RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Reynolds number: 200,000 Max Cl/Cd: 69.36 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15a213-il-200000.txt Download as CSV file: xf-rg15a213-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RG 15A 2.5/13.0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5463 0.07221 0.06843 -0.0637 1.0000 0.0389
-10.750 -0.5525 0.06805 0.06433 -0.0641 1.0000 0.0382
-10.500 -0.5836 0.06198 0.05820 -0.0671 1.0000 0.0379
-10.250 -0.6107 0.05806 0.05422 -0.0670 1.0000 0.0375
-10.000 -0.6398 0.05545 0.05158 -0.0642 1.0000 0.0370
-9.750 -0.6700 0.05276 0.04881 -0.0600 1.0000 0.0364
-9.500 -0.6946 0.04957 0.04544 -0.0562 1.0000 0.0361
-9.250 -0.7160 0.04594 0.04156 -0.0525 1.0000 0.0357
-9.000 -0.7335 0.04171 0.03694 -0.0490 1.0000 0.0350
-8.750 -0.7397 0.03824 0.03309 -0.0460 1.0000 0.0349
-8.500 -0.7394 0.03495 0.02936 -0.0435 1.0000 0.0348
-8.250 -0.7327 0.03224 0.02627 -0.0414 1.0000 0.0349
-8.000 -0.7213 0.03019 0.02392 -0.0396 1.0000 0.0354
-7.750 -0.7072 0.02837 0.02182 -0.0380 1.0000 0.0360
-7.500 -0.6760 0.02665 0.01975 -0.0394 0.9970 0.0375
-7.250 -0.6401 0.02520 0.01796 -0.0416 0.9933 0.0393
-7.000 -0.6076 0.02353 0.01627 -0.0432 0.9890 0.0412
-6.750 -0.5711 0.02248 0.01513 -0.0453 0.9850 0.0434
-6.500 -0.5354 0.02156 0.01407 -0.0471 0.9806 0.0462
-6.250 -0.5022 0.02044 0.01295 -0.0486 0.9754 0.0502
-6.000 -0.4632 0.01967 0.01214 -0.0511 0.9717 0.0553
-5.750 -0.4327 0.01869 0.01121 -0.0520 0.9653 0.0626
-5.500 -0.3960 0.01782 0.01038 -0.0541 0.9605 0.0821
-5.250 -0.3573 0.01718 0.00978 -0.0566 0.9565 0.1076
-5.000 -0.3269 0.01659 0.00931 -0.0575 0.9490 0.1265
-4.750 -0.2864 0.01614 0.00887 -0.0602 0.9451 0.1506
-4.500 -0.2550 0.01563 0.00851 -0.0612 0.9381 0.1774
-4.250 -0.2183 0.01503 0.00810 -0.0633 0.9328 0.2174
-4.000 -0.1772 0.01436 0.00767 -0.0662 0.9297 0.2767
-3.750 -0.1492 0.01379 0.00736 -0.0665 0.9212 0.3363
-3.500 -0.1108 0.01309 0.00700 -0.0687 0.9170 0.4161
-3.000 -0.0430 0.01215 0.00675 -0.0706 0.9054 0.5960
-2.750 -0.0031 0.01196 0.00664 -0.0723 0.9012 0.6510
-2.500 0.0326 0.01186 0.00653 -0.0732 0.8954 0.6851
-2.250 0.0651 0.01177 0.00642 -0.0735 0.8874 0.7099
-2.000 0.1047 0.01162 0.00626 -0.0751 0.8830 0.7327
-1.750 0.1304 0.01163 0.00625 -0.0739 0.8718 0.7541
-1.500 0.1623 0.01156 0.00616 -0.0740 0.8636 0.7717
-1.250 0.1929 0.01148 0.00604 -0.0738 0.8540 0.7858
-1.000 0.2196 0.01143 0.00598 -0.0729 0.8427 0.7977
-0.750 0.2491 0.01137 0.00586 -0.0726 0.8326 0.8097
-0.500 0.2773 0.01131 0.00576 -0.0720 0.8215 0.8221
-0.250 0.3023 0.01130 0.00570 -0.0710 0.8085 0.8347
0.000 0.3267 0.01128 0.00565 -0.0696 0.7958 0.8454
0.250 0.3519 0.01125 0.00558 -0.0685 0.7833 0.8561
0.500 0.3776 0.01122 0.00549 -0.0675 0.7707 0.8675
0.750 0.4020 0.01121 0.00542 -0.0663 0.7577 0.8782
1.000 0.4244 0.01118 0.00537 -0.0647 0.7435 0.8885
1.250 0.4474 0.01117 0.00532 -0.0633 0.7293 0.8995
1.500 0.4705 0.01116 0.00527 -0.0619 0.7150 0.9108
1.750 0.4949 0.01115 0.00522 -0.0608 0.7006 0.9209
2.000 0.5204 0.01115 0.00517 -0.0601 0.6857 0.9314
2.250 0.5472 0.01118 0.00514 -0.0596 0.6707 0.9426
2.500 0.5803 0.01122 0.00514 -0.0606 0.6548 0.9511
2.750 0.6141 0.01129 0.00515 -0.0617 0.6383 0.9600
3.000 0.6503 0.01138 0.00519 -0.0635 0.6212 0.9684
3.250 0.6890 0.01150 0.00523 -0.0658 0.6034 0.9753
3.500 0.7270 0.01163 0.00528 -0.0681 0.5854 0.9833
