0.0261 1.0000 0.0145
-18.750 -1.2155 0.08411 0.08042 -0.0290 1.0000 0.0146
-18.500 -1.2280 0.07883 0.07503 -0.0313 1.0000 0.0148
-18.250 -1.2459 0.07281 0.06889 -0.0340 1.0000 0.0149
-18.000 -1.2580 0.06775 0.06373 -0.0362 1.0000 0.0150
-17.750 -1.2687 0.06302 0.05889 -0.0382 1.0000 0.0151
-17.500 -1.2749 0.05896 0.05473 -0.0398 1.0000 0.0153
-17.250 -1.2924 0.05355 0.04919 -0.0419 1.0000 0.0155
-17.000 -1.3044 0.04904 0.04457 -0.0435 1.0000 0.0156
-16.750 -1.3163 0.04470 0.04013 -0.0449 1.0000 0.0160
-16.500 -1.3224 0.04125 0.03658 -0.0457 1.0000 0.0163
-16.250 -1.3243 0.03838 0.03364 -0.0462 1.0000 0.0167
-16.000 -1.3260 0.03567 0.03084 -0.0464 1.0000 0.0170
-15.750 -1.3237 0.03348 0.02858 -0.0463 1.0000 0.0173
-15.500 -1.3187 0.03165 0.02669 -0.0460 1.0000 0.0179
-15.250 -1.3132 0.02996 0.02492 -0.0455 1.0000 0.0183
-15.000 -1.3066 0.02844 0.02333 -0.0448 1.0000 0.0186
-14.750 -1.2997 0.02704 0.02185 -0.0439 1.0000 0.0189
-14.500 -1.2991 0.02527 0.02000 -0.0425 1.0000 0.0196
-14.250 -1.2952 0.02387 0.01856 -0.0409 1.0000 0.0205
-14.000 -1.2880 0.02279 0.01743 -0.0393 1.0000 0.0211
-13.750 -1.2795 0.02186 0.01646 -0.0375 1.0000 0.0218
-13.500 -1.2703 0.02105 0.01558 -0.0355 1.0000 0.0225
-13.250 -1.2590 0.02040 0.01488 -0.0336 1.0000 0.0231
-13.000 -1.2522 0.01959 0.01401 -0.0310 1.0000 0.0239
-12.750 -1.2455 0.01884 0.01323 -0.0281 1.0000 0.0250
-12.500 -1.2375 0.01823 0.01260 -0.0252 1.0000 0.0262
-12.250 -1.2280 0.01776 0.01210 -0.0223 1.0000 0.0274
-12.000 -1.2190 0.01737 0.01166 -0.0191 1.0000 0.0282
-11.750 -1.2127 0.01681 0.01109 -0.0154 1.0000 0.0302
-11.500 -1.2003 0.01630 0.01059 -0.0129 1.0000 0.0325
-11.250 -1.1850 0.01593 0.01019 -0.0108 1.0000 0.0342
-11.000 -1.1725 0.01540 0.00967 -0.0082 1.0000 0.0375
-10.750 -1.1569 0.01500 0.00926 -0.0061 1.0000 0.0403
-10.500 -1.1405 0.01462 0.00886 -0.0040 1.0000 0.0432
-10.250 -1.1251 0.01418 0.00845 -0.0019 1.0000 0.0467
-10.000 -1.1073 0.01388 0.00812 -0.0001 1.0000 0.0493
-9.750 -1.0906 0.01350 0.00775 0.0019 1.0000 0.0529
-9.500 -1.0738 0.01313 0.00740 0.0039 1.0000 0.0568
-9.250 -1.0554 0.01288 0.00712 0.0057 1.0000 0.0594
-9.000 -1.0393 0.01250 0.00677 0.0078 1.0000 0.0646
-8.750 -1.0222 0.01221 0.00650 0.0098 1.0000 0.0687
-8.500 -0.9926 0.01187 0.00618 0.0092 0.9988 0.0752
-8.250 -0.9579 0.01157 0.00589 0.0075 0.9968 0.0817
-8.000 -0.9232 0.01120 0.00559 0.0058 0.9948 0.0911
-7.750 -0.8874 0.01089 0.00532 0.0039 0.9932 0.1002
-7.500 -0.8550 0.01059 0.00504 0.0028 0.9898 0.1083
-7.250 -0.8213 0.01024 0.00476 0.0013 0.9866 0.1191
-7.000 -0.7859 0.00992 0.00449 -0.0005 0.9839 0.1313
-6.750 -0.7527 0.00959 0.00423 -0.0017 0.9800 0.1450
-6.500 -0.7222 0.00927 0.00398 -0.0024 0.9734 0.1582
