RG-12 (rg12-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG-12 (rg12-il) Reynolds number: 50,000 Max Cl/Cd: 34.36 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg12-il-50000-n5.txt Download as CSV file: xf-rg12-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5414 0.08101 0.07399 -0.0389 1.0000 0.0395
-8.750 -0.5510 0.07687 0.06988 -0.0400 1.0000 0.0392
-8.500 -0.5603 0.07301 0.06603 -0.0404 1.0000 0.0390
-8.250 -0.5680 0.06903 0.06200 -0.0407 1.0000 0.0387
-8.000 -0.5747 0.06502 0.05790 -0.0406 1.0000 0.0385
-7.750 -0.5798 0.06094 0.05367 -0.0401 1.0000 0.0384
-7.500 -0.5819 0.05696 0.04947 -0.0394 1.0000 0.0383
-7.250 -0.5808 0.05307 0.04530 -0.0384 1.0000 0.0382
-7.000 -0.5768 0.04920 0.04107 -0.0372 1.0000 0.0383
-6.750 -0.5694 0.04547 0.03691 -0.0358 1.0000 0.0385
-6.500 -0.5587 0.04200 0.03295 -0.0344 1.0000 0.0389
-6.250 -0.5446 0.03881 0.02922 -0.0329 1.0000 0.0394
-6.000 -0.5295 0.03606 0.02630 -0.0317 1.0000 0.0414
-5.750 -0.5121 0.03418 0.02422 -0.0305 1.0000 0.0450
-5.500 -0.4924 0.03205 0.02167 -0.0292 1.0000 0.0493
-5.250 -0.4710 0.02981 0.01904 -0.0277 1.0000 0.0525
-5.000 -0.4506 0.02805 0.01723 -0.0264 1.0000 0.0573
-4.750 -0.4296 0.02663 0.01559 -0.0250 1.0000 0.0675
-4.500 -0.4084 0.02521 0.01403 -0.0235 1.0000 0.0791
-4.250 -0.3884 0.02401 0.01288 -0.0222 1.0000 0.0990
-4.000 -0.3681 0.02277 0.01168 -0.0209 1.0000 0.1260
-3.750 -0.3479 0.02150 0.01060 -0.0199 1.0000 0.1686
-3.500 -0.3299 0.02024 0.00976 -0.0187 1.0000 0.2418
-3.250 -0.3139 0.01888 0.00914 -0.0172 1.0000 0.3719
-3.000 -0.3035 0.01778 0.00907 -0.0132 1.0000 0.5659
-2.750 -0.2937 0.01771 0.00941 -0.0077 1.0000 0.7267
-2.500 -0.2807 0.01779 0.00946 -0.0034 1.0000 0.8099
-2.250 -0.2598 0.01789 0.00944 -0.0005 1.0000 0.8756
-2.000 -0.2068 0.01809 0.00931 -0.0039 1.0000 0.9374
-1.750 -0.1192 0.01821 0.00887 -0.0150 1.0000 0.9824
-1.500 -0.0769 0.01810 0.00850 -0.0188 1.0000 1.0000
-1.250 -0.0762 0.01798 0.00830 -0.0152 1.0000 1.0000
-1.000 -0.0745 0.01791 0.00814 -0.0117 1.0000 1.0000
-0.750 -0.0702 0.01790 0.00802 -0.0088 1.0000 1.0000
-0.500 -0.0409 0.01811 0.00803 -0.0103 0.9932 1.0000
-0.250 0.0023 0.01838 0.00815 -0.0143 0.9809 1.0000
0.000 0.0440 0.01861 0.00825 -0.0179 0.9679 1.0000
0.250 0.0845 0.01880 0.00833 -0.0211 0.9543 1.0000
0.500 0.1243 0.01895 0.00841 -0.0240 0.9402 1.0000
0.750 0.1637 0.01906 0.00848 -0.0267 0.9258 1.0000
1.000 0.2030 0.01915 0.00854 -0.0292 0.9110 1.0000
