RG-12 (rg12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG-12 (rg12-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.36 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg12-il-1000000.txt Download as CSV file: xf-rg12-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RG-12
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5447 0.07940 0.07784 -0.0290 1.0000 0.0096
-9.250 -0.5539 0.07355 0.07202 -0.0327 1.0000 0.0097
-9.000 -0.5879 0.06207 0.06053 -0.0428 1.0000 0.0094
-8.750 -0.6406 0.05062 0.04888 -0.0433 1.0000 0.0090
-8.500 -0.6458 0.04818 0.04636 -0.0416 1.0000 0.0092
-7.500 -0.6721 0.02582 0.02239 -0.0311 0.9987 0.0084
-7.250 -0.6438 0.02340 0.01967 -0.0325 0.9969 0.0083
-7.000 -0.6159 0.02032 0.01630 -0.0337 0.9952 0.0078
-6.750 -0.5854 0.01824 0.01393 -0.0350 0.9939 0.0078
-5.750 -0.4625 0.01299 0.00798 -0.0387 0.9857 0.0081
-5.500 -0.4302 0.01164 0.00649 -0.0399 0.9842 0.0082
-5.250 -0.3975 0.01014 0.00478 -0.0413 0.9829 0.0093
-5.000 -0.3695 0.00962 0.00421 -0.0413 0.9786 0.0101
-4.750 -0.3369 0.00923 0.00378 -0.0424 0.9755 0.0111
-4.500 -0.3022 0.00887 0.00337 -0.0439 0.9733 0.0121
-4.250 -0.2667 0.00854 0.00300 -0.0456 0.9715 0.0131
-4.000 -0.2311 0.00797 0.00255 -0.0474 0.9700 0.0369
-3.750 -0.2044 0.00762 0.00230 -0.0472 0.9632 0.0613
-3.500 -0.1720 0.00729 0.00207 -0.0483 0.9590 0.0879
-3.250 -0.1413 0.00692 0.00186 -0.0490 0.9532 0.1310
-3.000 -0.1107 0.00655 0.00166 -0.0497 0.9456 0.1797
-2.750 -0.0807 0.00618 0.00149 -0.0504 0.9365 0.2417
-2.500 -0.0518 0.00565 0.00130 -0.0509 0.9258 0.3480
-2.250 -0.0242 0.00523 0.00116 -0.0510 0.9126 0.4420
-2.000 0.0022 0.00486 0.00104 -0.0508 0.8976 0.5368
-1.750 0.0268 0.00445 0.00099 -0.0502 0.8813 0.6624
-1.500 0.0532 0.00439 0.00098 -0.0497 0.8645 0.7099
-1.250 0.0801 0.00440 0.00096 -0.0493 0.8469 0.7342
-1.000 0.1069 0.00443 0.00095 -0.0489 0.8287 0.7509
-0.750 0.1336 0.00448 0.00094 -0.0485 0.8091 0.7646
-0.500 0.1601 0.00455 0.00094 -0.0481 0.7894 0.7769
-0.250 0.1868 0.00461 0.00094 -0.0477 0.7687 0.7874
0.000 0.2131 0.00469 0.00095 -0.0473 0.7479 0.7963
0.250 0.2398 0.00477 0.00096 -0.0469 0.7259 0.8049
0.500 0.2662 0.00485 0.00099 -0.0465 0.7039 0.8133
0.750 0.2925 0.00495 0.00101 -0.0461 0.6808 0.8211
1.000 0.3190 0.00505 0.00105 -0.0458 0.6571 0.8286
1.250 0.3453 0.00515 0.00109 -0.0454 0.6331 0.8353
1.500 0.3715 0.00528 0.00114 -0.0450 0.6076 0.8432
1.750 0.3975 0.00540 0.00119 -0.0445 0.5820 0.8508
2.000 0.4238 0.00554 0.00125 -0.0442 0.5561 0.8588
2.250 0.4495 0.00566 0.00133 -0.0437 0.5299 0.8664
2.500 0.4755 0.00581 0.00141 -0.0433 0.5034 0.8744
2.750 0.5010 0.00596 0.00150 -0.0428 0.4751 0.8818
3.000 0.5267 0.00614 0.00159 -0.0424 0.4450 0.8888
3.250 0.5521 0.00632 0.00170 -0.0419 0.4160 0.8954
