RG-12 (rg12-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG-12 (rg12-il) Reynolds number: 100,000 Max Cl/Cd: 47.26 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg12-il-100000-n5.txt Download as CSV file: xf-rg12-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5193 0.09251 0.08740 -0.0260 1.0000 0.0214
-9.500 -0.5302 0.08518 0.08017 -0.0301 1.0000 0.0205
-9.250 -0.5398 0.07538 0.07041 -0.0370 1.0000 0.0194
-9.000 -0.5516 0.06919 0.06423 -0.0414 1.0000 0.0192
-8.750 -0.5692 0.06452 0.05953 -0.0431 1.0000 0.0192
-8.500 -0.5841 0.06072 0.05568 -0.0428 1.0000 0.0190
-8.250 -0.5950 0.05676 0.05159 -0.0422 1.0000 0.0189
-8.000 -0.6029 0.05274 0.04738 -0.0412 1.0000 0.0188
-7.750 -0.6078 0.04861 0.04298 -0.0399 1.0000 0.0188
-7.500 -0.6082 0.04471 0.03873 -0.0383 1.0000 0.0187
-7.250 -0.6046 0.04104 0.03468 -0.0365 1.0000 0.0188
-7.000 -0.5975 0.03756 0.03075 -0.0347 1.0000 0.0189
-6.750 -0.5862 0.03464 0.02731 -0.0329 1.0000 0.0194
-6.500 -0.5744 0.03188 0.02428 -0.0315 1.0000 0.0206
-6.250 -0.5582 0.03035 0.02256 -0.0302 1.0000 0.0222
-6.000 -0.5406 0.02848 0.02040 -0.0288 1.0000 0.0237
-5.750 -0.5216 0.02637 0.01793 -0.0273 1.0000 0.0245
-5.500 -0.5016 0.02452 0.01579 -0.0259 1.0000 0.0254
-5.250 -0.4811 0.02293 0.01396 -0.0244 1.0000 0.0267
-5.000 -0.4605 0.02163 0.01245 -0.0230 1.0000 0.0282
-4.750 -0.4414 0.02020 0.01094 -0.0217 1.0000 0.0307
-4.500 -0.4210 0.01935 0.01004 -0.0205 1.0000 0.0361
-4.250 -0.4007 0.01847 0.00912 -0.0194 1.0000 0.0446
-4.000 -0.3800 0.01764 0.00829 -0.0183 1.0000 0.0589
-3.750 -0.3591 0.01690 0.00766 -0.0173 1.0000 0.0852
-3.500 -0.3379 0.01622 0.00712 -0.0165 1.0000 0.1197
-3.250 -0.3169 0.01558 0.00671 -0.0157 1.0000 0.1719
-3.000 -0.2863 0.01483 0.00635 -0.0170 0.9959 0.2698
-2.750 -0.2542 0.01394 0.00612 -0.0186 0.9897 0.4229
-2.500 -0.2259 0.01323 0.00633 -0.0183 0.9834 0.6263
-2.250 -0.1975 0.01321 0.00650 -0.0176 0.9747 0.7404
-2.000 -0.1663 0.01328 0.00653 -0.0176 0.9665 0.7943
-1.750 -0.1348 0.01332 0.00648 -0.0177 0.9581 0.8329
-1.500 -0.1050 0.01333 0.00643 -0.0174 0.9486 0.8630
-1.250 -0.0699 0.01334 0.00636 -0.0182 0.9411 0.8893
-1.000 -0.0339 0.01333 0.00625 -0.0192 0.9326 0.9127
-0.750 0.0092 0.01332 0.00615 -0.0218 0.9258 0.9318
-0.500 0.0569 0.01330 0.00604 -0.0255 0.9189 0.9478
-0.250 0.1069 0.01325 0.00591 -0.0298 0.9116 0.9606
0.000 0.1556 0.01315 0.00575 -0.0339 0.9030 0.9704
0.250 0.2036 0.01303 0.00558 -0.0380 0.8918 0.9769
0.500 0.2480 0.01289 0.00541 -0.0414 0.8788 0.9833
0.750 0.2925 0.01273 0.00522 -0.0447 0.8642 0.9880
1.000 0.3345 0.01258 0.00505 -0.0475 0.8475 0.9930
1.250 0.3742 0.01245 0.00491 -0.0499 0.8278 0.9984
1.500 0.4049 0.01237 0.00480 -0.0504 0.8063 1.0000
