RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Reynolds number: 100,000 Max Cl/Cd: 50.62 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15a213-il-100000.txt Download as CSV file: xf-rg15a213-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4013 0.09750 0.09252 -0.0366 1.0000 0.1429
-9.250 -0.3265 0.08846 0.08392 -0.0362 1.0000 0.1559
-9.000 -0.5693 0.06841 0.06359 -0.0544 1.0000 0.0785
-8.750 -0.5793 0.06499 0.06019 -0.0524 1.0000 0.0769
-8.500 -0.6579 0.05637 0.05070 -0.0491 1.0000 0.0677
-8.250 -0.6587 0.05224 0.04650 -0.0473 1.0000 0.0670
-8.000 -0.6603 0.04851 0.04258 -0.0452 1.0000 0.0664
-7.750 -0.6601 0.04485 0.03862 -0.0432 1.0000 0.0658
-7.500 -0.6567 0.04130 0.03468 -0.0413 1.0000 0.0655
-7.250 -0.6488 0.03813 0.03106 -0.0396 1.0000 0.0656
-7.000 -0.6375 0.03559 0.02799 -0.0380 1.0000 0.0670
-6.750 -0.6234 0.03298 0.02508 -0.0368 1.0000 0.0691
-6.500 -0.6063 0.03138 0.02339 -0.0357 1.0000 0.0717
-6.250 -0.5878 0.02975 0.02154 -0.0345 1.0000 0.0742
-6.000 -0.5683 0.02820 0.01966 -0.0333 1.0000 0.0775
-5.750 -0.5489 0.02672 0.01804 -0.0323 1.0000 0.0825
-5.500 -0.5297 0.02577 0.01704 -0.0313 1.0000 0.0895
-5.250 -0.5099 0.02446 0.01571 -0.0302 1.0000 0.0980
-5.000 -0.4905 0.02346 0.01474 -0.0292 1.0000 0.1120
-4.750 -0.4714 0.02271 0.01401 -0.0283 1.0000 0.1329
-4.500 -0.4522 0.02206 0.01342 -0.0274 1.0000 0.1541
-4.250 -0.4107 0.02183 0.01333 -0.0310 0.9934 0.1881
-4.000 -0.3703 0.02149 0.01310 -0.0341 0.9857 0.2263
-3.750 -0.3321 0.02091 0.01280 -0.0367 0.9781 0.2698
-3.500 -0.2914 0.02031 0.01261 -0.0397 0.9713 0.3404
-3.250 -0.2593 0.01958 0.01246 -0.0410 0.9621 0.4376
-3.000 -0.2275 0.01929 0.01290 -0.0414 0.9537 0.5692
-2.750 -0.1929 0.01964 0.01343 -0.0418 0.9449 0.6645
-2.500 -0.1653 0.01995 0.01375 -0.0409 0.9342 0.7166
-2.250 -0.1343 0.02027 0.01404 -0.0404 0.9250 0.7575
-2.000 -0.1041 0.02050 0.01424 -0.0396 0.9157 0.7913
-1.750 -0.0831 0.02066 0.01438 -0.0371 0.9045 0.8223
-1.500 -0.0537 0.02074 0.01442 -0.0359 0.8965 0.8527
-1.250 -0.0296 0.02073 0.01436 -0.0340 0.8859 0.8782
-1.000 -0.0013 0.02071 0.01427 -0.0331 0.8757 0.9012
-0.750 0.0477 0.02061 0.01408 -0.0358 0.8695 0.9230
-0.500 0.0990 0.02061 0.01398 -0.0396 0.8612 0.9429
-0.250 0.1771 0.02045 0.01370 -0.0482 0.8570 0.9568
0.000 0.2766 0.02002 0.01315 -0.0611 0.8551 0.9646
0.250 0.3617 0.01933 0.01238 -0.0714 0.8520 0.9730
0.500 0.4216 0.01888 0.01189 -0.0775 0.8408 0.9831
0.750 0.4897 0.01817 0.01114 -0.0850 0.8317 0.9905
1.000 0.5516 0.01745 0.01037 -0.0913 0.8211 0.9976
1.250 0.5837 0.01714 0.01002 -0.0923 0.8061 1.0000
1.500 0.6060 0.01694 0.00978 -0.0913 0.7905 1.0000
1.750 0.6273 0.01678 0.00959 -0.0900 0.7748 1.0000
2.000 0.6474 0.01666 0.00942 -0.0886 0.7590 1.0000
2.250 0.6665 0.01659 0.00930 -0.0870 0.7431 1.0000
2.500 0.6846 0.01655 0.00922 -0.0852 0.7271 1.0000
2.750 0.7017 0.01656 0.00918 -0.0832 0.7111 1.0000
