RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.52 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg12a189-il-1000000-n5.txt Download as CSV file: xf-rg12a189-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 12A-1.8/9.0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5252 0.08882 0.08718 -0.0240 1.0000 0.0029
-9.750 -0.5353 0.08290 0.08128 -0.0267 1.0000 0.0027
-8.750 -0.7118 0.02602 0.02300 -0.0466 0.9957 0.0029
-8.500 -0.6888 0.02241 0.01894 -0.0481 0.9938 0.0030
-8.250 -0.6648 0.02027 0.01649 -0.0486 0.9914 0.0031
-8.000 -0.6388 0.01846 0.01441 -0.0492 0.9892 0.0032
-7.750 -0.6109 0.01698 0.01269 -0.0500 0.9873 0.0033
-7.500 -0.5816 0.01573 0.01124 -0.0509 0.9857 0.0034
-7.250 -0.5514 0.01448 0.00977 -0.0519 0.9844 0.0034
-7.000 -0.5199 0.01361 0.00877 -0.0530 0.9833 0.0035
-6.750 -0.4959 0.01302 0.00809 -0.0524 0.9792 0.0036
-6.500 -0.4669 0.01252 0.00751 -0.0529 0.9763 0.0038
-6.250 -0.4369 0.01175 0.00663 -0.0536 0.9738 0.0039
-6.000 -0.4061 0.01083 0.00559 -0.0545 0.9718 0.0041
-5.750 -0.3779 0.01023 0.00490 -0.0547 0.9682 0.0044
-5.500 -0.3511 0.00977 0.00439 -0.0546 0.9629 0.0047
-5.250 -0.3194 0.00937 0.00396 -0.0555 0.9594 0.0050
-5.000 -0.2885 0.00902 0.00357 -0.0562 0.9549 0.0056
-4.750 -0.2577 0.00870 0.00321 -0.0569 0.9484 0.0061
-4.500 -0.2240 0.00837 0.00283 -0.0582 0.9423 0.0068
-4.250 -0.1915 0.00807 0.00250 -0.0592 0.9330 0.0083
-4.000 -0.1593 0.00784 0.00223 -0.0602 0.9210 0.0106
-3.750 -0.1290 0.00762 0.00197 -0.0607 0.9058 0.0149
-3.500 -0.1008 0.00740 0.00174 -0.0608 0.8882 0.0282
-3.250 -0.0737 0.00725 0.00158 -0.0606 0.8682 0.0427
-3.000 -0.0475 0.00710 0.00143 -0.0602 0.8468 0.0628
-2.750 -0.0217 0.00694 0.00130 -0.0598 0.8242 0.0954
-2.500 0.0038 0.00680 0.00117 -0.0594 0.8005 0.1307
-2.250 0.0293 0.00668 0.00108 -0.0590 0.7763 0.1677
-2.000 0.0547 0.00650 0.00099 -0.0586 0.7523 0.2253
-1.750 0.0803 0.00635 0.00092 -0.0582 0.7290 0.2807
-1.500 0.1061 0.00624 0.00085 -0.0579 0.7062 0.3290
-1.250 0.1320 0.00608 0.00080 -0.0576 0.6845 0.3930
-1.000 0.1574 0.00580 0.00075 -0.0573 0.6636 0.4961
-0.750 0.1824 0.00546 0.00073 -0.0569 0.6429 0.6189
-0.500 0.2083 0.00538 0.00076 -0.0566 0.6222 0.6874
-0.250 0.2350 0.00543 0.00079 -0.0563 0.6020 0.7172
0.000 0.2619 0.00550 0.00082 -0.0560 0.5814 0.7350
0.250 0.2888 0.00558 0.00086 -0.0558 0.5614 0.7487
0.500 0.3158 0.00568 0.00089 -0.0556 0.5407 0.7603
0.750 0.3426 0.00578 0.00094 -0.0554 0.5191 0.7703
1.000 0.3694 0.00589 0.00099 -0.0551 0.4970 0.7799
1.250 0.3963 0.00602 0.00105 -0.0549 0.4753 0.7892
1.500 0.4229 0.00614 0.00112 -0.0547 0.4532 0.7997
1.750 0.4494 0.00626 0.00120 -0.0544 0.4311 0.8106
2.000 0.4759 0.00642 0.00128 -0.0541 0.4073 0.8191
2.250 0.5024 0.00657 0.00138 -0.0539 0.3833 0.8249
2.500 0.5290 0.00676 0.00147 -0.0537 0.3574 0.8294
2.750 0.5555 0.00693 0.00157 -0.0534 0.3350 0.8333
3.000 0.5818 0.00712 0.00170 -0.0532 0.3102 0.8378
3.250 0.6080 0.00734 0.00183 -0.0529 0.2837 0.8425
3.500 0.6337 0.00760 0.00198 -0.0526 0.2541 0.8469
3.750 0.6590 0.00789 0.00215 -0.0522 0.2200 0.8521
