RG-12 (rg12-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG-12 (rg12-il) Reynolds number: 200,000 Max Cl/Cd: 58.92 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg12-il-200000-n5.txt Download as CSV file: xf-rg12-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5373 0.08416 0.08059 -0.0285 1.0000 0.0124
-9.500 -0.5455 0.07838 0.07486 -0.0316 1.0000 0.0123
-9.250 -0.5551 0.07220 0.06874 -0.0355 1.0000 0.0121
-9.000 -0.5734 0.06368 0.06022 -0.0425 1.0000 0.0119
-8.750 -0.5967 0.05843 0.05491 -0.0434 1.0000 0.0118
-8.500 -0.6132 0.05357 0.04992 -0.0430 1.0000 0.0117
-8.250 -0.6256 0.04884 0.04498 -0.0418 1.0000 0.0115
-8.000 -0.6344 0.04413 0.03999 -0.0400 1.0000 0.0114
-7.750 -0.6388 0.03955 0.03504 -0.0379 1.0000 0.0113
-7.500 -0.6378 0.03543 0.03049 -0.0356 1.0000 0.0112
-7.250 -0.6316 0.03185 0.02647 -0.0334 1.0000 0.0112
-7.000 -0.6215 0.02872 0.02288 -0.0313 1.0000 0.0113
-6.750 -0.6077 0.02613 0.01985 -0.0294 1.0000 0.0114
-6.500 -0.5913 0.02401 0.01736 -0.0277 1.0000 0.0117
-6.250 -0.5732 0.02224 0.01527 -0.0262 1.0000 0.0120
-6.000 -0.5539 0.02079 0.01356 -0.0247 1.0000 0.0124
-5.750 -0.5341 0.01960 0.01217 -0.0233 1.0000 0.0128
-5.500 -0.5150 0.01818 0.01062 -0.0220 1.0000 0.0134
-5.250 -0.4846 0.01741 0.00981 -0.0231 0.9975 0.0155
-5.000 -0.4508 0.01661 0.00890 -0.0246 0.9942 0.0174
-4.750 -0.4187 0.01572 0.00783 -0.0257 0.9902 0.0188
-4.500 -0.3857 0.01480 0.00682 -0.0271 0.9861 0.0216
-4.250 -0.3505 0.01418 0.00611 -0.0288 0.9827 0.0282
-4.000 -0.3200 0.01354 0.00552 -0.0296 0.9768 0.0433
-3.750 -0.2865 0.01298 0.00514 -0.0312 0.9721 0.0784
-3.500 -0.2544 0.01242 0.00477 -0.0324 0.9669 0.1208
-3.250 -0.2227 0.01189 0.00440 -0.0336 0.9606 0.1752
-3.000 -0.1877 0.01133 0.00410 -0.0355 0.9563 0.2464
-2.750 -0.1594 0.01072 0.00383 -0.0360 0.9481 0.3384
-2.500 -0.1264 0.00996 0.00359 -0.0375 0.9433 0.4693
-2.250 -0.1009 0.00933 0.00352 -0.0369 0.9344 0.6104
-2.000 -0.0692 0.00912 0.00357 -0.0371 0.9281 0.7076
-1.750 -0.0392 0.00904 0.00351 -0.0372 0.9187 0.7487
-1.500 -0.0082 0.00898 0.00345 -0.0374 0.9093 0.7772
-1.250 0.0248 0.00892 0.00335 -0.0381 0.9004 0.7992
-1.000 0.0559 0.00887 0.00326 -0.0384 0.8891 0.8174
-0.750 0.0860 0.00883 0.00320 -0.0384 0.8766 0.8331
-0.500 0.1160 0.00879 0.00312 -0.0384 0.8631 0.8473
-0.250 0.1456 0.00876 0.00305 -0.0384 0.8482 0.8601
0.000 0.1741 0.00875 0.00299 -0.0381 0.8322 0.8728
0.250 0.2008 0.00875 0.00295 -0.0374 0.8143 0.8848
0.500 0.2276 0.00877 0.00292 -0.0367 0.7955 0.8959
0.750 0.2548 0.00879 0.00287 -0.0362 0.7761 0.9060
1.000 0.2814 0.00883 0.00285 -0.0356 0.7551 0.9157
1.250 0.3094 0.00889 0.00283 -0.0354 0.7336 0.9236
1.500 0.3374 0.00895 0.00283 -0.0352 0.7104 0.9313
1.750 0.3661 0.00904 0.00283 -0.0353 0.6868 0.9385
2.000 0.3954 0.00914 0.00285 -0.0355 0.6619 0.9452
