S8035 for RC aerobatic 14% thick (s8035-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8035 for RC aerobatic 14% thick (s8035-il) Reynolds number: 200,000 Max Cl/Cd: 51.23 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8035-il-200000-n5.txt Download as CSV file: xf-s8035-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -0.8917 0.14540 0.14110 0.0012 1.0000 0.0254
-18.750 -0.9229 0.13417 0.12968 -0.0051 1.0000 0.0257
-18.500 -0.9423 0.12600 0.12137 -0.0097 1.0000 0.0259
-18.250 -0.9591 0.11860 0.11383 -0.0137 1.0000 0.0263
-18.000 -0.9737 0.11180 0.10689 -0.0174 1.0000 0.0267
-17.750 -0.9865 0.10555 0.10051 -0.0207 1.0000 0.0271
-17.500 -0.9989 0.09952 0.09433 -0.0238 1.0000 0.0275
-17.250 -1.0102 0.09380 0.08846 -0.0267 1.0000 0.0280
-17.000 -1.0196 0.08856 0.08307 -0.0293 1.0000 0.0283
-16.750 -1.0283 0.08370 0.07817 -0.0316 1.0000 0.0289
-16.500 -1.0369 0.07891 0.07330 -0.0338 1.0000 0.0293
-16.250 -1.0450 0.07426 0.06856 -0.0359 1.0000 0.0298
-16.000 -1.0532 0.06972 0.06392 -0.0380 1.0000 0.0304
-15.750 -1.0597 0.06554 0.05963 -0.0398 1.0000 0.0310
-15.500 -1.0655 0.06159 0.05557 -0.0414 1.0000 0.0318
-15.250 -1.0702 0.05793 0.05179 -0.0426 1.0000 0.0325
-15.000 -1.0739 0.05451 0.04824 -0.0437 1.0000 0.0333
-14.750 -1.0767 0.05132 0.04491 -0.0445 1.0000 0.0340
-14.500 -1.0805 0.04813 0.04163 -0.0451 1.0000 0.0348
-14.250 -1.0845 0.04505 0.03850 -0.0457 1.0000 0.0358
-14.000 -1.0859 0.04237 0.03573 -0.0459 1.0000 0.0366
-13.750 -1.0851 0.04002 0.03327 -0.0458 1.0000 0.0379
-13.500 -1.0838 0.03784 0.03099 -0.0455 1.0000 0.0392
-13.250 -1.0798 0.03599 0.02900 -0.0449 1.0000 0.0410
-13.000 -1.0782 0.03406 0.02700 -0.0441 1.0000 0.0423
-12.750 -1.0770 0.03225 0.02514 -0.0429 1.0000 0.0438
-12.500 -1.0727 0.03076 0.02358 -0.0416 1.0000 0.0457
-12.250 -1.0670 0.02945 0.02218 -0.0401 1.0000 0.0477
-12.000 -1.0592 0.02835 0.02095 -0.0385 1.0000 0.0498
-11.750 -1.0562 0.02707 0.01966 -0.0363 1.0000 0.0521
-11.500 -1.0498 0.02607 0.01861 -0.0341 1.0000 0.0547
-11.250 -1.0415 0.02523 0.01769 -0.0318 1.0000 0.0576
-11.000 -1.0338 0.02442 0.01682 -0.0292 1.0000 0.0605
-10.750 -1.0279 0.02364 0.01603 -0.0263 1.0000 0.0635
-10.500 -1.0198 0.02300 0.01535 -0.0233 1.0000 0.0671
-10.250 -1.0101 0.02242 0.01469 -0.0205 1.0000 0.0706
-10.000 -1.0005 0.02173 0.01400 -0.0178 1.0000 0.0747
-9.750 -0.9876 0.02117 0.01340 -0.0155 1.0000 0.0796
-9.500 -0.9747 0.02059 0.01281 -0.0132 1.0000 0.0843
-9.250 -0.9612 0.02004 0.01225 -0.0109 1.0000 0.0902
-9.000 -0.9463 0.01954 0.01172 -0.0088 1.0000 0.0961
-8.750 -0.9320 0.01901 0.01119 -0.0066 1.0000 0.1028
-8.500 -0.9165 0.01855 0.01071 -0.0046 1.0000 0.1098
-8.250 -0.9014 0.01807 0.01024 -0.0025 1.0000 0.1176
-8.000 -0.8858 0.01762 0.00980 -0.0004 1.0000 0.1255
