RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Reynolds number: 500,000 Max Cl/Cd: 74.69 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg12a189-il-500000-n5.txt Download as CSV file: xf-rg12a189-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5100 0.08506 0.08278 -0.0266 1.0000 0.0049
-9.250 -0.5184 0.07968 0.07743 -0.0290 1.0000 0.0048
-9.000 -0.5302 0.07397 0.07177 -0.0320 1.0000 0.0047
-8.750 -0.5478 0.06801 0.06587 -0.0362 1.0000 0.0048
-8.500 -0.5752 0.06112 0.05895 -0.0395 1.0000 0.0046
-8.250 -0.5927 0.05438 0.05209 -0.0407 1.0000 0.0045
-8.000 -0.6095 0.04684 0.04434 -0.0401 1.0000 0.0045
-7.750 -0.6301 0.03594 0.03291 -0.0383 0.9997 0.0046
-7.500 -0.6155 0.02703 0.02314 -0.0407 0.9960 0.0047
-7.250 -0.5907 0.02316 0.01872 -0.0419 0.9936 0.0048
-7.000 -0.5630 0.02159 0.01688 -0.0428 0.9910 0.0052
-6.750 -0.5343 0.01982 0.01480 -0.0436 0.9884 0.0056
-6.500 -0.5044 0.01803 0.01268 -0.0446 0.9861 0.0058
-6.250 -0.4734 0.01645 0.01083 -0.0456 0.9842 0.0059
-6.000 -0.4444 0.01524 0.00944 -0.0461 0.9814 0.0060
-5.750 -0.4164 0.01423 0.00825 -0.0463 0.9776 0.0061
-5.500 -0.3857 0.01338 0.00728 -0.0471 0.9744 0.0064
-5.250 -0.3541 0.01235 0.00614 -0.0482 0.9719 0.0068
-5.000 -0.3247 0.01173 0.00547 -0.0487 0.9679 0.0075
-4.750 -0.2958 0.01123 0.00492 -0.0490 0.9629 0.0082
-4.500 -0.2634 0.01078 0.00439 -0.0500 0.9595 0.0093
-4.250 -0.2325 0.01032 0.00388 -0.0508 0.9553 0.0114
-4.000 -0.2035 0.00993 0.00346 -0.0510 0.9488 0.0140
-3.750 -0.1690 0.00952 0.00304 -0.0524 0.9447 0.0202
-3.500 -0.1387 0.00913 0.00272 -0.0530 0.9372 0.0401
-3.250 -0.1043 0.00873 0.00245 -0.0546 0.9310 0.0707
-3.000 -0.0722 0.00839 0.00222 -0.0556 0.9217 0.1060
-2.750 -0.0390 0.00798 0.00199 -0.0570 0.9115 0.1620
-2.500 -0.0072 0.00754 0.00178 -0.0581 0.8988 0.2375
-2.250 0.0231 0.00717 0.00160 -0.0587 0.8829 0.3119
-2.000 0.0519 0.00686 0.00145 -0.0591 0.8646 0.3850
-1.750 0.0790 0.00653 0.00131 -0.0590 0.8445 0.4722
-1.500 0.1029 0.00599 0.00125 -0.0583 0.8225 0.6290
-1.250 0.1280 0.00591 0.00129 -0.0575 0.8000 0.7074
-1.000 0.1542 0.00596 0.00128 -0.0570 0.7765 0.7341
-0.750 0.1802 0.00603 0.00128 -0.0564 0.7531 0.7537
-0.500 0.2062 0.00612 0.00128 -0.0558 0.7298 0.7692
-0.250 0.2321 0.00622 0.00129 -0.0553 0.7067 0.7821
0.000 0.2580 0.00632 0.00131 -0.0547 0.6844 0.7934
0.250 0.2839 0.00643 0.00133 -0.0542 0.6625 0.8044
0.500 0.3099 0.00653 0.00137 -0.0537 0.6408 0.8152
1.000 0.3609 0.00674 0.00147 -0.0525 0.5978 0.8374
1.250 0.3865 0.00686 0.00153 -0.0519 0.5762 0.8473
1.500 0.4123 0.00698 0.00159 -0.0514 0.5531 0.8543
1.750 0.4385 0.00712 0.00165 -0.0511 0.5304 0.8599
2.000 0.4641 0.00726 0.00172 -0.0506 0.5069 0.8646
2.250 0.4901 0.00741 0.00181 -0.0503 0.4834 0.8699
2.500 0.5159 0.00757 0.00190 -0.0498 0.4585 0.8752
2.750 0.5412 0.00775 0.00200 -0.0493 0.4334 0.8808