2.250 0.4253 0.00927 0.00291 -0.0359 0.6361 0.9521
2.500 0.4556 0.00941 0.00296 -0.0364 0.6087 0.9589
2.750 0.4865 0.00958 0.00304 -0.0371 0.5798 0.9662
3.000 0.5179 0.00976 0.00313 -0.0379 0.5491 0.9735
3.250 0.5490 0.00997 0.00328 -0.0388 0.5179 0.9818
3.500 0.5813 0.01021 0.00342 -0.0399 0.4851 0.9902
3.750 0.6119 0.01048 0.00358 -0.0408 0.4516 1.0000
4.000 0.6304 0.01075 0.00375 -0.0392 0.4216 1.0000
4.250 0.6507 0.01106 0.00396 -0.0379 0.3897 1.0000
4.500 0.6720 0.01141 0.00422 -0.0368 0.3571 1.0000
4.750 0.6941 0.01178 0.00449 -0.0359 0.3243 1.0000
5.000 0.7163 0.01219 0.00479 -0.0350 0.2906 1.0000
5.250 0.7387 0.01263 0.00513 -0.0342 0.2569 1.0000
5.500 0.7611 0.01311 0.00550 -0.0334 0.2237 1.0000
5.750 0.7831 0.01364 0.00591 -0.0327 0.1897 1.0000
6.000 0.8051 0.01422 0.00640 -0.0319 0.1565 1.0000
6.250 0.8266 0.01486 0.00691 -0.0311 0.1253 1.0000
6.500 0.8481 0.01553 0.00746 -0.0303 0.0982 1.0000
6.750 0.8697 0.01619 0.00805 -0.0294 0.0754 1.0000
7.000 0.8909 0.01690 0.00871 -0.0286 0.0584 1.0000
7.250 0.9121 0.01762 0.00944 -0.0276 0.0461 1.0000
7.500 0.9321 0.01846 0.01032 -0.0266 0.0365 1.0000
7.750 0.9524 0.01926 0.01117 -0.0256 0.0288 1.0000
8.000 0.9715 0.02018 0.01219 -0.0243 0.0241 1.0000
8.250 0.9910 0.02102 0.01310 -0.0232 0.0199 1.0000
8.500 1.0073 0.02221 0.01438 -0.0217 0.0169 1.0000
8.750 1.0243 0.02328 0.01561 -0.0202 0.0152 1.0000
9.000 1.0405 0.02441 0.01686 -0.0187 0.0136 1.0000
9.250 1.0527 0.02589 0.01842 -0.0169 0.0122 1.0000
9.500 1.0676 0.02713 0.01987 -0.0153 0.0111 1.0000
9.750 1.0819 0.02835 0.02126 -0.0137 0.0101 1.0000
10.000 1.0939 0.02972 0.02278 -0.0119 0.0094 1.0000
10.250 1.1027 0.03119 0.02439 -0.0097 0.0089 1.0000
10.500 1.1093 0.03275 0.02610 -0.0073 0.0086 1.0000
10.750 1.1133 0.03456 0.02805 -0.0049 0.0083 1.0000
11.000 1.1122 0.03699 0.03067 -0.0023 0.0079 1.0000
11.250 1.1109 0.03953 0.03341 -0.0001 0.0078 1.0000
11.500 1.1094 0.04201 0.03615 0.0018 0.0077 1.0000
11.750 1.1051 0.04483 0.03922 0.0032 0.0076 1.0000
12.000 1.0986 0.04799 0.04263 0.0041 0.0075 1.0000
12.250 1.0894 0.05166 0.04656 0.0043 0.0074 1.0000
12.500 1.0781 0.05588 0.05101 0.0036 0.0074 1.0000
12.750 1.0655 0.06066 0.05602 0.0020 0.0074 1.0000
13.000 1.0520 0.06602 0.06158 -0.0005 0.0074 1.0000
13.250 1.0340 0.07270 0.06849 -0.0043 0.0074 1.0000
13.500 1.0184 0.07952 0.07549 -0.0085 0.0074 1.0000
13.750 1.0003 0.08748 0.08362 -0.0137 0.0074 1.0000
14.000 0.9817 0.09608 0.09237 -0.0193 0.0075 1.0000
14.250 0.9609 0.10587 0.10230 -0.0255 0.0076 1.0000
14.500 0.9406 0.11613 0.11267 -0.0318 0.0077 1.0000
14.750 0.9208 0.12669 0.12330 -0.0379 0.0078 1.0000
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Polar data table (+)
Polar graphs
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