ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 13% AIRFOIL (arad13-il) Reynolds number: 500,000 Max Cl/Cd: 79.39 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad13-il-500000-n5.txt Download as CSV file: xf-arad13-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 13% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -1.0970 0.04629 0.04234 -0.0520 1.0000 0.0144
-14.000 -1.1211 0.04076 0.03655 -0.0527 1.0000 0.0144
-13.750 -1.1221 0.03758 0.03316 -0.0524 1.0000 0.0145
-13.500 -1.1160 0.03505 0.03048 -0.0519 1.0000 0.0146
-13.250 -1.1044 0.03300 0.02830 -0.0513 1.0000 0.0148
-13.000 -1.0890 0.03129 0.02647 -0.0509 1.0000 0.0149
-12.750 -1.0712 0.02981 0.02486 -0.0505 1.0000 0.0151
-12.500 -1.0516 0.02848 0.02342 -0.0501 1.0000 0.0153
-12.250 -1.0306 0.02726 0.02209 -0.0497 1.0000 0.0155
-12.000 -1.0085 0.02614 0.02087 -0.0494 1.0000 0.0157
-11.750 -0.9856 0.02509 0.01971 -0.0492 1.0000 0.0160
-11.500 -0.9620 0.02411 0.01863 -0.0489 1.0000 0.0163
-11.250 -0.9376 0.02319 0.01759 -0.0487 1.0000 0.0166
-11.000 -0.9126 0.02233 0.01663 -0.0485 1.0000 0.0169
-10.750 -0.8871 0.02154 0.01573 -0.0484 1.0000 0.0171
-10.500 -0.8615 0.02069 0.01484 -0.0483 1.0000 0.0175
-10.250 -0.8352 0.01999 0.01409 -0.0482 1.0000 0.0180
-10.000 -0.8084 0.01936 0.01341 -0.0481 1.0000 0.0184
-9.750 -0.7813 0.01877 0.01275 -0.0481 1.0000 0.0190
-9.500 -0.7539 0.01819 0.01210 -0.0480 1.0000 0.0196
-9.250 -0.7264 0.01762 0.01147 -0.0480 1.0000 0.0202
-9.000 -0.6989 0.01704 0.01088 -0.0480 1.0000 0.0208
-8.750 -0.6710 0.01655 0.01035 -0.0480 1.0000 0.0215
-8.500 -0.6380 0.01609 0.00984 -0.0491 0.9810 0.0224
-8.250 -0.6057 0.01567 0.00935 -0.0499 0.9610 0.0233
-8.000 -0.5761 0.01528 0.00893 -0.0501 0.9397 0.0243
-7.750 -0.5491 0.01499 0.00856 -0.0496 0.9180 0.0255
-7.500 -0.5225 0.01471 0.00818 -0.0490 0.8974 0.0267
-7.250 -0.4957 0.01442 0.00784 -0.0485 0.8778 0.0280
-7.000 -0.4682 0.01419 0.00751 -0.0481 0.8596 0.0297
-6.750 -0.4404 0.01394 0.00718 -0.0479 0.8423 0.0313
-6.500 -0.4122 0.01373 0.00689 -0.0477 0.8257 0.0332
-6.250 -0.3836 0.01350 0.00659 -0.0475 0.8099 0.0350
-6.000 -0.3549 0.01329 0.00632 -0.0475 0.7949 0.0371
-5.750 -0.3260 0.01310 0.00605 -0.0474 0.7806 0.0391
-5.500 -0.2971 0.01291 0.00580 -0.0474 0.7661 0.0414
-5.250 -0.2679 0.01273 0.00556 -0.0474 0.7519 0.0439
-5.000 -0.2386 0.01255 0.00534 -0.0475 0.7382 0.0467
-4.750 -0.2093 0.01240 0.00513 -0.0475 0.7246 0.0497
