ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: ARA-D 13% AIRFOIL (arad13-il) Reynolds number: 500,000 Max Cl/Cd: 78.61 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad13-il-500000.txt Download as CSV file: xf-arad13-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.9499 0.04584 0.04240 -0.0528 1.0000 0.0209
-12.500 -0.9653 0.04131 0.03758 -0.0528 1.0000 0.0209
-12.250 -0.9635 0.03824 0.03428 -0.0524 1.0000 0.0211
-12.000 -0.9549 0.03573 0.03157 -0.0520 1.0000 0.0213
-11.750 -0.9425 0.03348 0.02910 -0.0515 1.0000 0.0215
-11.500 -0.9269 0.03151 0.02694 -0.0510 1.0000 0.0218
-11.250 -0.9093 0.02964 0.02486 -0.0506 1.0000 0.0221
-11.000 -0.8898 0.02794 0.02294 -0.0502 1.0000 0.0225
-10.750 -0.8685 0.02641 0.02118 -0.0499 1.0000 0.0228
-10.500 -0.8455 0.02515 0.01969 -0.0496 1.0000 0.0232
-10.250 -0.8235 0.02352 0.01796 -0.0493 1.0000 0.0236
-10.000 -0.7985 0.02261 0.01703 -0.0492 1.0000 0.0241
-9.750 -0.7726 0.02183 0.01620 -0.0490 1.0000 0.0246
-9.500 -0.7464 0.02103 0.01532 -0.0489 1.0000 0.0252
-9.250 -0.7198 0.02026 0.01441 -0.0488 1.0000 0.0260
-9.000 -0.6931 0.01944 0.01345 -0.0487 1.0000 0.0268
-8.750 -0.6666 0.01864 0.01267 -0.0487 1.0000 0.0276
-8.500 -0.6392 0.01810 0.01212 -0.0486 1.0000 0.0285
-8.250 -0.6116 0.01750 0.01144 -0.0485 1.0000 0.0295
-8.000 -0.5845 0.01680 0.01066 -0.0484 1.0000 0.0306
-7.750 -0.5576 0.01626 0.01016 -0.0483 1.0000 0.0318
-7.500 -0.5315 0.01585 0.00972 -0.0480 1.0000 0.0333
-7.250 -0.4986 0.01525 0.00908 -0.0490 0.9952 0.0350
-7.000 -0.4617 0.01484 0.00868 -0.0509 0.9856 0.0370
-6.750 -0.4262 0.01438 0.00816 -0.0524 0.9727 0.0395
-6.500 -0.3937 0.01411 0.00789 -0.0531 0.9557 0.0419
-6.250 -0.3660 0.01378 0.00750 -0.0527 0.9357 0.0444
-6.000 -0.3400 0.01357 0.00726 -0.0518 0.9150 0.0468
-5.750 -0.3137 0.01331 0.00690 -0.0511 0.8956 0.0495
-5.500 -0.2868 0.01310 0.00665 -0.0505 0.8773 0.0522
-5.250 -0.2593 0.01288 0.00635 -0.0501 0.8600 0.0554
-5.000 -0.2314 0.01271 0.00613 -0.0497 0.8432 0.0587
-4.750 -0.2030 0.01249 0.00585 -0.0495 0.8267 0.0623
-4.500 -0.1743 0.01235 0.00567 -0.0494 0.8106 0.0662
-4.250 -0.1455 0.01213 0.00541 -0.0493 0.7950 0.0704
-4.000 -0.1165 0.01203 0.00523 -0.0492 0.7791 0.0749
-3.750 -0.0876 0.01182 0.00500 -0.0492 0.7626 0.0800
-3.500 -0.0584 0.01171 0.00480 -0.0491 0.7461 0.0855
-3.250 -0.0291 0.01157 0.00464 -0.0492 0.7302 0.0920