3.500 0.5777 0.00651 0.00182 -0.0415 0.3871 0.9025
3.750 0.6025 0.00672 0.00194 -0.0409 0.3564 0.9103
4.000 0.6272 0.00691 0.00207 -0.0403 0.3294 0.9190
4.250 0.6514 0.00713 0.00222 -0.0396 0.3007 0.9296
4.750 0.6973 0.00769 0.00258 -0.0377 0.2283 0.9596
5.000 0.7264 0.00806 0.00280 -0.0382 0.1903 0.9772
5.250 0.7599 0.00844 0.00305 -0.0398 0.1569 0.9937
5.500 0.7871 0.00882 0.00330 -0.0400 0.1296 1.0000
5.750 0.8117 0.00920 0.00359 -0.0396 0.1066 1.0000
6.000 0.8360 0.00960 0.00389 -0.0391 0.0847 1.0000
6.250 0.8601 0.01004 0.00421 -0.0386 0.0634 1.0000
6.500 0.8841 0.01048 0.00455 -0.0381 0.0459 1.0000
6.750 0.9081 0.01092 0.00492 -0.0376 0.0326 1.0000
7.000 0.9320 0.01136 0.00532 -0.0370 0.0231 1.0000
7.250 0.9558 0.01183 0.00579 -0.0364 0.0173 1.0000
7.500 0.9800 0.01222 0.00619 -0.0359 0.0146 1.0000
7.750 1.0031 0.01275 0.00675 -0.0351 0.0116 1.0000
8.000 1.0261 0.01327 0.00727 -0.0345 0.0090 1.0000
8.250 1.0476 0.01397 0.00805 -0.0334 0.0074 1.0000
8.500 1.0704 0.01449 0.00863 -0.0327 0.0065 1.0000
8.750 1.0923 0.01508 0.00929 -0.0318 0.0058 1.0000
9.000 1.1121 0.01590 0.01020 -0.0306 0.0052 1.0000
9.250 1.1266 0.01726 0.01173 -0.0285 0.0047 1.0000
9.500 1.1397 0.01871 0.01335 -0.0264 0.0044 1.0000
9.750 1.1596 0.01937 0.01409 -0.0253 0.0043 1.0000
10.000 1.1767 0.02030 0.01512 -0.0238 0.0043 1.0000
10.250 1.1916 0.02141 0.01636 -0.0221 0.0042 1.0000
10.500 1.2056 0.02254 0.01761 -0.0202 0.0041 1.0000
10.750 1.2175 0.02380 0.01901 -0.0182 0.0041 1.0000
11.000 1.2276 0.02506 0.02041 -0.0158 0.0040 1.0000
11.250 1.2324 0.02644 0.02193 -0.0127 0.0039 1.0000
11.500 1.2344 0.02800 0.02366 -0.0094 0.0039 1.0000
11.750 1.2360 0.02956 0.02538 -0.0064 0.0038 1.0000
12.000 1.2338 0.03151 0.02750 -0.0034 0.0038 1.0000
12.250 1.2334 0.03330 0.02943 -0.0010 0.0037 1.0000
12.500 1.2292 0.03555 0.03184 0.0011 0.0037 1.0000
12.750 1.2235 0.03810 0.03456 0.0028 0.0036 1.0000
13.000 1.2152 0.04118 0.03780 0.0038 0.0036 1.0000
13.250 1.1990 0.04551 0.04235 0.0040 0.0036 1.0000
13.500 1.1894 0.04945 0.04644 0.0032 0.0036 1.0000
13.750 1.1673 0.05567 0.05288 0.0010 0.0037 1.0000
14.000 1.1605 0.06012 0.05745 -0.0012 0.0036 1.0000
14.250 1.1439 0.06668 0.06416 -0.0049 0.0036 1.0000
14.500 1.1266 0.07393 0.07157 -0.0093 0.0036 1.0000
14.750 1.1064 0.08228 0.08007 -0.0145 0.0036 1.0000
15.000 1.0854 0.09140 0.08933 -0.0202 0.0036 1.0000
15.250 1.0592 0.10228 0.10035 -0.0269 0.0037 1.0000
15.500 1.0252 0.11568 0.11392 -0.0349 0.0038 1.0000
15.750 0.9922 0.12982 0.12817 -0.0430 0.0040 1.0000
16.000 0.9271 0.15507 0.15357 -0.0564 0.0042 1.0000
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Polar data table (+)
Polar graphs
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