RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Reynolds number: 100,000 Max Cl/Cd: 50.76 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg12a189-il-100000.txt Download as CSV file: xf-rg12a189-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3848 0.09295 0.08825 -0.0264 1.0000 0.1037
-9.000 -0.4789 0.09751 0.09256 -0.0245 1.0000 0.0952
-8.750 -0.4729 0.09438 0.08945 -0.0240 1.0000 0.0985
-8.500 -0.4776 0.09103 0.08618 -0.0256 1.0000 0.1025
-8.250 -0.5008 0.08769 0.08297 -0.0303 1.0000 0.1049
-8.000 -0.5341 0.08411 0.07939 -0.0369 1.0000 0.1058
-7.750 -0.5065 0.07973 0.07514 -0.0308 1.0000 0.1091
-7.500 -0.5029 0.07684 0.07228 -0.0299 1.0000 0.1144
-7.250 -0.5322 0.07317 0.06843 -0.0366 1.0000 0.1195
-7.000 -0.4805 0.05844 0.05411 -0.0350 1.0000 0.1336
-6.750 -0.4532 0.05497 0.05084 -0.0298 1.0000 0.1418
-6.250 -0.4632 0.04739 0.04325 -0.0291 1.0000 0.1553
-6.000 -0.4686 0.04340 0.03918 -0.0291 1.0000 0.1652
-5.750 -0.4693 0.03998 0.03564 -0.0288 1.0000 0.1779
-5.500 -0.4778 0.03980 0.03324 -0.0344 1.0000 0.0800
-5.250 -0.4575 0.03448 0.02742 -0.0329 1.0000 0.0626
-5.000 -0.4381 0.03064 0.02311 -0.0317 1.0000 0.0579
-4.750 -0.4150 0.02727 0.01892 -0.0302 1.0000 0.0544
-4.500 -0.3918 0.02499 0.01627 -0.0290 1.0000 0.0543
-4.250 -0.3689 0.02307 0.01417 -0.0279 1.0000 0.0566
-4.000 -0.3458 0.02188 0.01275 -0.0268 1.0000 0.0632
-3.750 -0.3220 0.02011 0.01089 -0.0257 1.0000 0.0680
-3.500 -0.2987 0.01895 0.00967 -0.0245 1.0000 0.0784
-3.250 -0.2763 0.01751 0.00846 -0.0236 1.0000 0.1034
-3.000 -0.2543 0.01582 0.00735 -0.0228 1.0000 0.1860
-2.750 -0.2420 0.01316 0.00707 -0.0202 1.0000 0.5937
-2.500 -0.2404 0.01319 0.00759 -0.0128 1.0000 0.8006
-2.250 -0.2357 0.01331 0.00772 -0.0067 1.0000 0.8707
-2.000 -0.2138 0.01345 0.00777 -0.0038 1.0000 0.9419
-1.750 -0.0928 0.01387 0.00757 -0.0204 1.0000 1.0000
-1.500 -0.0979 0.01372 0.00737 -0.0160 1.0000 1.0000
-1.250 -0.0995 0.01364 0.00720 -0.0123 1.0000 1.0000
-1.000 -0.0908 0.01369 0.00713 -0.0103 1.0000 1.0000
-0.750 -0.0760 0.01386 0.00717 -0.0094 1.0000 1.0000
-0.500 -0.0336 0.01432 0.00744 -0.0135 0.9925 1.0000
-0.250 0.0183 0.01479 0.00776 -0.0190 0.9814 1.0000
0.000 0.0706 0.01515 0.00801 -0.0245 0.9703 1.0000
0.250 0.1194 0.01535 0.00811 -0.0291 0.9577 1.0000
0.500 0.1674 0.01545 0.00816 -0.0334 0.9447 1.0000
0.750 0.2148 0.01547 0.00815 -0.0374 0.9316 1.0000