-3.000 0.0004 0.01141 0.00447 -0.0493 0.7151 0.0994
-2.750 0.0299 0.01132 0.00433 -0.0493 0.7005 0.1072
-2.500 0.0594 0.01123 0.00422 -0.0494 0.6861 0.1158
-2.250 0.0889 0.01113 0.00410 -0.0496 0.6716 0.1252
-2.000 0.1187 0.01105 0.00399 -0.0497 0.6570 0.1347
-1.750 0.1484 0.01099 0.00391 -0.0499 0.6428 0.1450
-1.500 0.1780 0.01091 0.00382 -0.0500 0.6286 0.1566
-1.000 0.2374 0.01080 0.00367 -0.0504 0.5993 0.1827
-0.750 0.2671 0.01073 0.00362 -0.0506 0.5852 0.2004
-0.500 0.2968 0.01064 0.00357 -0.0508 0.5716 0.2250
-0.250 0.3264 0.01052 0.00353 -0.0511 0.5570 0.2658
0.000 0.3556 0.01005 0.00351 -0.0516 0.5419 0.4112
0.250 0.3802 0.00891 0.00358 -0.0510 0.5281 0.7781
0.500 0.3990 0.00847 0.00350 -0.0479 0.5150 0.9582
0.750 0.4357 0.00843 0.00335 -0.0496 0.4981 1.0000
1.000 0.4650 0.00858 0.00337 -0.0498 0.4814 1.0000
1.250 0.4942 0.00873 0.00340 -0.0499 0.4646 1.0000
1.500 0.5235 0.00890 0.00344 -0.0501 0.4474 1.0000
1.750 0.5528 0.00907 0.00350 -0.0503 0.4289 1.0000
2.000 0.5820 0.00926 0.00357 -0.0505 0.4094 1.0000
2.250 0.6111 0.00947 0.00366 -0.0507 0.3897 1.0000
2.500 0.6402 0.00969 0.00376 -0.0508 0.3698 1.0000
2.750 0.6691 0.00994 0.00388 -0.0510 0.3494 1.0000
3.000 0.6979 0.01020 0.00401 -0.0512 0.3302 1.0000
3.250 0.7267 0.01046 0.00416 -0.0514 0.3133 1.0000
3.500 0.7555 0.01073 0.00433 -0.0516 0.2982 1.0000
3.750 0.7841 0.01100 0.00450 -0.0518 0.2844 1.0000
4.000 0.8125 0.01131 0.00470 -0.0519 0.2717 1.0000
4.250 0.8413 0.01153 0.00488 -0.0521 0.2613 1.0000
4.500 0.8697 0.01181 0.00509 -0.0523 0.2517 1.0000
4.750 0.8981 0.01208 0.00530 -0.0524 0.2424 1.0000
5.000 0.9264 0.01235 0.00551 -0.0525 0.2346 1.0000
5.250 0.9546 0.01262 0.00573 -0.0527 0.2271 1.0000
5.500 0.9825 0.01292 0.00599 -0.0528 0.2202 1.0000
5.750 1.0107 0.01316 0.00621 -0.0529 0.2140 1.0000
6.000 1.0381 0.01351 0.00649 -0.0529 0.2077 1.0000
6.250 1.0660 0.01375 0.00675 -0.0530 0.2028 1.0000
6.500 1.0937 0.01403 0.00700 -0.0531 0.1975 1.0000
6.750 1.1204 0.01442 0.00733 -0.0530 0.1922 1.0000
7.000 1.1479 0.01469 0.00762 -0.0531 0.1883 1.0000
7.250 1.1752 0.01495 0.00789 -0.0531 0.1839 1.0000
7.500 1.2016 0.01531 0.00821 -0.0530 0.1794 1.0000
7.750 1.2276 0.01573 0.00861 -0.0528 0.1753 1.0000
8.000 1.2546 0.01598 0.00890 -0.0528 0.1720 1.0000
8.250 1.2809 0.01630 0.00923 -0.0527 0.1682 1.0000