-4.500 -0.1800 0.01226 0.00494 -0.0476 0.7106 0.0531
-4.250 -0.1505 0.01210 0.00475 -0.0477 0.6964 0.0566
-4.000 -0.1210 0.01199 0.00458 -0.0478 0.6817 0.0604
-3.750 -0.0916 0.01187 0.00441 -0.0479 0.6653 0.0645
-3.500 -0.0620 0.01178 0.00426 -0.0480 0.6482 0.0691
-3.250 -0.0325 0.01169 0.00412 -0.0481 0.6324 0.0744
-3.000 -0.0028 0.01160 0.00400 -0.0483 0.6175 0.0801
-2.750 0.0269 0.01152 0.00388 -0.0485 0.6031 0.0862
-2.500 0.0566 0.01146 0.00379 -0.0486 0.5889 0.0931
-2.250 0.0863 0.01140 0.00370 -0.0488 0.5746 0.1003
-2.000 0.1160 0.01136 0.00362 -0.0490 0.5597 0.1077
-1.750 0.1458 0.01132 0.00356 -0.0492 0.5449 0.1160
-1.500 0.1755 0.01129 0.00350 -0.0494 0.5298 0.1247
-1.250 0.2053 0.01129 0.00345 -0.0496 0.5143 0.1334
-1.000 0.2350 0.01128 0.00342 -0.0498 0.4990 0.1436
-0.750 0.2646 0.01128 0.00339 -0.0501 0.4836 0.1545
-0.500 0.2944 0.01128 0.00337 -0.0503 0.4690 0.1670
-0.250 0.3240 0.01129 0.00336 -0.0505 0.4533 0.1819
0.000 0.3537 0.01130 0.00336 -0.0508 0.4367 0.1994
0.250 0.3832 0.01130 0.00338 -0.0511 0.4208 0.2223
0.500 0.4128 0.01129 0.00340 -0.0513 0.4049 0.2545
0.750 0.4422 0.01120 0.00343 -0.0517 0.3871 0.3174
1.000 0.4710 0.01080 0.00349 -0.0522 0.3685 0.5011
1.250 0.4981 0.01026 0.00360 -0.0522 0.3515 0.7224
1.500 0.5152 0.00979 0.00365 -0.0490 0.3374 0.9300
1.750 0.5490 0.00978 0.00356 -0.0501 0.3197 1.0000
2.000 0.5782 0.01000 0.00365 -0.0503 0.3037 1.0000
2.500 0.6365 0.01041 0.00387 -0.0507 0.2779 1.0000
2.750 0.6655 0.01062 0.00399 -0.0509 0.2666 1.0000
3.250 0.7236 0.01104 0.00426 -0.0513 0.2466 1.0000
3.500 0.7524 0.01128 0.00441 -0.0515 0.2380 1.0000
3.750 0.7814 0.01147 0.00455 -0.0517 0.2300 1.0000
4.000 0.8101 0.01172 0.00472 -0.0519 0.2219 1.0000
4.250 0.8390 0.01190 0.00488 -0.0521 0.2157 1.0000
4.500 0.8675 0.01214 0.00506 -0.0523 0.2089 1.0000
4.750 0.8961 0.01237 0.00524 -0.0524 0.2030 1.0000
5.000 0.9246 0.01259 0.00543 -0.0526 0.1970 1.0000
5.250 0.9527 0.01286 0.00564 -0.0527 0.1915 1.0000
5.500 0.9812 0.01307 0.00585 -0.0528 0.1869 1.0000
5.750 1.0093 0.01332 0.00606 -0.0530 0.1817 1.0000
6.000 1.0370 0.01361 0.00630 -0.0530 0.1770 1.0000
6.250 1.0650 0.01384 0.00653 -0.0531 0.1732 1.0000
6.500 1.0928 0.01409 0.00677 -0.0532 0.1690 1.0000
6.750 1.1202 0.01438 0.00703 -0.0533 0.1649 1.0000
7.000 1.1474 0.01468 0.00732 -0.0533 0.1614 1.0000
7.250 1.1748 0.01493 0.00758 -0.0533 0.1582 1.0000
7.500 1.2019 0.01521 0.00786 -0.0533 0.1545 1.0000
