RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Reynolds number: 100,000 Max Cl/Cd: 51.25 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg15a213-il-100000-n5.txt Download as CSV file: xf-rg15a213-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4940 0.09120 0.08588 -0.0489 1.0000 0.0311
-11.250 -0.5323 0.07831 0.07302 -0.0559 1.0000 0.0305
-11.000 -0.5852 0.06500 0.05962 -0.0654 1.0000 0.0292
-10.750 -0.6274 0.05775 0.05220 -0.0689 1.0000 0.0287
-10.500 -0.6629 0.05345 0.04774 -0.0681 1.0000 0.0283
-10.250 -0.6906 0.05092 0.04509 -0.0645 1.0000 0.0283
-10.000 -0.7076 0.04829 0.04229 -0.0615 1.0000 0.0285
-9.750 -0.7193 0.04577 0.03956 -0.0585 1.0000 0.0289
-9.500 -0.7268 0.04322 0.03675 -0.0555 1.0000 0.0294
-9.250 -0.7301 0.04069 0.03393 -0.0528 1.0000 0.0298
-9.000 -0.7292 0.03824 0.03115 -0.0503 1.0000 0.0304
-8.750 -0.7242 0.03599 0.02856 -0.0479 1.0000 0.0309
-8.500 -0.7160 0.03394 0.02613 -0.0458 1.0000 0.0317
-8.250 -0.7049 0.03247 0.02457 -0.0440 1.0000 0.0327
-8.000 -0.6920 0.03147 0.02352 -0.0424 1.0000 0.0340
-7.750 -0.6675 0.03014 0.02200 -0.0429 0.9973 0.0360
-7.500 -0.6363 0.02855 0.02011 -0.0443 0.9931 0.0379
-7.250 -0.6065 0.02710 0.01851 -0.0455 0.9883 0.0397
-7.000 -0.5742 0.02608 0.01744 -0.0473 0.9838 0.0425
-6.750 -0.5441 0.02509 0.01626 -0.0482 0.9783 0.0465
-6.500 -0.5127 0.02406 0.01523 -0.0497 0.9731 0.0507
-6.250 -0.4821 0.02311 0.01415 -0.0507 0.9676 0.0568
-6.000 -0.4516 0.02227 0.01331 -0.0518 0.9615 0.0664
-5.750 -0.4180 0.02152 0.01255 -0.0534 0.9567 0.0807
-5.500 -0.3896 0.02086 0.01187 -0.0540 0.9492 0.0948
-5.250 -0.3546 0.02025 0.01131 -0.0559 0.9445 0.1128
-5.000 -0.3266 0.01980 0.01090 -0.0563 0.9367 0.1366
-4.750 -0.2925 0.01924 0.01043 -0.0579 0.9312 0.1622
-4.500 -0.2626 0.01873 0.00998 -0.0586 0.9242 0.1868
-4.250 -0.2303 0.01821 0.00954 -0.0597 0.9177 0.2168
-4.000 -0.1942 0.01765 0.00910 -0.0615 0.9133 0.2570
-3.750 -0.1679 0.01719 0.00879 -0.0614 0.9042 0.3004
-3.500 -0.1319 0.01660 0.00842 -0.0631 0.8995 0.3604
-3.250 -0.1056 0.01614 0.00820 -0.0629 0.8905 0.4224
-3.000 -0.0718 0.01568 0.00804 -0.0638 0.8849 0.4977
-2.750 -0.0453 0.01548 0.00808 -0.0631 0.8760 0.5663
-2.500 -0.0124 0.01536 0.00803 -0.0634 0.8694 0.6268
-2.250 0.0147 0.01534 0.00803 -0.0626 0.8599 0.6668
-2.000 0.0481 0.01527 0.00792 -0.0630 0.8530 0.6985
-1.750 0.0750 0.01525 0.00784 -0.0624 0.8425 0.7210
-1.500 0.1088 0.01516 0.00769 -0.0628 0.8353 0.7408
-1.250 0.1348 0.01514 0.00764 -0.0619 0.8242 0.7584
-1.000 0.1627 0.01510 0.00755 -0.0613 0.8139 0.7753
-0.750 0.1945 0.01501 0.00740 -0.0614 0.8050 0.7913
-0.500 0.2197 0.01499 0.00734 -0.0604 0.7928 0.8063
-0.250 0.2466 0.01495 0.00726 -0.0597 0.7813 0.8207
0.000 0.2753 0.01489 0.00714 -0.0593 0.7704 0.8348
0.250 0.3029 0.01483 0.00703 -0.0586 0.7587 0.8479
0.500 0.3283 0.01480 0.00698 -0.0576 0.7457 0.8604
0.750 0.3548 0.01477 0.00691 -0.0569 0.7328 0.8727
1.000 0.3822 0.01474 0.00683 -0.0565 0.7199 0.8847
1.250 0.4101 0.01471 0.00675 -0.0561 0.7068 0.8968
1.500 0.4401 0.01469 0.00668 -0.0562 0.6935 0.9073
1.750 0.4702 0.01469 0.00664 -0.0564 0.6794 0.9180
2.000 0.5005 0.01472 0.00662 -0.0568 0.6644 0.9290
2.250 0.5330 0.01476 0.00663 -0.0577 0.6493 0.9392
2.500 0.5675 0.01482 0.00665 -0.0590 0.6336 0.9490
2.750 0.6023 0.01490 0.00668 -0.0604 0.6175 0.9596
3.000 0.6377 0.01500 0.00674 -0.0621 0.6010 0.9708
