RG-12 (rg12-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG-12 (rg12-il) Reynolds number: 500,000 Max Cl/Cd: 82.65 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg12-il-500000.txt Download as CSV file: xf-rg12-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5091 0.08558 0.08331 -0.0297 1.0000 0.0194
-9.250 -0.5133 0.07970 0.07746 -0.0332 1.0000 0.0194
-9.000 -0.5229 0.07051 0.06827 -0.0413 1.0000 0.0194
-8.750 -0.5398 0.06545 0.06317 -0.0444 1.0000 0.0194
-8.500 -0.5611 0.06222 0.05987 -0.0433 1.0000 0.0194
-8.250 -0.5740 0.05855 0.05609 -0.0423 1.0000 0.0194
-8.000 -0.6149 0.04976 0.04707 -0.0405 1.0000 0.0200
-7.750 -0.6228 0.04556 0.04271 -0.0385 1.0000 0.0204
-7.500 -0.6223 0.04256 0.03958 -0.0365 1.0000 0.0209
-7.250 -0.6152 0.04064 0.03760 -0.0347 1.0000 0.0214
-7.000 -0.6090 0.03822 0.03502 -0.0327 1.0000 0.0219
-6.250 -0.5861 0.02650 0.02216 -0.0249 1.0000 0.0179
-6.000 -0.5679 0.01994 0.01460 -0.0228 0.9993 0.0133
-5.750 -0.5338 0.01861 0.01307 -0.0243 0.9971 0.0130
-5.500 -0.5002 0.01697 0.01123 -0.0257 0.9951 0.0129
-5.250 -0.4701 0.01443 0.00842 -0.0264 0.9932 0.0134
-5.000 -0.4386 0.01305 0.00691 -0.0274 0.9902 0.0142
-4.750 -0.4042 0.01231 0.00610 -0.0290 0.9872 0.0156
-4.500 -0.3678 0.01173 0.00546 -0.0309 0.9847 0.0173
-4.250 -0.3298 0.01128 0.00493 -0.0331 0.9827 0.0192
-4.000 -0.2991 0.01057 0.00421 -0.0338 0.9776 0.0273
-3.750 -0.2643 0.00985 0.00369 -0.0354 0.9739 0.0701
-3.500 -0.2269 0.00942 0.00339 -0.0377 0.9713 0.1088
-3.250 -0.1937 0.00887 0.00313 -0.0392 0.9671 0.1770
-3.000 -0.1617 0.00822 0.00288 -0.0405 0.9619 0.2780
-2.750 -0.1264 0.00746 0.00263 -0.0425 0.9587 0.4134
-2.500 -0.0922 0.00676 0.00241 -0.0442 0.9552 0.5486
-2.250 -0.0642 0.00624 0.00234 -0.0441 0.9479 0.6794
-2.000 -0.0290 0.00607 0.00228 -0.0454 0.9435 0.7370
-1.750 0.0008 0.00598 0.00221 -0.0455 0.9343 0.7639
-1.500 0.0338 0.00590 0.00212 -0.0462 0.9264 0.7838
-1.250 0.0656 0.00584 0.00203 -0.0468 0.9163 0.7999
-1.000 0.0950 0.00581 0.00198 -0.0468 0.9036 0.8137
-0.750 0.1238 0.00579 0.00194 -0.0466 0.8896 0.8256
-0.500 0.1518 0.00579 0.00189 -0.0463 0.8742 0.8361
-0.250 0.1788 0.00582 0.00186 -0.0459 0.8571 0.8464
0.000 0.2050 0.00585 0.00185 -0.0452 0.8389 0.8560
0.250 0.2308 0.00589 0.00184 -0.0445 0.8200 0.8648
0.500 0.2568 0.00595 0.00183 -0.0438 0.8001 0.8736
0.750 0.2817 0.00600 0.00183 -0.0429 0.7794 0.8819
1.000 0.3064 0.00607 0.00184 -0.0420 0.7582 0.8908
1.250 0.3310 0.00616 0.00186 -0.0411 0.7360 0.9004
1.500 0.3546 0.00622 0.00189 -0.0399 0.7132 0.9089
1.750 0.3783 0.00631 0.00191 -0.0388 0.6897 0.9177