7.750 1.2284 0.01554 0.00817 -0.0533 0.1508 1.0000
8.000 1.2548 0.01587 0.00850 -0.0532 0.1479 1.0000
8.250 1.2814 0.01615 0.00880 -0.0531 0.1451 1.0000
8.500 1.3076 0.01647 0.00912 -0.0530 0.1418 1.0000
8.750 1.3332 0.01683 0.00947 -0.0528 0.1384 1.0000
9.000 1.3582 0.01723 0.00987 -0.0526 0.1355 1.0000
9.250 1.3838 0.01754 0.01022 -0.0524 0.1332 1.0000
9.500 1.4088 0.01789 0.01060 -0.0521 0.1303 1.0000
9.750 1.4331 0.01829 0.01100 -0.0518 0.1272 1.0000
10.000 1.4564 0.01875 0.01146 -0.0513 0.1244 1.0000
10.250 1.4802 0.01914 0.01189 -0.0509 0.1222 1.0000
10.500 1.5035 0.01954 0.01233 -0.0504 0.1197 1.0000
10.750 1.5258 0.01999 0.01280 -0.0498 0.1169 1.0000
11.000 1.5469 0.02051 0.01333 -0.0490 0.1143 1.0000
11.250 1.5671 0.02105 0.01389 -0.0481 0.1121 1.0000
11.500 1.5878 0.02152 0.01442 -0.0472 0.1101 1.0000
11.750 1.6070 0.02205 0.01499 -0.0462 0.1077 1.0000
12.000 1.6245 0.02265 0.01563 -0.0449 0.1054 1.0000
12.250 1.6397 0.02335 0.01635 -0.0434 0.1034 1.0000
12.500 1.6516 0.02409 0.01715 -0.0412 0.1017 1.0000
12.750 1.6633 0.02484 0.01797 -0.0392 0.1000 1.0000
13.000 1.6744 0.02571 0.01891 -0.0373 0.0982 1.0000
13.250 1.6849 0.02672 0.01997 -0.0355 0.0964 1.0000
13.500 1.6944 0.02788 0.02118 -0.0339 0.0947 1.0000
13.750 1.7021 0.02927 0.02261 -0.0325 0.0930 1.0000
14.000 1.7122 0.03056 0.02399 -0.0314 0.0916 1.0000
14.250 1.7221 0.03194 0.02546 -0.0304 0.0901 1.0000
14.500 1.7305 0.03351 0.02711 -0.0296 0.0885 1.0000
14.750 1.7375 0.03529 0.02896 -0.0288 0.0870 1.0000
15.000 1.7427 0.03733 0.03105 -0.0283 0.0855 1.0000
15.250 1.7452 0.03970 0.03348 -0.0278 0.0840 1.0000
15.500 1.7500 0.04189 0.03578 -0.0275 0.0829 1.0000
15.750 1.7544 0.04419 0.03818 -0.0273 0.0817 1.0000
16.000 1.7569 0.04675 0.04083 -0.0272 0.0804 1.0000
16.250 1.7573 0.04959 0.04376 -0.0273 0.0790 1.0000
16.500 1.7552 0.05277 0.04702 -0.0275 0.0778 1.0000
16.750 1.7505 0.05634 0.05068 -0.0279 0.0767 1.0000
17.000 1.7429 0.06032 0.05475 -0.0285 0.0757 1.0000
17.250 1.7390 0.06393 0.05847 -0.0291 0.0748 1.0000
17.500 1.7347 0.06769 0.06235 -0.0298 0.0738 1.0000
17.750 1.7284 0.07180 0.06658 -0.0308 0.0728 1.0000
18.000 1.7199 0.07626 0.07114 -0.0319 0.0717 1.0000
18.250 1.7095 0.08107 0.07606 -0.0333 0.0707 1.0000
18.500 1.6972 0.08624 0.08132 -0.0349 0.0698 1.0000
18.750 1.6831 0.09177 0.08695 -0.0367 0.0689 1.0000
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