RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Reynolds number: 50,000 Max Cl/Cd: 35.9 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg12a189-il-50000-n5.txt Download as CSV file: xf-rg12a189-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4940 0.09085 0.08384 -0.0331 1.0000 0.0408
-8.750 -0.4950 0.08678 0.07984 -0.0342 1.0000 0.0403
-8.500 -0.4983 0.08274 0.07586 -0.0357 1.0000 0.0398
-8.250 -0.5057 0.07869 0.07188 -0.0371 1.0000 0.0393
-8.000 -0.5121 0.07447 0.06770 -0.0383 1.0000 0.0389
-7.750 -0.5179 0.07027 0.06347 -0.0391 1.0000 0.0384
-7.500 -0.5220 0.06618 0.05932 -0.0396 1.0000 0.0379
-7.250 -0.5248 0.06195 0.05498 -0.0398 1.0000 0.0376
-7.000 -0.5249 0.05776 0.05061 -0.0396 1.0000 0.0372
-6.750 -0.5219 0.05367 0.04627 -0.0392 1.0000 0.0369
-6.500 -0.5159 0.04965 0.04188 -0.0386 1.0000 0.0368
-6.250 -0.5066 0.04582 0.03767 -0.0378 1.0000 0.0368
-6.000 -0.4942 0.04225 0.03366 -0.0368 1.0000 0.0371
-5.750 -0.4790 0.03897 0.02986 -0.0357 1.0000 0.0386
-5.500 -0.4607 0.03608 0.02630 -0.0345 1.0000 0.0408
-5.250 -0.4423 0.03342 0.02339 -0.0336 1.0000 0.0430
-5.000 -0.4219 0.03124 0.02094 -0.0325 1.0000 0.0452
-4.750 -0.3999 0.02918 0.01857 -0.0312 1.0000 0.0478
-4.500 -0.3769 0.02751 0.01648 -0.0298 1.0000 0.0533
-4.250 -0.3559 0.02601 0.01495 -0.0287 1.0000 0.0609
-4.000 -0.3337 0.02452 0.01329 -0.0271 1.0000 0.0690
-3.750 -0.3126 0.02335 0.01211 -0.0259 1.0000 0.0865
-3.500 -0.2909 0.02211 0.01092 -0.0249 1.0000 0.1184
-3.250 -0.2706 0.02075 0.00993 -0.0240 1.0000 0.1794
-3.000 -0.2516 0.01916 0.00912 -0.0233 1.0000 0.3093
-2.750 -0.2416 0.01765 0.00908 -0.0194 1.0000 0.5692
-2.500 -0.2354 0.01756 0.00939 -0.0129 1.0000 0.7676
-2.250 -0.2229 0.01760 0.00938 -0.0082 1.0000 0.8587
-2.000 -0.1686 0.01770 0.00915 -0.0114 1.0000 0.9504
-1.750 -0.0934 0.01769 0.00859 -0.0207 1.0000 1.0000
-1.500 -0.0900 0.01759 0.00834 -0.0174 1.0000 1.0000
-1.250 -0.0833 0.01755 0.00814 -0.0147 1.0000 1.0000
-1.000 -0.0722 0.01759 0.00800 -0.0129 1.0000 1.0000
-0.750 -0.0440 0.01781 0.00802 -0.0141 0.9947 1.0000
-0.500 -0.0002 0.01813 0.00809 -0.0182 0.9830 1.0000
-0.250 0.0424 0.01839 0.00817 -0.0218 0.9706 1.0000
0.000 0.0836 0.01860 0.00824 -0.0251 0.9574 1.0000
0.250 0.1240 0.01877 0.00828 -0.0282 0.9437 1.0000
0.500 0.1636 0.01889 0.00833 -0.0309 0.9295 1.0000
0.750 0.2025 0.01899 0.00838 -0.0333 0.9149 1.0000
1.000 0.2410 0.01905 0.00841 -0.0356 0.8998 1.0000
