S8036 (16%) (s8036-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8036 (16%) (s8036-il) Reynolds number: 50,000 Max Cl/Cd: 25.68 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8036-il-50000-n5.txt Download as CSV file: xf-s8036-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8036 (16%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4731 0.10870 0.10096 -0.0512 1.0000 0.0497
-12.500 -0.4894 0.10078 0.09308 -0.0552 1.0000 0.0495
-12.250 -0.5066 0.09354 0.08584 -0.0588 1.0000 0.0491
-12.000 -0.5349 0.08548 0.07775 -0.0633 1.0000 0.0487
-11.750 -0.5617 0.07897 0.07118 -0.0662 1.0000 0.0483
-11.500 -0.5893 0.07339 0.06550 -0.0680 1.0000 0.0480
-11.250 -0.6148 0.06887 0.06085 -0.0682 1.0000 0.0477
-11.000 -0.6377 0.06518 0.05703 -0.0671 1.0000 0.0476
-10.750 -0.6612 0.06204 0.05373 -0.0647 1.0000 0.0478
-10.500 -0.6822 0.05946 0.05100 -0.0612 1.0000 0.0479
-10.250 -0.7011 0.05729 0.04869 -0.0567 1.0000 0.0481
-10.000 -0.7192 0.05502 0.04619 -0.0520 1.0000 0.0488
-9.750 -0.7323 0.05278 0.04370 -0.0476 1.0000 0.0494
-9.500 -0.7392 0.05084 0.04162 -0.0437 1.0000 0.0503
-9.250 -0.7397 0.04941 0.04019 -0.0403 1.0000 0.0515
-9.000 -0.7420 0.04793 0.03860 -0.0366 1.0000 0.0525
-8.750 -0.7447 0.04646 0.03699 -0.0327 1.0000 0.0538
-8.500 -0.7462 0.04493 0.03525 -0.0288 1.0000 0.0551
-8.250 -0.7459 0.04349 0.03355 -0.0251 1.0000 0.0567
-8.000 -0.7386 0.04207 0.03200 -0.0227 0.9988 0.0592
-7.750 -0.7060 0.04034 0.03015 -0.0247 0.9914 0.0636
-7.500 -0.6716 0.03853 0.02813 -0.0266 0.9844 0.0691
-7.250 -0.6394 0.03709 0.02654 -0.0280 0.9764 0.0763
-7.000 -0.6078 0.03573 0.02519 -0.0294 0.9687 0.0846
-6.750 -0.5760 0.03442 0.02384 -0.0308 0.9611 0.0958
-6.500 -0.5495 0.03322 0.02263 -0.0313 0.9520 0.1093
-6.250 -0.5217 0.03198 0.02139 -0.0321 0.9441 0.1283
-6.000 -0.5003 0.03074 0.02029 -0.0320 0.9347 0.1522
-5.750 -0.4812 0.02948 0.01923 -0.0315 0.9255 0.1862
-5.500 -0.4619 0.02806 0.01819 -0.0312 0.9171 0.2437
-5.250 -0.4518 0.02685 0.01755 -0.0290 0.9071 0.3237
-5.000 -0.4317 0.02606 0.01743 -0.0276 0.9001 0.4412
-4.750 -0.4140 0.02612 0.01776 -0.0249 0.8910 0.5232
-4.500 -0.3873 0.02634 0.01795 -0.0238 0.8842 0.5847
-4.250 -0.3665 0.02663 0.01814 -0.0217 0.8762 0.6267
-4.000 -0.3402 0.02698 0.01835 -0.0204 0.8690 0.6613
-3.750 -0.3012 0.02741 0.01863 -0.0210 0.8646 0.6929
-3.500 -0.2864 0.02770 0.01880 -0.0181 0.8551 0.7172
-3.250 -0.2455 0.02816 0.01910 -0.0191 0.8501 0.7403
-3.000 -0.2017 0.02843 0.01918 -0.0209 0.8460 0.7598
-2.750 -0.1819 0.02865 0.01927 -0.0192 0.8368 0.7756
-2.500 -0.1454 0.02865 0.01910 -0.0205 0.8316 0.7904
-2.250 -0.1091 0.02879 0.01907 -0.0218 0.8254 0.8020
-2.000 -0.0780 0.02889 0.01904 -0.0225 0.8181 0.8129
-1.750 -0.0434 0.02877 0.01877 -0.0238 0.8131 0.8250
-1.500 -0.0086 0.02898 0.01886 -0.0252 0.8058 0.8336
-1.250 0.0207 0.02899 0.01876 -0.0258 0.7991 0.8444
-1.000 0.0693 0.02895 0.01858 -0.0296 0.7950 0.8521
-0.750 0.0878 0.02917 0.01875 -0.0285 0.7860 0.8629
-0.500 0.1289 0.02919 0.01867 -0.0311 0.7804 0.8709
-0.250 0.1666 0.02915 0.01853 -0.0332 0.7752 0.8794
0.000 0.1965 0.02943 0.01879 -0.0342 0.7665 0.8877