1.750 0.4295 0.01234 0.00474 -0.0497 0.7828 1.0000
2.000 0.4536 0.01234 0.00472 -0.0489 0.7590 1.0000
2.250 0.4768 0.01238 0.00471 -0.0478 0.7344 1.0000
2.500 0.4981 0.01245 0.00474 -0.0465 0.7086 1.0000
2.750 0.5192 0.01256 0.00480 -0.0450 0.6822 1.0000
3.000 0.5400 0.01271 0.00488 -0.0435 0.6553 1.0000
3.250 0.5610 0.01288 0.00503 -0.0421 0.6275 1.0000
3.500 0.5822 0.01309 0.00517 -0.0407 0.5987 1.0000
3.750 0.6036 0.01334 0.00534 -0.0393 0.5689 1.0000
4.000 0.6253 0.01361 0.00554 -0.0381 0.5381 1.0000
4.250 0.6471 0.01392 0.00578 -0.0368 0.5057 1.0000
4.500 0.6688 0.01426 0.00609 -0.0356 0.4725 1.0000
4.750 0.6904 0.01464 0.00639 -0.0345 0.4381 1.0000
5.000 0.7118 0.01506 0.00673 -0.0333 0.4019 1.0000
5.250 0.7331 0.01553 0.00711 -0.0321 0.3644 1.0000
5.500 0.7540 0.01605 0.00754 -0.0310 0.3266 1.0000
5.750 0.7746 0.01663 0.00802 -0.0299 0.2879 1.0000
6.000 0.7952 0.01726 0.00860 -0.0288 0.2488 1.0000
6.250 0.8153 0.01797 0.00921 -0.0277 0.2100 1.0000
6.500 0.8350 0.01877 0.00989 -0.0266 0.1726 1.0000
6.750 0.8541 0.01968 0.01066 -0.0255 0.1385 1.0000
7.000 0.8730 0.02064 0.01152 -0.0244 0.1088 1.0000
7.250 0.8910 0.02172 0.01250 -0.0231 0.0853 1.0000
7.500 0.9091 0.02280 0.01360 -0.0218 0.0673 1.0000
7.750 0.9263 0.02398 0.01485 -0.0205 0.0534 1.0000
8.000 0.9414 0.02538 0.01630 -0.0188 0.0455 1.0000
8.250 0.9571 0.02673 0.01777 -0.0171 0.0395 1.0000
8.500 0.9720 0.02819 0.01934 -0.0155 0.0340 1.0000
8.750 0.9872 0.02962 0.02091 -0.0140 0.0298 1.0000
9.000 0.9989 0.03156 0.02292 -0.0122 0.0272 1.0000
9.250 1.0137 0.03347 0.02507 -0.0106 0.0248 1.0000
9.500 1.0275 0.03506 0.02691 -0.0091 0.0218 1.0000
9.750 1.0390 0.03691 0.02894 -0.0075 0.0201 1.0000
10.000 1.0481 0.03910 0.03136 -0.0057 0.0191 1.0000
10.250 1.0528 0.04194 0.03441 -0.0037 0.0182 1.0000
10.500 1.0537 0.04517 0.03790 -0.0015 0.0177 1.0000
10.750 1.0521 0.04794 0.04101 0.0009 0.0174 1.0000
11.000 1.0457 0.05108 0.04449 0.0032 0.0172 1.0000
11.250 1.0362 0.05441 0.04812 0.0048 0.0170 1.0000
11.500 1.0235 0.05815 0.05215 0.0056 0.0168 1.0000
11.750 1.0085 0.06240 0.05666 0.0053 0.0167 1.0000
12.000 0.9923 0.06725 0.06175 0.0038 0.0167 1.0000
12.250 0.9744 0.07293 0.06765 0.0011 0.0168 1.0000
12.500 0.9554 0.07950 0.07440 -0.0029 0.0169 1.0000
12.750 0.9363 0.08691 0.08196 -0.0078 0.0171 1.0000
13.000 0.9172 0.09512 0.09029 -0.0134 0.0174 1.0000
13.250 0.8952 0.10493 0.10021 -0.0200 0.0175 1.0000
13.500 0.8772 0.11440 0.10972 -0.0259 0.0178 1.0000
13.750 0.8527 0.12785 0.12321 -0.0339 0.0184 1.0000
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Polar data table (+)
Polar graphs
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