-7.750 -0.8696 0.01722 0.00940 0.0016 1.0000 0.1342
-7.500 -0.8543 0.01679 0.00900 0.0037 1.0000 0.1425
-7.250 -0.8381 0.01644 0.00864 0.0057 1.0000 0.1517
-7.000 -0.8228 0.01608 0.00830 0.0079 1.0000 0.1614
-6.750 -0.8052 0.01572 0.00798 0.0095 0.9994 0.1716
-6.500 -0.7696 0.01533 0.00760 0.0075 0.9943 0.1857
-6.250 -0.7359 0.01494 0.00725 0.0060 0.9883 0.2010
-6.000 -0.7010 0.01458 0.00693 0.0042 0.9824 0.2175
-5.750 -0.6700 0.01422 0.00660 0.0033 0.9738 0.2343
-5.500 -0.6379 0.01387 0.00630 0.0022 0.9655 0.2524
-5.250 -0.6049 0.01353 0.00601 0.0010 0.9574 0.2716
-5.000 -0.5737 0.01318 0.00573 0.0001 0.9481 0.2903
-4.750 -0.5371 0.01286 0.00546 -0.0018 0.9413 0.3098
-4.500 -0.5049 0.01258 0.00522 -0.0027 0.9308 0.3286
-4.250 -0.4702 0.01230 0.00497 -0.0041 0.9219 0.3484
-4.000 -0.4356 0.01203 0.00475 -0.0055 0.9120 0.3676
-3.750 -0.4029 0.01178 0.00454 -0.0065 0.9005 0.3873
-3.500 -0.3700 0.01155 0.00436 -0.0074 0.8887 0.4077
-3.250 -0.3380 0.01135 0.00418 -0.0082 0.8759 0.4288
-3.000 -0.3082 0.01116 0.00403 -0.0084 0.8618 0.4495
-2.750 -0.2806 0.01101 0.00391 -0.0081 0.8463 0.4689
-2.500 -0.2538 0.01089 0.00379 -0.0077 0.8305 0.4872
-2.250 -0.2276 0.01079 0.00369 -0.0071 0.8150 0.5051
-2.000 -0.2018 0.01070 0.00361 -0.0065 0.7997 0.5238
-1.750 -0.1764 0.01061 0.00354 -0.0057 0.7843 0.5423
-1.500 -0.1511 0.01053 0.00348 -0.0049 0.7689 0.5611
-1.250 -0.1260 0.01046 0.00344 -0.0041 0.7528 0.5802
-1.000 -0.1008 0.01042 0.00339 -0.0033 0.7361 0.5989
-0.750 -0.0757 0.01038 0.00335 -0.0024 0.7189 0.6174
-0.500 -0.0505 0.01036 0.00332 -0.0016 0.7019 0.6348
-0.250 -0.0252 0.01035 0.00330 -0.0008 0.6852 0.6518
0.000 0.0000 0.01034 0.00330 0.0000 0.6685 0.6684
0.250 0.0253 0.01035 0.00330 0.0008 0.6519 0.6852
0.500 0.0505 0.01036 0.00332 0.0016 0.6348 0.7019
0.750 0.0757 0.01038 0.00335 0.0024 0.6173 0.7190
1.000 0.1008 0.01042 0.00339 0.0033 0.5990 0.7361
1.250 0.1259 0.01046 0.00344 0.0041 0.5800 0.7529
1.500 0.1511 0.01053 0.00348 0.0049 0.5611 0.7689
1.750 0.1764 0.01061 0.00354 0.0057 0.5424 0.7843
2.000 0.2018 0.01070 0.00361 0.0065 0.5237 0.7998
2.250 0.2276 0.01079 0.00369 0.0071 0.5053 0.8149
2.500 0.2538 0.01089 0.00379 0.0077 0.4872 0.8305
2.750 0.2806 0.01101 0.00391 0.0081 0.4690 0.8463
3.000 0.3082 0.01116 0.00403 0.0084 0.4494 0.8618
3.250 0.3379 0.01135 0.00418 0.0082 0.4288 0.8759
3.500 0.3700 0.01155 0.00436 0.0074 0.4080 0.8886
3.750 0.4029 0.01178 0.00454 0.0065 0.3872 0.9005
4.000 0.4356 0.01203 0.00475 0.0055 0.3675 0.9120
4.250 0.4701 0.01230 0.00497 0.0041 0.3484 0.9218
4.500 0.5049 0.01258 0.00522 0.0027 0.3287 0.9308
4.750 0.5372 0.01286 0.00546 0.0018 0.3100 0.9413
5.000 0.5738 0.01318 0.00573 -0.0001 0.2904 0.9481
5.250 0.6049 0.01353 0.00601 -0.0010 0.2716 0.9574
5.500 0.6379 0.01387 0.00630 -0.0022 0.2525 0.9655