-6.250 -0.6890 0.00897 0.00374 -0.0036 0.9682 0.1715
-6.000 -0.6593 0.00870 0.00350 -0.0040 0.9594 0.1840
-5.750 -0.6228 0.00841 0.00327 -0.0059 0.9536 0.1987
-5.500 -0.5863 0.00812 0.00305 -0.0078 0.9449 0.2159
-5.250 -0.5495 0.00786 0.00284 -0.0097 0.9333 0.2325
-5.000 -0.5164 0.00766 0.00264 -0.0108 0.9165 0.2477
-4.750 -0.4883 0.00750 0.00248 -0.0108 0.8968 0.2634
-4.500 -0.4626 0.00738 0.00234 -0.0102 0.8786 0.2792
-4.250 -0.4374 0.00725 0.00222 -0.0096 0.8625 0.2966
-4.000 -0.4123 0.00713 0.00212 -0.0089 0.8475 0.3150
-3.750 -0.3869 0.00702 0.00202 -0.0083 0.8330 0.3322
-3.500 -0.3614 0.00692 0.00192 -0.0077 0.8186 0.3485
-3.250 -0.3358 0.00682 0.00183 -0.0071 0.8040 0.3639
-3.000 -0.3102 0.00674 0.00175 -0.0065 0.7886 0.3801
-2.750 -0.2847 0.00666 0.00167 -0.0059 0.7718 0.3977
-2.500 -0.2592 0.00658 0.00160 -0.0053 0.7552 0.4149
-2.250 -0.2333 0.00652 0.00154 -0.0048 0.7400 0.4311
-2.000 -0.2075 0.00645 0.00148 -0.0042 0.7250 0.4494
-1.750 -0.1817 0.00638 0.00143 -0.0037 0.7097 0.4678
-1.500 -0.1559 0.00633 0.00139 -0.0031 0.6941 0.4875
-1.250 -0.1299 0.00628 0.00135 -0.0026 0.6791 0.5069
-1.000 -0.1039 0.00625 0.00132 -0.0021 0.6630 0.5247
-0.750 -0.0778 0.00623 0.00130 -0.0016 0.6460 0.5411
-0.500 -0.0517 0.00622 0.00128 -0.0011 0.6281 0.5569
-0.250 -0.0257 0.00621 0.00127 -0.0006 0.6101 0.5735
0.000 0.0000 0.00621 0.00127 0.0000 0.5915 0.5914
0.250 0.0258 0.00621 0.00127 0.0006 0.5736 0.6102
0.500 0.0517 0.00622 0.00128 0.0011 0.5568 0.6285
0.750 0.0778 0.00623 0.00130 0.0016 0.5411 0.6461
1.000 0.1039 0.00625 0.00132 0.0021 0.5246 0.6631
1.250 0.1299 0.00628 0.00135 0.0026 0.5070 0.6791
1.500 0.1559 0.00633 0.00139 0.0031 0.4877 0.6940
1.750 0.1817 0.00639 0.00143 0.0037 0.4675 0.7095
2.000 0.2075 0.00645 0.00148 0.0042 0.4489 0.7250
2.250 0.2333 0.00652 0.00154 0.0048 0.4313 0.7401
2.500 0.2592 0.00658 0.00160 0.0053 0.4149 0.7553
2.750 0.2848 0.00665 0.00167 0.0059 0.3982 0.7718
3.000 0.3102 0.00674 0.00175 0.0065 0.3801 0.7884
3.250 0.3358 0.00682 0.00183 0.0071 0.3639 0.8040
3.500 0.3614 0.00692 0.00192 0.0077 0.3484 0.8186
3.750 0.3868 0.00702 0.00202 0.0083 0.3318 0.8330
4.000 0.4122 0.00713 0.00212 0.0089 0.3152 0.8476
4.250 0.4374 0.00725 0.00223 0.0096 0.2964 0.8626
4.500 0.4625 0.00738 0.00234 0.0102 0.2790 0.8786
4.750 0.4883 0.00751 0.00248 0.0108 0.2633 0.8967
5.000 0.5163 0.00766 0.00264 0.0108 0.2477 0.9164
5.250 0.5495 0.00786 0.00284 0.0097 0.2324 0.9334
5.500 0.5863 0.00812 0.00305 0.0078 0.2160 0.9449
5.750 0.6228 0.00841 0.00327 0.0059 0.1985 0.9534
6.000 0.6593 0.00870 0.00350 0.0040 0.1839 0.9594
6.250 0.6890 0.00897 0.00374 0.0036 0.1716 0.9683
6.500 0.7222 0.00927 0.00398 0.0024 0.1582 0.9733
6.750 0.7528 0.00959 0.00423 0.0017 0.1450 0.9799