0.250 0.2349 0.02936 0.01864 -0.0364 0.7612 0.8960
0.500 0.2706 0.02960 0.01885 -0.0385 0.7535 0.9033
0.750 0.3008 0.02969 0.01891 -0.0395 0.7463 0.9128
1.000 0.3517 0.02950 0.01867 -0.0438 0.7418 0.9181
1.250 0.3690 0.02999 0.01919 -0.0430 0.7314 0.9294
1.500 0.4158 0.02985 0.01902 -0.0466 0.7259 0.9355
1.750 0.4400 0.03024 0.01944 -0.0470 0.7166 0.9460
2.000 0.4813 0.03017 0.01938 -0.0498 0.7099 0.9535
2.250 0.5123 0.03041 0.01966 -0.0512 0.7012 0.9629
2.500 0.5477 0.03044 0.01973 -0.0531 0.6933 0.9721
2.750 0.5828 0.03056 0.01989 -0.0552 0.6847 0.9813
3.000 0.6208 0.03051 0.01989 -0.0576 0.6760 0.9896
3.250 0.6567 0.03060 0.02006 -0.0600 0.6662 0.9990
3.500 0.6744 0.03054 0.02001 -0.0585 0.6576 1.0000
3.750 0.6687 0.03106 0.02056 -0.0535 0.6466 1.0000
4.000 0.6911 0.03075 0.02024 -0.0523 0.6391 1.0000
4.250 0.6791 0.03143 0.02094 -0.0463 0.6270 1.0000
4.500 0.6907 0.03146 0.02098 -0.0435 0.6177 1.0000
4.750 0.7010 0.03152 0.02105 -0.0405 0.6073 1.0000
5.000 0.6996 0.03201 0.02155 -0.0359 0.5954 1.0000
5.250 0.7258 0.03162 0.02117 -0.0348 0.5860 1.0000
5.750 0.7370 0.03223 0.02181 -0.0274 0.5610 1.0000
6.000 0.7519 0.03222 0.02182 -0.0249 0.5490 1.0000
6.250 0.7825 0.03159 0.02121 -0.0243 0.5378 1.0000
6.500 0.7858 0.03199 0.02165 -0.0203 0.5235 1.0000
6.750 0.7913 0.03233 0.02201 -0.0166 0.5091 1.0000
7.000 0.7982 0.03258 0.02227 -0.0130 0.4948 1.0000
7.250 0.8070 0.03274 0.02246 -0.0096 0.4800 1.0000
7.500 0.8173 0.03287 0.02261 -0.0066 0.4647 1.0000
7.750 0.8281 0.03305 0.02279 -0.0037 0.4485 1.0000
8.000 0.8387 0.03328 0.02303 -0.0008 0.4313 1.0000
8.250 0.8497 0.03357 0.02331 0.0018 0.4133 1.0000
8.500 0.8621 0.03384 0.02353 0.0043 0.3946 1.0000
8.750 0.8758 0.03411 0.02372 0.0065 0.3757 1.0000
9.000 0.8823 0.03490 0.02446 0.0092 0.3563 1.0000
9.250 0.8894 0.03576 0.02527 0.0116 0.3373 1.0000
9.500 0.8967 0.03669 0.02613 0.0138 0.3190 1.0000
9.750 0.9040 0.03773 0.02709 0.0159 0.3017 1.0000
10.000 0.9113 0.03886 0.02816 0.0178 0.2858 1.0000
10.250 0.9184 0.04009 0.02933 0.0195 0.2709 1.0000
10.500 0.9257 0.04138 0.03058 0.0212 0.2571 1.0000
10.750 0.9349 0.04262 0.03174 0.0227 0.2449 1.0000
11.000 0.9429 0.04401 0.03311 0.0241 0.2333 1.0000
11.250 0.9497 0.04560 0.03475 0.0253 0.2224 1.0000
11.500 0.9602 0.04692 0.03604 0.0265 0.2129 1.0000
11.750 0.9687 0.04848 0.03765 0.0276 0.2039 1.0000
12.000 0.9775 0.05007 0.03929 0.0286 0.1957 1.0000
12.250 0.9871 0.05159 0.04084 0.0295 0.1879 1.0000
12.500 0.9963 0.05331 0.04264 0.0303 0.1811 1.0000
12.750 1.0030 0.05520 0.04465 0.0311 0.1744 1.0000
13.000 1.0171 0.05653 0.04596 0.0319 0.1684 1.0000
13.250 1.0149 0.05932 0.04899 0.0325 0.1630 1.0000
13.500 1.0255 0.06095 0.05066 0.0331 0.1577 1.0000
13.750 1.0324 0.06306 0.05286 0.0337 0.1532 1.0000
14.000 1.0220 0.06683 0.05689 0.0339 0.1492 1.0000
14.250 1.0210 0.06971 0.05992 0.0340 0.1451 1.0000
14.500 1.0424 0.07035 0.06046 0.0348 0.1405 1.0000
14.750 1.0159 0.07614 0.06659 0.0339 0.1383 1.0000
15.000 0.9814 0.08345 0.07419 0.0320 0.1362 1.0000
15.250 0.9295 0.09430 0.08529 0.0279 0.1345 1.0000
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