5.750 0.6700 0.01422 0.00660 -0.0033 0.2343 0.9738
6.000 0.7011 0.01458 0.00693 -0.0042 0.2174 0.9824
6.250 0.7360 0.01494 0.00725 -0.0060 0.2009 0.9883
6.500 0.7697 0.01533 0.00760 -0.0076 0.1857 0.9943
6.750 0.8053 0.01572 0.00797 -0.0096 0.1718 0.9994
7.000 0.8228 0.01608 0.00830 -0.0079 0.1614 1.0000
7.250 0.8381 0.01644 0.00863 -0.0057 0.1517 1.0000
7.500 0.8543 0.01679 0.00899 -0.0037 0.1426 1.0000
7.750 0.8696 0.01722 0.00940 -0.0016 0.1342 1.0000
8.000 0.8858 0.01762 0.00980 0.0004 0.1255 1.0000
8.250 0.9014 0.01807 0.01024 0.0025 0.1176 1.0000
8.500 0.9165 0.01855 0.01070 0.0046 0.1098 1.0000
8.750 0.9321 0.01901 0.01119 0.0066 0.1028 1.0000
9.000 0.9463 0.01955 0.01171 0.0088 0.0960 1.0000
9.250 0.9612 0.02004 0.01225 0.0109 0.0901 1.0000
9.500 0.9748 0.02059 0.01281 0.0132 0.0844 1.0000
9.750 0.9877 0.02117 0.01340 0.0155 0.0795 1.0000
10.000 1.0006 0.02172 0.01400 0.0178 0.0747 1.0000
10.250 1.0102 0.02242 0.01469 0.0205 0.0707 1.0000
10.500 1.0199 0.02300 0.01535 0.0233 0.0671 1.0000
10.750 1.0281 0.02364 0.01603 0.0262 0.0636 1.0000
11.000 1.0341 0.02442 0.01682 0.0292 0.0605 1.0000
11.250 1.0418 0.02523 0.01768 0.0318 0.0577 1.0000
11.500 1.0502 0.02606 0.01861 0.0340 0.0547 1.0000
11.750 1.0566 0.02706 0.01966 0.0362 0.0520 1.0000
12.000 1.0598 0.02833 0.02093 0.0384 0.0498 1.0000
12.250 1.0675 0.02944 0.02217 0.0400 0.0477 1.0000
12.500 1.0733 0.03074 0.02357 0.0416 0.0457 1.0000
12.750 1.0776 0.03222 0.02512 0.0429 0.0439 1.0000
13.000 1.0791 0.03402 0.02696 0.0440 0.0423 1.0000
13.250 1.0812 0.03591 0.02893 0.0448 0.0407 1.0000
13.500 1.0843 0.03783 0.03097 0.0454 0.0394 1.0000
13.750 1.0863 0.03995 0.03321 0.0458 0.0379 1.0000
14.000 1.0868 0.04234 0.03569 0.0458 0.0366 1.0000
14.250 1.0854 0.04503 0.03846 0.0456 0.0356 1.0000
14.500 1.0818 0.04807 0.04157 0.0450 0.0348 1.0000
14.750 1.0782 0.05123 0.04482 0.0443 0.0340 1.0000
15.000 1.0756 0.05442 0.04815 0.0435 0.0332 1.0000
15.250 1.0719 0.05784 0.05170 0.0425 0.0324 1.0000
15.500 1.0671 0.06152 0.05550 0.0412 0.0316 1.0000
15.750 1.0614 0.06542 0.05952 0.0397 0.0310 1.0000
16.000 1.0544 0.06969 0.06389 0.0378 0.0303 1.0000
16.250 1.0470 0.07414 0.06843 0.0358 0.0298 1.0000
16.500 1.0385 0.07881 0.07319 0.0337 0.0293 1.0000
16.750 1.0303 0.08358 0.07804 0.0314 0.0288 1.0000
17.000 1.0216 0.08844 0.08295 0.0291 0.0283 1.0000
17.250 1.0111 0.09390 0.08856 0.0264 0.0278 1.0000
17.500 1.0007 0.09944 0.09425 0.0237 0.0275 1.0000
17.750 0.9883 0.10549 0.10045 0.0205 0.0270 1.0000
18.000 0.9753 0.11180 0.10690 0.0172 0.0266 1.0000
18.250 0.9606 0.11860 0.11383 0.0135 0.0262 1.0000
18.500 0.9439 0.12602 0.12138 0.0094 0.0258 1.0000
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Polar data table (+)
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