3.750 0.7679 0.01177 0.00537 -0.0711 0.5661 0.9900
4.000 0.8070 0.01192 0.00548 -0.0737 0.5462 0.9992
4.250 0.8166 0.01204 0.00556 -0.0707 0.5311 1.0000
4.500 0.8286 0.01220 0.00566 -0.0681 0.5158 1.0000
4.750 0.8488 0.01242 0.00581 -0.0669 0.4992 1.0000
5.000 0.8712 0.01267 0.00599 -0.0661 0.4820 1.0000
5.250 0.8941 0.01294 0.00620 -0.0653 0.4647 1.0000
5.500 0.9168 0.01323 0.00643 -0.0645 0.4473 1.0000
5.750 0.9391 0.01354 0.00667 -0.0636 0.4298 1.0000
6.000 0.9611 0.01388 0.00693 -0.0626 0.4121 1.0000
6.250 0.9827 0.01421 0.00722 -0.0616 0.3940 1.0000
6.500 1.0040 0.01455 0.00754 -0.0605 0.3762 1.0000
6.750 1.0250 0.01492 0.00787 -0.0594 0.3586 1.0000
7.000 1.0455 0.01532 0.00824 -0.0582 0.3416 1.0000
7.250 1.0657 0.01574 0.00863 -0.0570 0.3250 1.0000
7.500 1.0852 0.01619 0.00904 -0.0557 0.3085 1.0000
7.750 1.1039 0.01666 0.00948 -0.0543 0.2921 1.0000
8.000 1.1219 0.01716 0.00995 -0.0527 0.2758 1.0000
8.250 1.1389 0.01769 0.01044 -0.0511 0.2596 1.0000
8.500 1.1546 0.01826 0.01095 -0.0492 0.2434 1.0000
8.750 1.1681 0.01883 0.01147 -0.0470 0.2274 1.0000
9.000 1.1813 0.01941 0.01204 -0.0448 0.2117 1.0000
9.250 1.1940 0.02008 0.01267 -0.0426 0.1975 1.0000
9.500 1.2070 0.02077 0.01336 -0.0405 0.1842 1.0000
9.750 1.2198 0.02149 0.01409 -0.0384 0.1715 1.0000
10.000 1.2319 0.02227 0.01489 -0.0364 0.1598 1.0000
10.250 1.2428 0.02316 0.01578 -0.0342 0.1494 1.0000
10.500 1.2512 0.02419 0.01676 -0.0319 0.1398 1.0000
10.750 1.2623 0.02508 0.01772 -0.0300 0.1301 1.0000
11.000 1.2712 0.02616 0.01883 -0.0280 0.1213 1.0000
11.250 1.2764 0.02750 0.02010 -0.0258 0.1132 1.0000
11.500 1.2861 0.02858 0.02131 -0.0241 0.1049 1.0000
11.750 1.2904 0.03012 0.02284 -0.0221 0.0978 1.0000
12.000 1.2963 0.03156 0.02435 -0.0204 0.0908 1.0000
12.250 1.2992 0.03338 0.02619 -0.0186 0.0846 1.0000
12.500 1.3038 0.03508 0.02795 -0.0172 0.0791 1.0000
12.750 1.3054 0.03722 0.03005 -0.0157 0.0746 1.0000
13.000 1.3108 0.03902 0.03200 -0.0145 0.0705 1.0000
13.250 1.3147 0.04099 0.03402 -0.0136 0.0672 1.0000
13.500 1.3194 0.04324 0.03621 -0.0124 0.0640 1.0000
13.750 1.3246 0.04527 0.03844 -0.0117 0.0620 1.0000
14.000 1.3296 0.04738 0.04068 -0.0110 0.0598 1.0000
14.250 1.3340 0.04955 0.04294 -0.0105 0.0577 1.0000
14.500 1.3386 0.05180 0.04521 -0.0101 0.0558 1.0000
14.750 1.3480 0.05405 0.04746 -0.0094 0.0537 1.0000
15.000 1.3489 0.05671 0.05033 -0.0092 0.0526 1.0000
15.250 1.3489 0.05956 0.05338 -0.0092 0.0512 1.0000
15.500 1.3479 0.06258 0.05655 -0.0095 0.0497 1.0000
15.750 1.3475 0.06556 0.05965 -0.0099 0.0483 1.0000
16.000 1.3486 0.06839 0.06252 -0.0104 0.0467 1.0000
16.250 1.3530 0.07133 0.06546 -0.0103 0.0448 1.0000
16.500 1.3441 0.07559 0.06995 -0.0118 0.0440 1.0000
16.750 1.3354 0.08007 0.07466 -0.0134 0.0430 1.0000
17.000 1.3271 0.08472 0.07950 -0.0153 0.0420 1.0000
17.250 1.3191 0.08947 0.08443 -0.0173 0.0410 1.0000
17.500 1.3124 0.09416 0.08925 -0.0195 0.0400 1.0000
17.750 1.3091 0.09830 0.09347 -0.0214 0.0389 1.0000
18.000 1.3112 0.10151 0.09666 -0.0226 0.0377 1.0000
18.250 1.2989 0.10742 0.10272 -0.0253 0.0368 1.0000
18.500 1.2817 0.11450 0.11004 -0.0294 0.0365 1.0000
18.750 1.2620 0.12234 0.11812 -0.0342 0.0362 1.0000
19.000 1.2395 0.13105 0.12707 -0.0397 0.0359 1.0000
19.250 1.2128 0.14107 0.13732 -0.0463 0.0359 1.0000
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Polar data table (+)
Polar graphs
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