3.000 0.7178 0.01659 0.00916 -0.0810 0.6952 1.0000
3.250 0.7330 0.01665 0.00916 -0.0787 0.6792 1.0000
3.500 0.7480 0.01674 0.00921 -0.0763 0.6633 1.0000
3.750 0.7641 0.01686 0.00927 -0.0741 0.6472 1.0000
4.000 0.7818 0.01703 0.00937 -0.0722 0.6306 1.0000
4.250 0.8017 0.01723 0.00953 -0.0707 0.6132 1.0000
4.500 0.8235 0.01745 0.00971 -0.0695 0.5954 1.0000
4.750 0.8464 0.01768 0.00989 -0.0685 0.5776 1.0000
5.000 0.8698 0.01792 0.01008 -0.0675 0.5595 1.0000
5.250 0.8937 0.01818 0.01029 -0.0667 0.5415 1.0000
5.500 0.9179 0.01847 0.01050 -0.0659 0.5235 1.0000
5.750 0.9423 0.01878 0.01072 -0.0651 0.5056 1.0000
6.000 0.9632 0.01915 0.01109 -0.0638 0.4864 1.0000
6.250 0.9847 0.01952 0.01146 -0.0626 0.4673 1.0000
6.500 1.0065 0.01991 0.01180 -0.0614 0.4484 1.0000
6.750 1.0285 0.02032 0.01213 -0.0603 0.4296 1.0000
7.000 1.0501 0.02078 0.01252 -0.0592 0.4110 1.0000
7.250 1.0687 0.02126 0.01303 -0.0576 0.3916 1.0000
7.500 1.0879 0.02177 0.01353 -0.0561 0.3725 1.0000
7.750 1.1071 0.02232 0.01403 -0.0547 0.3540 1.0000
8.000 1.1263 0.02291 0.01457 -0.0533 0.3360 1.0000
8.250 1.1454 0.02358 0.01515 -0.0519 0.3184 1.0000
8.500 1.1619 0.02427 0.01589 -0.0502 0.3007 1.0000
8.750 1.1779 0.02501 0.01663 -0.0484 0.2833 1.0000
9.000 1.1935 0.02580 0.01743 -0.0466 0.2665 1.0000
9.250 1.2086 0.02664 0.01826 -0.0447 0.2504 1.0000
9.500 1.2218 0.02747 0.01907 -0.0426 0.2346 1.0000
9.750 1.2332 0.02831 0.01991 -0.0403 0.2194 1.0000
10.000 1.2437 0.02922 0.02080 -0.0380 0.2052 1.0000
10.250 1.2532 0.03017 0.02177 -0.0356 0.1923 1.0000
10.500 1.2633 0.03123 0.02279 -0.0333 0.1804 1.0000
10.750 1.2754 0.03238 0.02384 -0.0314 0.1688 1.0000
11.000 1.2794 0.03354 0.02517 -0.0284 0.1585 1.0000
11.250 1.2871 0.03491 0.02660 -0.0261 0.1485 1.0000
11.500 1.2978 0.03632 0.02792 -0.0244 0.1389 1.0000
11.750 1.3021 0.03778 0.02954 -0.0219 0.1303 1.0000
12.000 1.3109 0.03959 0.03142 -0.0202 0.1223 1.0000
12.250 1.3224 0.04117 0.03292 -0.0189 0.1144 1.0000
12.500 1.3247 0.04327 0.03526 -0.0167 0.1084 1.0000
12.750 1.3339 0.04499 0.03700 -0.0153 0.1027 1.0000
13.000 1.3457 0.04744 0.03955 -0.0143 0.0978 1.0000
13.250 1.3445 0.04988 0.04228 -0.0123 0.0944 1.0000
13.500 1.3498 0.05205 0.04458 -0.0111 0.0909 1.0000
13.750 1.3687 0.05470 0.04717 -0.0110 0.0868 1.0000
14.000 1.3550 0.05770 0.05054 -0.0088 0.0854 1.0000
14.250 1.3419 0.06112 0.05427 -0.0074 0.0838 1.0000
14.500 1.3287 0.06490 0.05834 -0.0065 0.0825 1.0000
14.750 1.3141 0.06905 0.06276 -0.0061 0.0814 1.0000
15.000 1.2978 0.07360 0.06754 -0.0063 0.0805 1.0000
15.250 1.2765 0.07891 0.07311 -0.0073 0.0799 1.0000
15.500 1.2398 0.08642 0.08093 -0.0098 0.0803 1.0000
15.750 1.1773 0.09863 0.09351 -0.0162 0.0824 1.0000
16.000 1.1047 0.11541 0.11052 -0.0265 0.0852 1.0000
16.250 1.0373 0.13516 0.13037 -0.0385 0.0875 1.0000
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