J5012 12% (j5012-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: J5012 12% (j5012-il) Reynolds number: 200,000 Max Cl/Cd: 45.73 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-j5012-il-200000-n5.txt Download as CSV file: xf-j5012-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: J5012 12%
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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8530 0.10026 0.09591 -0.0277 1.0000 0.0202
-15.500 -0.8930 0.08788 0.08329 -0.0355 1.0000 0.0200
-15.250 -0.9201 0.07903 0.07423 -0.0411 1.0000 0.0201
-15.000 -0.9442 0.07147 0.06646 -0.0454 1.0000 0.0199
-14.750 -0.9622 0.06544 0.06023 -0.0487 1.0000 0.0200
-14.500 -0.9770 0.06033 0.05491 -0.0510 1.0000 0.0202
-14.250 -0.9891 0.05600 0.05037 -0.0526 1.0000 0.0206
-14.000 -0.9992 0.05208 0.04625 -0.0533 1.0000 0.0206
-13.750 -1.0071 0.04874 0.04269 -0.0535 1.0000 0.0209
-13.500 -1.0133 0.04579 0.03951 -0.0532 1.0000 0.0212
-13.250 -1.0166 0.04327 0.03676 -0.0523 1.0000 0.0215
-13.000 -1.0178 0.04094 0.03433 -0.0512 1.0000 0.0218
-12.750 -1.0166 0.03897 0.03226 -0.0498 1.0000 0.0221
-12.500 -1.0139 0.03726 0.03046 -0.0483 1.0000 0.0225
-12.250 -1.0102 0.03576 0.02887 -0.0465 1.0000 0.0228
-12.000 -1.0057 0.03428 0.02728 -0.0446 1.0000 0.0232
-11.750 -1.0005 0.03290 0.02578 -0.0425 1.0000 0.0236
-11.500 -0.9946 0.03166 0.02442 -0.0402 1.0000 0.0242
-11.250 -0.9880 0.03046 0.02309 -0.0378 1.0000 0.0249
-11.000 -0.9807 0.02936 0.02186 -0.0352 1.0000 0.0256
-10.750 -0.9726 0.02841 0.02077 -0.0326 1.0000 0.0264
-10.500 -0.9668 0.02737 0.01967 -0.0295 1.0000 0.0272
-10.250 -0.9613 0.02646 0.01873 -0.0262 1.0000 0.0279
-10.000 -0.9538 0.02570 0.01792 -0.0231 1.0000 0.0288
-9.750 -0.9439 0.02490 0.01705 -0.0204 1.0000 0.0298
-9.500 -0.9333 0.02410 0.01617 -0.0177 1.0000 0.0309
-9.250 -0.9223 0.02334 0.01533 -0.0150 1.0000 0.0319
-9.000 -0.9109 0.02262 0.01452 -0.0123 1.0000 0.0331
-8.750 -0.9013 0.02184 0.01373 -0.0094 1.0000 0.0346
-8.500 -0.8891 0.02122 0.01307 -0.0068 1.0000 0.0364
-8.250 -0.8759 0.02068 0.01246 -0.0043 1.0000 0.0389
-8.000 -0.8636 0.02007 0.01180 -0.0016 1.0000 0.0413
-7.750 -0.8516 0.01946 0.01119 0.0011 1.0000 0.0439
-7.500 -0.8380 0.01896 0.01064 0.0036 1.0000 0.0471
-7.250 -0.8244 0.01846 0.01008 0.0061 1.0000 0.0506
-7.000 -0.8107 0.01796 0.00960 0.0085 1.0000 0.0553
-6.750 -0.7958 0.01756 0.00914 0.0108 1.0000 0.0603
-6.500 -0.7816 0.01709 0.00871 0.0131 1.0000 0.0666
-6.250 -0.7566 0.01663 0.00825 0.0132 0.9980 0.0757
-6.000 -0.7249 0.01614 0.00780 0.0119 0.9943 0.0889
-5.750 -0.6949 0.01565 0.00737 0.0110 0.9902 0.1054
-5.500 -0.6640 0.01517 0.00697 0.0099 0.9859 0.1267
-5.000 -0.6043 0.01422 0.00625 0.0082 0.9768 0.1835
-4.750 -0.5736 0.01373 0.00593 0.0071 0.9723 0.2212
-4.500 -0.5433 0.01326 0.00563 0.0062 0.9678 0.2622
-4.250 -0.5162 0.01284 0.00536 0.0061 0.9615 0.3033
-4.000 -0.4846 0.01241 0.00511 0.0050 0.9572 0.3496
-3.750 -0.4572 0.01202 0.00490 0.0049 0.9514 0.3959
-3.500 -0.4290 0.01165 0.00470 0.0047 0.9453 0.4414
-3.250 -0.3963 0.01129 0.00453 0.0036 0.9414 0.4874
-3.000 -0.3704 0.01101 0.00438 0.0041 0.9339 0.5257
-2.750 -0.3390 0.01074 0.00425 0.0034 0.9283 0.5640
-2.500 -0.3077 0.01050 0.00413 0.0029 0.9228 0.5999
-2.250 -0.2805 0.01030 0.00404 0.0032 0.9146 0.6322
-2.000 -0.2463 0.01010 0.00393 0.0021 0.9096 0.6635
-1.750 -0.2202 0.00997 0.00388 0.0028 0.8996 0.6900
-1.500 -0.1858 0.00982 0.00380 0.0017 0.8934 0.7150
-1.250 -0.1582 0.00972 0.00376 0.0021 0.8828 0.7378