1.250 0.2424 0.01919 0.00859 -0.0316 0.8961 1.0000
1.500 0.2823 0.01919 0.00863 -0.0340 0.8807 1.0000
1.750 0.3204 0.01918 0.00867 -0.0358 0.8646 1.0000
2.000 0.3580 0.01913 0.00868 -0.0374 0.8479 1.0000
2.250 0.3921 0.01910 0.00870 -0.0383 0.8293 1.0000
2.500 0.4239 0.01908 0.00879 -0.0386 0.8091 1.0000
2.750 0.4574 0.01902 0.00880 -0.0391 0.7890 1.0000
3.000 0.4864 0.01904 0.00889 -0.0388 0.7659 1.0000
3.250 0.5149 0.01908 0.00898 -0.0383 0.7418 1.0000
3.500 0.5433 0.01913 0.00914 -0.0377 0.7167 1.0000
3.750 0.5705 0.01923 0.00929 -0.0370 0.6899 1.0000
4.000 0.5963 0.01938 0.00948 -0.0360 0.6614 1.0000
4.250 0.6211 0.01958 0.00972 -0.0348 0.6312 1.0000
4.500 0.6452 0.01982 0.00998 -0.0336 0.5994 1.0000
4.750 0.6689 0.02010 0.01032 -0.0322 0.5667 1.0000
5.000 0.6908 0.02047 0.01071 -0.0307 0.5312 1.0000
5.250 0.7125 0.02088 0.01110 -0.0292 0.4950 1.0000
5.500 0.7331 0.02136 0.01156 -0.0276 0.4569 1.0000
5.750 0.7528 0.02191 0.01209 -0.0260 0.4169 1.0000
6.000 0.7716 0.02256 0.01268 -0.0243 0.3753 1.0000
6.250 0.7895 0.02330 0.01343 -0.0226 0.3328 1.0000
6.500 0.8065 0.02417 0.01421 -0.0210 0.2902 1.0000
6.750 0.8227 0.02518 0.01511 -0.0193 0.2477 1.0000
7.000 0.8385 0.02635 0.01618 -0.0178 0.2076 1.0000
7.250 0.8541 0.02770 0.01743 -0.0163 0.1713 1.0000
7.500 0.8690 0.02920 0.01883 -0.0148 0.1411 1.0000
7.750 0.8836 0.03081 0.02040 -0.0133 0.1158 1.0000
8.000 0.8976 0.03260 0.02215 -0.0118 0.0980 1.0000
8.250 0.9130 0.03438 0.02407 -0.0104 0.0821 1.0000
8.500 0.9285 0.03640 0.02610 -0.0090 0.0719 1.0000
8.750 0.9435 0.03832 0.02824 -0.0076 0.0620 1.0000
9.000 0.9606 0.04078 0.03098 -0.0064 0.0554 1.0000
9.250 0.9771 0.04341 0.03386 -0.0052 0.0511 1.0000
9.500 0.9907 0.04628 0.03681 -0.0041 0.0475 1.0000
9.750 0.9973 0.04925 0.04035 -0.0023 0.0439 1.0000
10.000 1.0010 0.05194 0.04335 -0.0006 0.0407 1.0000
10.250 1.0030 0.05478 0.04639 0.0011 0.0388 1.0000
10.500 1.0015 0.05796 0.04977 0.0028 0.0378 1.0000
11.000 0.9831 0.06553 0.05779 0.0056 0.0369 1.0000
11.250 0.9673 0.06977 0.06231 0.0058 0.0368 1.0000
11.500 0.9498 0.07457 0.06734 0.0048 0.0368 1.0000
11.750 0.9314 0.08001 0.07297 0.0026 0.0369 1.0000
12.000 0.9134 0.08608 0.07919 -0.0008 0.0370 1.0000
12.250 0.8753 0.09712 0.09054 -0.0094 0.0385 1.0000
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Polar data table (+)
Polar graphs
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