7.000 0.7859 0.00992 0.00449 0.0005 0.1311 0.9839
7.250 0.8213 0.01025 0.00476 -0.0013 0.1190 0.9866
7.500 0.8550 0.01059 0.00504 -0.0028 0.1084 0.9898
7.750 0.8874 0.01089 0.00532 -0.0039 0.1002 0.9932
8.000 0.9232 0.01120 0.00559 -0.0058 0.0911 0.9948
8.250 0.9580 0.01157 0.00589 -0.0075 0.0817 0.9969
8.500 0.9928 0.01187 0.00618 -0.0092 0.0753 0.9988
8.750 1.0222 0.01221 0.00650 -0.0098 0.0688 1.0000
9.000 1.0393 0.01250 0.00677 -0.0078 0.0646 1.0000
9.250 1.0554 0.01288 0.00712 -0.0057 0.0594 1.0000
9.500 1.0738 0.01313 0.00740 -0.0039 0.0568 1.0000
9.750 1.0906 0.01350 0.00775 -0.0019 0.0529 1.0000
10.000 1.1073 0.01387 0.00812 0.0001 0.0493 1.0000
10.250 1.1251 0.01418 0.00845 0.0019 0.0468 1.0000
10.500 1.1406 0.01462 0.00886 0.0040 0.0432 1.0000
10.750 1.1569 0.01500 0.00926 0.0061 0.0404 1.0000
11.000 1.1725 0.01540 0.00967 0.0082 0.0375 1.0000
11.250 1.1852 0.01593 0.01018 0.0107 0.0342 1.0000
11.500 1.2005 0.01630 0.01058 0.0129 0.0324 1.0000
11.750 1.2132 0.01679 0.01107 0.0154 0.0304 1.0000
12.000 1.2190 0.01737 0.01166 0.0191 0.0283 1.0000
12.250 1.2283 0.01776 0.01210 0.0222 0.0274 1.0000
12.500 1.2375 0.01824 0.01261 0.0252 0.0263 1.0000
12.750 1.2462 0.01882 0.01322 0.0280 0.0252 1.0000
13.000 1.2525 0.01959 0.01401 0.0310 0.0239 1.0000
13.250 1.2605 0.02034 0.01481 0.0334 0.0229 1.0000
13.500 1.2705 0.02106 0.01559 0.0355 0.0225 1.0000
13.750 1.2807 0.02181 0.01640 0.0373 0.0217 1.0000
14.000 1.2889 0.02276 0.01739 0.0391 0.0210 1.0000
14.250 1.2957 0.02387 0.01855 0.0408 0.0203 1.0000
14.500 1.2997 0.02526 0.02000 0.0424 0.0197 1.0000
14.750 1.2992 0.02712 0.02193 0.0439 0.0190 1.0000
15.000 1.3098 0.02823 0.02310 0.0446 0.0185 1.0000
15.250 1.3137 0.02997 0.02493 0.0454 0.0183 1.0000
15.500 1.3208 0.03152 0.02655 0.0459 0.0178 1.0000
15.750 1.3247 0.03346 0.02856 0.0462 0.0174 1.0000
16.000 1.3263 0.03572 0.03089 0.0462 0.0170 1.0000
16.250 1.3266 0.03822 0.03347 0.0461 0.0166 1.0000
16.500 1.3235 0.04122 0.03655 0.0456 0.0163 1.0000
16.750 1.3187 0.04454 0.03997 0.0448 0.0160 1.0000
17.000 1.3077 0.04875 0.04427 0.0435 0.0157 1.0000
17.250 1.2904 0.05394 0.04959 0.0416 0.0154 1.0000
17.500 1.2803 0.05840 0.05415 0.0398 0.0152 1.0000
17.750 1.2745 0.06240 0.05826 0.0383 0.0150 1.0000
18.000 1.2623 0.06735 0.06332 0.0362 0.0150 1.0000
18.250 1.2517 0.07220 0.06827 0.0341 0.0147 1.0000
18.500 1.2326 0.07838 0.07458 0.0313 0.0147 1.0000
18.750 1.2174 0.08408 0.08038 0.0287 0.0146 1.0000
19.000 1.2001 0.09024 0.08665 0.0259 0.0145 1.0000
19.250 1.1827 0.09647 0.09298 0.0230 0.0144 1.0000
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Polar data table (+)
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