3.000 0.5667 0.00795 0.00212 -0.0489 0.4063 0.8869
3.250 0.5915 0.00814 0.00226 -0.0483 0.3800 0.8934
3.500 0.6167 0.00835 0.00241 -0.0478 0.3543 0.9010
3.750 0.6408 0.00858 0.00256 -0.0471 0.3257 0.9089
4.750 0.7379 0.00991 0.00343 -0.0448 0.1837 0.9613
5.000 0.7685 0.01035 0.00372 -0.0457 0.1470 0.9855
5.250 0.7944 0.01081 0.00405 -0.0457 0.1171 1.0000
5.500 0.8183 0.01130 0.00440 -0.0453 0.0889 1.0000
5.750 0.8427 0.01174 0.00475 -0.0449 0.0688 1.0000
6.000 0.8668 0.01220 0.00514 -0.0444 0.0520 1.0000
6.250 0.8907 0.01268 0.00556 -0.0439 0.0362 1.0000
6.500 0.9138 0.01324 0.00607 -0.0433 0.0227 1.0000
6.750 0.9377 0.01372 0.00655 -0.0427 0.0181 1.0000
7.000 0.9610 0.01425 0.00712 -0.0420 0.0153 1.0000
7.250 0.9848 0.01471 0.00764 -0.0415 0.0143 1.0000
7.500 1.0082 0.01521 0.00822 -0.0408 0.0136 1.0000
7.750 1.0310 0.01576 0.00887 -0.0401 0.0130 1.0000
8.000 1.0532 0.01635 0.00954 -0.0393 0.0124 1.0000
8.250 1.0747 0.01700 0.01027 -0.0384 0.0118 1.0000
8.500 1.0954 0.01770 0.01104 -0.0375 0.0112 1.0000
8.750 1.1133 0.01868 0.01212 -0.0361 0.0103 1.0000
9.000 1.1298 0.01978 0.01334 -0.0345 0.0098 1.0000
9.250 1.1500 0.02044 0.01410 -0.0335 0.0095 1.0000
9.500 1.1699 0.02110 0.01487 -0.0325 0.0090 1.0000
9.750 1.1885 0.02184 0.01572 -0.0314 0.0084 1.0000
10.000 1.2060 0.02265 0.01662 -0.0301 0.0079 1.0000
10.250 1.2222 0.02354 0.01761 -0.0286 0.0075 1.0000
10.500 1.2372 0.02445 0.01861 -0.0271 0.0071 1.0000
10.750 1.2496 0.02544 0.01969 -0.0252 0.0067 1.0000
11.000 1.2530 0.02696 0.02134 -0.0220 0.0064 1.0000
11.250 1.2594 0.02825 0.02276 -0.0194 0.0061 1.0000
11.500 1.2681 0.02935 0.02400 -0.0172 0.0059 1.0000
11.750 1.2788 0.03026 0.02504 -0.0154 0.0055 1.0000
12.000 1.2838 0.03168 0.02663 -0.0133 0.0052 1.0000
12.250 1.2925 0.03276 0.02783 -0.0118 0.0049 1.0000
12.500 1.2951 0.03447 0.02967 -0.0099 0.0047 1.0000
12.750 1.3004 0.03598 0.03128 -0.0087 0.0044 1.0000
13.000 1.3027 0.03787 0.03329 -0.0076 0.0043 1.0000
13.250 1.3037 0.04005 0.03559 -0.0069 0.0041 1.0000
13.500 1.3008 0.04281 0.03850 -0.0065 0.0041 1.0000
13.750 1.2976 0.04586 0.04167 -0.0067 0.0039 1.0000
14.000 1.2880 0.05000 0.04595 -0.0076 0.0038 1.0000
14.250 1.2757 0.05491 0.05104 -0.0093 0.0038 1.0000
14.500 1.2667 0.05976 0.05606 -0.0114 0.0037 1.0000
14.750 1.2511 0.06602 0.06250 -0.0144 0.0037 1.0000
15.000 1.2368 0.07244 0.06909 -0.0179 0.0037 1.0000
15.250 1.2212 0.07952 0.07634 -0.0219 0.0037 1.0000
15.500 1.2014 0.08772 0.08470 -0.0266 0.0036 1.0000
15.750 1.1817 0.09632 0.09346 -0.0316 0.0037 1.0000
16.000 1.1596 0.10579 0.10307 -0.0371 0.0037 1.0000
16.250 1.1409 0.11496 0.11238 -0.0425 0.0036 1.0000
16.500 1.1179 0.12529 0.12283 -0.0484 0.0037 1.0000
16.750 1.0971 0.13553 0.13318 -0.0543 0.0037 1.0000
17.000 1.0746 0.14677 0.14458 -0.0607 0.0039 1.0000
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