-1.000 -0.1264 0.00963 0.00372 0.0016 0.8735 0.7587
-0.750 -0.0934 0.00955 0.00367 0.0009 0.8638 0.7782
-0.500 -0.0633 0.00951 0.00366 0.0008 0.8517 0.7957
-0.250 -0.0320 0.00948 0.00364 0.0005 0.8393 0.8118
0.000 0.0000 0.00947 0.00364 0.0000 0.8263 0.8263
0.250 0.0320 0.00948 0.00365 -0.0005 0.8118 0.8394
0.500 0.0633 0.00951 0.00366 -0.0008 0.7958 0.8516
0.750 0.0934 0.00955 0.00367 -0.0009 0.7782 0.8638
1.000 0.1264 0.00963 0.00372 -0.0016 0.7588 0.8735
1.250 0.1582 0.00972 0.00375 -0.0021 0.7379 0.8828
1.500 0.1857 0.00982 0.00380 -0.0017 0.7150 0.8935
1.750 0.2201 0.00997 0.00388 -0.0028 0.6899 0.8996
2.000 0.2462 0.01010 0.00393 -0.0021 0.6631 0.9096
2.250 0.2804 0.01030 0.00404 -0.0032 0.6322 0.9146
2.500 0.3078 0.01050 0.00413 -0.0029 0.6000 0.9228
2.750 0.3390 0.01074 0.00425 -0.0034 0.5651 0.9283
3.000 0.3705 0.01101 0.00438 -0.0041 0.5260 0.9339
3.250 0.3962 0.01129 0.00452 -0.0036 0.4870 0.9413
3.500 0.4289 0.01164 0.00470 -0.0047 0.4413 0.9452
3.750 0.4571 0.01202 0.00489 -0.0049 0.3957 0.9513
4.000 0.4847 0.01241 0.00511 -0.0050 0.3502 0.9572
4.250 0.5162 0.01284 0.00536 -0.0061 0.3040 0.9615
4.500 0.5433 0.01326 0.00562 -0.0062 0.2622 0.9678
4.750 0.5736 0.01373 0.00593 -0.0072 0.2213 0.9723
5.000 0.6044 0.01421 0.00624 -0.0082 0.1841 0.9768
5.250 0.6316 0.01470 0.00660 -0.0085 0.1535 0.9825
5.500 0.6639 0.01517 0.00697 -0.0099 0.1263 0.9859
5.750 0.6949 0.01565 0.00736 -0.0110 0.1053 0.9902
6.000 0.7250 0.01614 0.00780 -0.0119 0.0889 0.9943
6.250 0.7567 0.01662 0.00825 -0.0132 0.0759 0.9980
6.500 0.7816 0.01709 0.00871 -0.0131 0.0666 1.0000
6.750 0.7958 0.01755 0.00914 -0.0108 0.0602 1.0000
7.000 0.8107 0.01796 0.00960 -0.0085 0.0551 1.0000
7.250 0.8244 0.01846 0.01008 -0.0061 0.0505 1.0000
7.500 0.8380 0.01896 0.01064 -0.0035 0.0470 1.0000
7.750 0.8516 0.01946 0.01119 -0.0011 0.0439 1.0000
8.000 0.8634 0.02009 0.01181 0.0016 0.0410 1.0000
8.250 0.8762 0.02066 0.01244 0.0042 0.0387 1.0000
8.500 0.8891 0.02123 0.01308 0.0068 0.0365 1.0000
8.750 0.9014 0.02183 0.01372 0.0094 0.0345 1.0000
9.000 0.9105 0.02265 0.01452 0.0123 0.0330 1.0000
9.250 0.9224 0.02334 0.01532 0.0150 0.0318 1.0000
9.500 0.9334 0.02409 0.01617 0.0177 0.0306 1.0000
9.750 0.9439 0.02489 0.01703 0.0204 0.0296 1.0000
10.000 0.9538 0.02570 0.01791 0.0231 0.0287 1.0000
10.250 0.9613 0.02647 0.01874 0.0262 0.0279 1.0000
10.500 0.9669 0.02737 0.01966 0.0295 0.0271 1.0000
10.750 0.9726 0.02846 0.02082 0.0326 0.0264 1.0000
11.000 0.9806 0.02943 0.02194 0.0352 0.0256 1.0000
11.250 0.9881 0.03049 0.02313 0.0377 0.0249 1.0000
11.500 0.9948 0.03169 0.02445 0.0402 0.0243 1.0000
11.750 1.0009 0.03295 0.02582 0.0424 0.0238 1.0000
12.000 1.0062 0.03430 0.02731 0.0445 0.0233 1.0000
12.250 1.0106 0.03575 0.02885 0.0465 0.0228 1.0000
12.500 1.0143 0.03728 0.03048 0.0482 0.0224 1.0000
12.750 1.0171 0.03899 0.03228 0.0498 0.0221 1.0000
13.000 1.0186 0.04092 0.03431 0.0511 0.0218 1.0000
13.250 1.0178 0.04324 0.03672 0.0522 0.0215 1.0000
13.500 1.0135 0.04586 0.03958 0.0531 0.0212 1.0000
13.750 1.0075 0.04883 0.04277 0.0534 0.0210 1.0000
14.000 1.0003 0.05204 0.04620 0.0532 0.0206 1.0000
14.250 0.9899 0.05593 0.05031 0.0523 0.0204 1.0000
14.500 0.9776 0.06040 0.05498 0.0509 0.0203 1.0000
14.750 0.9632 0.06546 0.06024 0.0485 0.0201 1.0000
15.000 0.9444 0.07164 0.06663 0.0453 0.0201 1.0000
15.250 0.9232 0.07871 0.07391 0.0411 0.0200 1.0000
15.500 0.8962 0.08751 0.08292 0.0355 0.0200 1.0000
15.750 0.8544 0.10023 0.09587 0.0276 0.0203 1.0000
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