1.000 0.2623 0.01541 0.00808 -0.0413 0.9183 1.0000
1.250 0.3106 0.01525 0.00794 -0.0451 0.9052 1.0000
1.500 0.3608 0.01498 0.00773 -0.0490 0.8922 1.0000
1.750 0.4078 0.01466 0.00746 -0.0521 0.8781 1.0000
2.000 0.4528 0.01431 0.00716 -0.0547 0.8624 1.0000
2.250 0.4958 0.01396 0.00689 -0.0568 0.8453 1.0000
2.500 0.5261 0.01382 0.00677 -0.0566 0.8222 1.0000
2.750 0.5581 0.01367 0.00664 -0.0566 0.7992 1.0000
3.000 0.5882 0.01360 0.00654 -0.0562 0.7748 1.0000
3.250 0.6137 0.01365 0.00661 -0.0551 0.7475 1.0000
3.500 0.6387 0.01376 0.00668 -0.0539 0.7194 1.0000
3.750 0.6631 0.01393 0.00679 -0.0526 0.6905 1.0000
4.000 0.6866 0.01414 0.00695 -0.0512 0.6602 1.0000
4.250 0.7091 0.01439 0.00720 -0.0497 0.6280 1.0000
4.500 0.7316 0.01466 0.00742 -0.0483 0.5951 1.0000
4.750 0.7541 0.01497 0.00763 -0.0468 0.5618 1.0000
5.000 0.7753 0.01530 0.00794 -0.0452 0.5251 1.0000
5.250 0.7964 0.01569 0.00828 -0.0437 0.4878 1.0000
5.500 0.8168 0.01612 0.00861 -0.0420 0.4486 1.0000
5.750 0.8362 0.01662 0.00902 -0.0403 0.4059 1.0000
6.000 0.8549 0.01720 0.00951 -0.0386 0.3602 1.0000
6.250 0.8725 0.01792 0.01008 -0.0368 0.3112 1.0000
6.500 0.8882 0.01876 0.01074 -0.0348 0.2556 1.0000
6.750 0.9024 0.01982 0.01147 -0.0329 0.1968 1.0000
7.000 0.9157 0.02132 0.01264 -0.0309 0.1424 1.0000
7.250 0.9272 0.02342 0.01438 -0.0285 0.1018 1.0000
7.500 0.9434 0.02522 0.01613 -0.0267 0.0797 1.0000
7.750 0.9632 0.02725 0.01815 -0.0253 0.0694 1.0000
8.000 0.9871 0.03001 0.02074 -0.0249 0.0629 1.0000
8.250 1.0110 0.03208 0.02322 -0.0238 0.0592 1.0000
8.500 1.0314 0.03401 0.02534 -0.0228 0.0544 1.0000
8.750 1.0533 0.03746 0.02888 -0.0224 0.0515 1.0000
9.000 1.0695 0.04129 0.03312 -0.0210 0.0507 1.0000
9.250 1.0804 0.04472 0.03708 -0.0188 0.0503 1.0000
9.500 1.0870 0.04854 0.04139 -0.0166 0.0502 1.0000
9.750 1.0880 0.05215 0.04549 -0.0140 0.0498 1.0000
10.000 1.0839 0.05580 0.04959 -0.0113 0.0493 1.0000
10.250 1.0753 0.05961 0.05378 -0.0087 0.0491 1.0000
10.500 1.0611 0.06337 0.05785 -0.0061 0.0491 1.0000
10.750 1.0442 0.06714 0.06184 -0.0036 0.0494 1.0000
11.000 1.0247 0.07128 0.06616 -0.0023 0.0497 1.0000
11.250 1.0080 0.07608 0.07109 -0.0023 0.0502 1.0000
11.500 0.8349 0.08333 0.07913 -0.0069 0.0575 1.0000
11.750 0.7965 0.09417 0.09005 -0.0137 0.0591 1.0000
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Polar data table (+)
Polar graphs
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