1.250 0.2796 0.01908 0.00843 -0.0378 0.8845 1.0000
1.500 0.3180 0.01908 0.00846 -0.0397 0.8688 1.0000
1.750 0.3546 0.01907 0.00849 -0.0412 0.8521 1.0000
2.000 0.3913 0.01903 0.00850 -0.0426 0.8351 1.0000
2.250 0.4282 0.01897 0.00849 -0.0439 0.8177 1.0000
2.500 0.4585 0.01900 0.00860 -0.0440 0.7965 1.0000
2.750 0.4926 0.01897 0.00862 -0.0445 0.7765 1.0000
3.000 0.5220 0.01902 0.00874 -0.0443 0.7535 1.0000
3.250 0.5529 0.01907 0.00882 -0.0443 0.7307 1.0000
3.500 0.5819 0.01917 0.00902 -0.0439 0.7060 1.0000
3.750 0.6090 0.01934 0.00923 -0.0432 0.6797 1.0000
4.000 0.6355 0.01954 0.00948 -0.0424 0.6525 1.0000
4.250 0.6611 0.01978 0.00977 -0.0415 0.6241 1.0000
4.500 0.6859 0.02007 0.01013 -0.0404 0.5945 1.0000
4.750 0.7100 0.02039 0.01048 -0.0393 0.5638 1.0000
5.000 0.7328 0.02076 0.01089 -0.0380 0.5312 1.0000
5.250 0.7548 0.02118 0.01134 -0.0366 0.4970 1.0000
5.500 0.7763 0.02165 0.01185 -0.0352 0.4617 1.0000
5.750 0.7966 0.02219 0.01240 -0.0336 0.4242 1.0000
6.000 0.8161 0.02281 0.01302 -0.0321 0.3853 1.0000
6.250 0.8347 0.02352 0.01370 -0.0305 0.3449 1.0000
6.500 0.8521 0.02434 0.01447 -0.0288 0.3030 1.0000
6.750 0.8685 0.02532 0.01537 -0.0271 0.2601 1.0000
7.000 0.8838 0.02647 0.01647 -0.0255 0.2174 1.0000
7.250 0.8980 0.02784 0.01771 -0.0239 0.1765 1.0000
7.500 0.9108 0.02944 0.01912 -0.0223 0.1395 1.0000
7.750 0.9234 0.03118 0.02075 -0.0207 0.1085 1.0000
8.000 0.9355 0.03305 0.02251 -0.0191 0.0886 1.0000
8.250 0.9490 0.03495 0.02448 -0.0175 0.0740 1.0000
8.500 0.9639 0.03699 0.02661 -0.0160 0.0660 1.0000
8.750 0.9823 0.03926 0.02919 -0.0147 0.0598 1.0000
9.000 0.9972 0.04131 0.03135 -0.0135 0.0544 1.0000
9.250 1.0127 0.04378 0.03407 -0.0124 0.0500 1.0000
9.500 1.0281 0.04664 0.03734 -0.0112 0.0472 1.0000
9.750 1.0398 0.04967 0.04073 -0.0098 0.0453 1.0000
10.000 1.0473 0.05281 0.04418 -0.0084 0.0439 1.0000
10.250 1.0510 0.05608 0.04773 -0.0068 0.0428 1.0000
10.500 1.0499 0.05942 0.05130 -0.0051 0.0419 1.0000
11.000 1.0314 0.06683 0.05919 -0.0020 0.0408 1.0000
11.250 1.0150 0.07099 0.06363 -0.0016 0.0407 1.0000
11.500 0.9968 0.07573 0.06861 -0.0024 0.0406 1.0000
11.750 0.9778 0.08114 0.07422 -0.0044 0.0407 1.0000
12.000 0.9592 0.08723 0.08047 -0.0076 0.0409 1.0000
12.250 0.9103 0.10036 0.09393 -0.0178 0.0435 1.0000
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Polar data table (+)
Polar graphs
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