3.250 0.6740 0.01513 0.00681 -0.0640 0.5840 0.9832
3.500 0.7090 0.01527 0.00693 -0.0657 0.5662 1.0000
3.750 0.7255 0.01543 0.00703 -0.0638 0.5510 1.0000
4.000 0.7455 0.01563 0.00716 -0.0626 0.5352 1.0000
4.250 0.7672 0.01586 0.00733 -0.0616 0.5191 1.0000
4.500 0.7897 0.01611 0.00754 -0.0608 0.5028 1.0000
4.750 0.8124 0.01638 0.00776 -0.0599 0.4862 1.0000
5.000 0.8351 0.01667 0.00801 -0.0591 0.4697 1.0000
5.250 0.8576 0.01699 0.00830 -0.0583 0.4531 1.0000
5.500 0.8800 0.01732 0.00859 -0.0574 0.4364 1.0000
5.750 0.9020 0.01767 0.00891 -0.0565 0.4198 1.0000
6.000 0.9237 0.01804 0.00926 -0.0555 0.4033 1.0000
6.250 0.9451 0.01844 0.00964 -0.0545 0.3869 1.0000
6.500 0.9659 0.01885 0.01003 -0.0534 0.3703 1.0000
6.750 0.9862 0.01929 0.01045 -0.0522 0.3538 1.0000
7.000 1.0058 0.01976 0.01089 -0.0510 0.3371 1.0000
7.250 1.0249 0.02026 0.01138 -0.0497 0.3208 1.0000
7.500 1.0434 0.02078 0.01188 -0.0483 0.3046 1.0000
7.750 1.0612 0.02133 0.01242 -0.0469 0.2889 1.0000
8.000 1.0785 0.02191 0.01301 -0.0453 0.2735 1.0000
8.250 1.0952 0.02251 0.01362 -0.0438 0.2589 1.0000
8.500 1.1111 0.02314 0.01427 -0.0421 0.2448 1.0000
8.750 1.1257 0.02379 0.01495 -0.0402 0.2316 1.0000
9.000 1.1393 0.02449 0.01568 -0.0383 0.2188 1.0000
9.250 1.1521 0.02526 0.01648 -0.0363 0.2066 1.0000
9.500 1.1638 0.02609 0.01731 -0.0342 0.1950 1.0000
9.750 1.1740 0.02700 0.01821 -0.0321 0.1835 1.0000
10.000 1.1843 0.02793 0.01918 -0.0301 0.1709 1.0000
10.250 1.1935 0.02894 0.02023 -0.0281 0.1586 1.0000
10.500 1.2020 0.03004 0.02137 -0.0261 0.1475 1.0000
10.750 1.2090 0.03126 0.02260 -0.0242 0.1380 1.0000
11.000 1.2161 0.03254 0.02393 -0.0224 0.1291 1.0000
11.250 1.2234 0.03389 0.02536 -0.0208 0.1213 1.0000
11.500 1.2278 0.03545 0.02695 -0.0191 0.1144 1.0000
11.750 1.2341 0.03699 0.02861 -0.0177 0.1074 1.0000
12.000 1.2366 0.03883 0.03050 -0.0163 0.1015 1.0000
12.250 1.2410 0.04066 0.03245 -0.0151 0.0955 1.0000
12.500 1.2428 0.04274 0.03461 -0.0141 0.0902 1.0000
12.750 1.2434 0.04504 0.03696 -0.0132 0.0860 1.0000
13.000 1.2458 0.04730 0.03938 -0.0125 0.0813 1.0000
13.250 1.2448 0.04994 0.04209 -0.0121 0.0777 1.0000
13.500 1.2435 0.05272 0.04492 -0.0117 0.0744 1.0000
13.750 1.2439 0.05548 0.04786 -0.0116 0.0707 1.0000
14.000 1.2423 0.05851 0.05100 -0.0117 0.0677 1.0000
14.250 1.2388 0.06182 0.05435 -0.0121 0.0653 1.0000
14.500 1.2374 0.06505 0.05771 -0.0124 0.0630 1.0000
14.750 1.2364 0.06839 0.06124 -0.0129 0.0607 1.0000
15.000 1.2345 0.07191 0.06490 -0.0136 0.0587 1.0000
15.250 1.2320 0.07557 0.06867 -0.0145 0.0570 1.0000
15.500 1.2295 0.07930 0.07248 -0.0155 0.0555 1.0000
15.750 1.2291 0.08269 0.07587 -0.0163 0.0540 1.0000
16.000 1.2231 0.08730 0.08074 -0.0180 0.0527 1.0000
16.250 1.2164 0.09213 0.08579 -0.0199 0.0514 1.0000
16.500 1.2084 0.09731 0.09116 -0.0222 0.0502 1.0000
16.750 1.2001 0.10265 0.09668 -0.0247 0.0491 1.0000
17.000 1.1916 0.10811 0.10230 -0.0273 0.0481 1.0000
17.250 1.1830 0.11374 0.10807 -0.0302 0.0473 1.0000
17.500 1.1753 0.11928 0.11373 -0.0332 0.0465 1.0000
17.750 1.1710 0.12411 0.11864 -0.0357 0.0456 1.0000
18.000 1.1671 0.12892 0.12350 -0.0382 0.0448 1.0000
18.250 1.1416 0.13895 0.13377 -0.0446 0.0445 1.0000
18.500 1.1029 0.15285 0.14791 -0.0536 0.0445 1.0000
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Polar data table (+)
Polar graphs
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