2.000 0.4019 0.00641 0.00194 -0.0377 0.6653 0.9267
2.250 0.4254 0.00651 0.00198 -0.0366 0.6398 0.9348
2.500 0.4494 0.00662 0.00202 -0.0357 0.6137 0.9436
2.750 0.4744 0.00674 0.00207 -0.0350 0.5872 0.9519
3.000 0.5015 0.00689 0.00214 -0.0348 0.5594 0.9601
3.250 0.5298 0.00706 0.00222 -0.0350 0.5294 0.9692
3.500 0.5628 0.00729 0.00235 -0.0362 0.4957 0.9755
3.750 0.5954 0.00752 0.00248 -0.0375 0.4609 0.9832
4.000 0.6306 0.00780 0.00263 -0.0393 0.4247 0.9889
4.250 0.6652 0.00810 0.00281 -0.0411 0.3864 0.9957
4.500 0.6926 0.00838 0.00300 -0.0414 0.3535 1.0000
4.750 0.7119 0.00868 0.00318 -0.0400 0.3209 1.0000
5.000 0.7342 0.00905 0.00340 -0.0392 0.2850 1.0000
5.250 0.7570 0.00949 0.00367 -0.0385 0.2446 1.0000
5.500 0.7797 0.00998 0.00397 -0.0378 0.2016 1.0000
5.750 0.8027 0.01048 0.00432 -0.0371 0.1652 1.0000
6.000 0.8260 0.01096 0.00468 -0.0365 0.1350 1.0000
6.250 0.8492 0.01146 0.00507 -0.0359 0.1076 1.0000
6.500 0.8721 0.01201 0.00550 -0.0352 0.0834 1.0000
6.750 0.8943 0.01263 0.00600 -0.0345 0.0601 1.0000
7.000 0.9166 0.01325 0.00654 -0.0337 0.0416 1.0000
7.250 0.9382 0.01395 0.00721 -0.0328 0.0298 1.0000
7.500 0.9602 0.01461 0.00792 -0.0318 0.0238 1.0000
7.750 0.9791 0.01561 0.00896 -0.0304 0.0180 1.0000
8.000 1.0022 0.01609 0.00950 -0.0298 0.0153 1.0000
8.250 1.0204 0.01711 0.01057 -0.0283 0.0127 1.0000
8.500 1.0374 0.01827 0.01187 -0.0266 0.0113 1.0000
8.750 1.0559 0.01921 0.01292 -0.0252 0.0103 1.0000
9.000 1.0738 0.02019 0.01398 -0.0238 0.0094 1.0000
9.250 1.0900 0.02131 0.01521 -0.0223 0.0088 1.0000
9.500 1.1027 0.02289 0.01692 -0.0202 0.0084 1.0000
9.750 1.1124 0.02502 0.01923 -0.0178 0.0081 1.0000
10.000 1.1202 0.02777 0.02222 -0.0154 0.0079 1.0000
10.250 1.1264 0.03085 0.02559 -0.0129 0.0078 1.0000
10.500 1.1358 0.03237 0.02729 -0.0108 0.0077 1.0000
10.750 1.1412 0.03380 0.02891 -0.0080 0.0076 1.0000
11.000 1.1459 0.03495 0.03024 -0.0053 0.0074 1.0000
11.250 1.1449 0.03695 0.03244 -0.0024 0.0073 1.0000
11.500 1.1392 0.03945 0.03517 0.0003 0.0072 1.0000
11.750 1.1320 0.04209 0.03802 0.0025 0.0071 1.0000
12.000 1.1201 0.04544 0.04160 0.0041 0.0071 1.0000
12.250 1.1081 0.04901 0.04538 0.0047 0.0071 1.0000
12.500 1.0932 0.05332 0.04989 0.0043 0.0071 1.0000
12.750 1.0773 0.05828 0.05505 0.0028 0.0071 1.0000
13.000 1.0601 0.06404 0.06099 0.0000 0.0072 1.0000
13.250 1.0377 0.07144 0.06858 -0.0043 0.0072 1.0000
13.500 1.0197 0.07881 0.07611 -0.0091 0.0073 1.0000
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Polar data table (+)
Polar graphs
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