4.000 0.6830 0.00834 0.00239 -0.0517 0.1711 0.8580
4.250 0.7079 0.00866 0.00261 -0.0512 0.1414 0.8636
4.500 0.7333 0.00894 0.00281 -0.0508 0.1196 0.8699
4.750 0.7584 0.00923 0.00304 -0.0504 0.0997 0.8763
5.000 0.7830 0.00954 0.00329 -0.0499 0.0795 0.8838
5.250 0.8071 0.00988 0.00358 -0.0493 0.0587 0.8924
5.500 0.8311 0.01021 0.00386 -0.0486 0.0434 0.9026
5.750 0.8544 0.01054 0.00416 -0.0478 0.0300 0.9151
6.000 0.8765 0.01089 0.00450 -0.0467 0.0184 0.9311
6.250 0.8995 0.01115 0.00480 -0.0458 0.0141 0.9554
6.500 0.9299 0.01147 0.00515 -0.0466 0.0124 1.0000
6.750 0.9549 0.01182 0.00553 -0.0462 0.0112 1.0000
7.000 0.9796 0.01222 0.00597 -0.0457 0.0104 1.0000
7.250 1.0038 0.01265 0.00645 -0.0452 0.0098 1.0000
7.500 1.0284 0.01302 0.00687 -0.0447 0.0097 1.0000
7.750 1.0526 0.01342 0.00734 -0.0442 0.0095 1.0000
8.000 1.0767 0.01380 0.00777 -0.0438 0.0091 1.0000
8.250 1.1004 0.01422 0.00824 -0.0432 0.0087 1.0000
8.500 1.1241 0.01463 0.00869 -0.0427 0.0082 1.0000
8.750 1.1473 0.01507 0.00916 -0.0421 0.0077 1.0000
9.000 1.1699 0.01556 0.00969 -0.0414 0.0073 1.0000
9.250 1.1914 0.01616 0.01036 -0.0406 0.0068 1.0000
9.500 1.2097 0.01706 0.01137 -0.0392 0.0063 1.0000
9.750 1.2320 0.01750 0.01186 -0.0385 0.0061 1.0000
10.000 1.2542 0.01792 0.01234 -0.0379 0.0059 1.0000
10.250 1.2759 0.01838 0.01284 -0.0371 0.0055 1.0000
10.500 1.2970 0.01886 0.01338 -0.0363 0.0052 1.0000
10.750 1.3175 0.01937 0.01394 -0.0354 0.0048 1.0000
11.000 1.3370 0.01994 0.01456 -0.0344 0.0045 1.0000
11.250 1.3563 0.02050 0.01516 -0.0333 0.0042 1.0000
11.500 1.3727 0.02126 0.01599 -0.0319 0.0038 1.0000
11.750 1.3889 0.02199 0.01679 -0.0304 0.0036 1.0000
12.000 1.4034 0.02271 0.01761 -0.0287 0.0034 1.0000
12.250 1.4154 0.02344 0.01842 -0.0265 0.0033 1.0000
12.500 1.4258 0.02424 0.01930 -0.0242 0.0031 1.0000
12.750 1.4362 0.02505 0.02018 -0.0220 0.0028 1.0000
13.000 1.4451 0.02597 0.02118 -0.0198 0.0027 1.0000
13.250 1.4533 0.02696 0.02224 -0.0176 0.0025 1.0000
13.500 1.4585 0.02819 0.02356 -0.0153 0.0024 1.0000
13.750 1.4616 0.02964 0.02512 -0.0131 0.0022 1.0000
14.000 1.4619 0.03138 0.02698 -0.0110 0.0021 1.0000
14.250 1.4620 0.03326 0.02899 -0.0093 0.0020 1.0000
14.500 1.4628 0.03522 0.03107 -0.0080 0.0020 1.0000
14.750 1.4592 0.03777 0.03375 -0.0070 0.0019 1.0000
15.000 1.4567 0.04044 0.03654 -0.0066 0.0019 1.0000
15.250 1.4514 0.04366 0.03990 -0.0066 0.0018 1.0000
15.500 1.4447 0.04733 0.04371 -0.0073 0.0018 1.0000
15.750 1.4365 0.05151 0.04803 -0.0085 0.0018 1.0000
16.000 1.4237 0.05669 0.05337 -0.0106 0.0018 1.0000
16.250 1.4093 0.06254 0.05936 -0.0133 0.0017 1.0000
16.500 1.3957 0.06859 0.06555 -0.0164 0.0017 1.0000
16.750 1.3744 0.07636 0.07349 -0.0207 0.0017 1.0000
17.000 1.3557 0.08408 0.08134 -0.0250 0.0017 1.0000
17.250 1.3208 0.09543 0.09289 -0.0316 0.0017 1.0000
17.500 1.2889 0.10667 0.10429 -0.0381 0.0018 1.0000
17.750 1.2568 0.11842 0.11619 -0.0449 0.0018 1.0000
18.000 1.2202 0.13160 0.12953 -0.0527 0.0019 1.0000
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Polar data table (+)
Polar graphs
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