8.500 1.3059 0.01674 0.00963 -0.0525 0.1642 1.0000
8.750 1.3310 0.01716 0.01006 -0.0522 0.1607 1.0000
9.000 1.3569 0.01745 0.01040 -0.0520 0.1578 1.0000
9.250 1.3821 0.01781 0.01078 -0.0518 0.1545 1.0000
9.500 1.4057 0.01829 0.01123 -0.0513 0.1509 1.0000
9.750 1.4286 0.01882 0.01176 -0.0508 0.1477 1.0000
10.000 1.4533 0.01914 0.01215 -0.0505 0.1451 1.0000
10.250 1.4769 0.01953 0.01258 -0.0500 0.1421 1.0000
10.500 1.4989 0.02002 0.01306 -0.0494 0.1391 1.0000
10.750 1.5176 0.02076 0.01378 -0.0482 0.1357 1.0000
11.000 1.5404 0.02111 0.01422 -0.0477 0.1337 1.0000
11.250 1.5618 0.02155 0.01472 -0.0469 0.1311 1.0000
11.500 1.5814 0.02206 0.01526 -0.0459 0.1285 1.0000
11.750 1.5979 0.02275 0.01594 -0.0445 0.1259 1.0000
12.000 1.6115 0.02359 0.01681 -0.0427 0.1234 1.0000
12.250 1.6281 0.02413 0.01744 -0.0412 0.1215 1.0000
12.500 1.6405 0.02481 0.01819 -0.0392 0.1195 1.0000
12.750 1.6518 0.02562 0.01906 -0.0372 0.1174 1.0000
13.000 1.6613 0.02664 0.02011 -0.0352 0.1154 1.0000
13.250 1.6669 0.02805 0.02152 -0.0331 0.1132 1.0000
13.500 1.6779 0.02918 0.02274 -0.0318 0.1116 1.0000
13.750 1.6900 0.03027 0.02394 -0.0307 0.1098 1.0000
14.000 1.7009 0.03152 0.02528 -0.0298 0.1080 1.0000
14.250 1.7098 0.03299 0.02680 -0.0288 0.1062 1.0000
14.500 1.7161 0.03476 0.02861 -0.0279 0.1045 1.0000
14.750 1.7179 0.03700 0.03087 -0.0269 0.1026 1.0000
15.000 1.7259 0.03875 0.03274 -0.0264 0.1012 1.0000
15.250 1.7336 0.04060 0.03470 -0.0261 0.0997 1.0000
15.500 1.7396 0.04266 0.03685 -0.0258 0.0982 1.0000
15.750 1.7439 0.04494 0.03921 -0.0256 0.0967 1.0000
16.000 1.7454 0.04754 0.04186 -0.0255 0.0952 1.0000
16.250 1.7434 0.05052 0.04488 -0.0254 0.0937 1.0000
16.500 1.7412 0.05354 0.04797 -0.0252 0.0923 1.0000
16.750 1.7426 0.05635 0.05092 -0.0255 0.0912 1.0000
17.000 1.7423 0.05938 0.05407 -0.0259 0.0900 1.0000
17.250 1.7409 0.06264 0.05743 -0.0264 0.0887 1.0000
17.500 1.7382 0.06612 0.06101 -0.0271 0.0874 1.0000
17.750 1.7337 0.06988 0.06483 -0.0280 0.0862 1.0000
18.000 1.7273 0.07385 0.06885 -0.0288 0.0850 1.0000
18.250 1.7209 0.07769 0.07272 -0.0294 0.0836 1.0000
18.500 1.7152 0.08191 0.07710 -0.0307 0.0828 1.0000
18.750 1.7086 0.08628 0.08160 -0.0321 0.0817 1.0000
19.000 1.7012 0.09077 0.08620 -0.0336 0.0806 1.0000
19.250 1.6934 0.09535 0.09089 -0.0353 0.0795 1.0000
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