ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 13% AIRFOIL (arad13-il) Reynolds number: 200,000 Max Cl/Cd: 58.35 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad13-il-200000-n5.txt Download as CSV file: xf-arad13-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4997 0.13517 0.13122 0.0056 1.0000 0.0231
-12.000 -0.4994 0.13014 0.12621 0.0035 1.0000 0.0233
-11.000 -0.8093 0.04473 0.03995 -0.0496 1.0000 0.0239
-10.750 -0.8073 0.04066 0.03555 -0.0502 1.0000 0.0242
-10.500 -0.7977 0.03750 0.03209 -0.0503 1.0000 0.0246
-10.250 -0.7843 0.03469 0.02895 -0.0503 1.0000 0.0252
-10.000 -0.7681 0.03207 0.02596 -0.0502 1.0000 0.0258
-9.750 -0.7496 0.02962 0.02309 -0.0500 1.0000 0.0265
-9.500 -0.7266 0.02848 0.02190 -0.0499 1.0000 0.0270
-9.250 -0.7025 0.02750 0.02086 -0.0497 1.0000 0.0277
-9.000 -0.6781 0.02643 0.01966 -0.0496 1.0000 0.0286
-8.750 -0.6538 0.02513 0.01811 -0.0494 1.0000 0.0299
-8.500 -0.6286 0.02422 0.01713 -0.0493 1.0000 0.0309
-8.250 -0.6028 0.02349 0.01636 -0.0492 1.0000 0.0320
-8.000 -0.5773 0.02259 0.01532 -0.0490 1.0000 0.0334
-7.750 -0.5519 0.02169 0.01430 -0.0487 1.0000 0.0347
-7.500 -0.5268 0.02109 0.01370 -0.0484 1.0000 0.0359
-7.250 -0.4964 0.02039 0.01289 -0.0491 0.9932 0.0379
-7.000 -0.4611 0.01975 0.01220 -0.0508 0.9800 0.0400
-6.750 -0.4263 0.01917 0.01153 -0.0523 0.9656 0.0425
-6.500 -0.3926 0.01862 0.01093 -0.0534 0.9497 0.0449
-6.250 -0.3605 0.01817 0.01039 -0.0541 0.9327 0.0478
-6.000 -0.3307 0.01775 0.00993 -0.0543 0.9144 0.0505
-5.750 -0.3022 0.01740 0.00949 -0.0541 0.8962 0.0537
-5.500 -0.2747 0.01707 0.00911 -0.0537 0.8784 0.0567
-5.250 -0.2475 0.01677 0.00870 -0.0532 0.8613 0.0602
-5.000 -0.2204 0.01648 0.00838 -0.0527 0.8446 0.0635
-4.750 -0.1928 0.01621 0.00799 -0.0523 0.8283 0.0676
-4.500 -0.1651 0.01594 0.00771 -0.0520 0.8128 0.0714
-4.250 -0.1371 0.01570 0.00737 -0.0516 0.7977 0.0761
-4.000 -0.1091 0.01548 0.00712 -0.0514 0.7832 0.0809
-3.750 -0.0808 0.01526 0.00684 -0.0511 0.7683 0.0862
-3.500 -0.0522 0.01508 0.00660 -0.0510 0.7534 0.0924
-3.250 -0.0237 0.01489 0.00638 -0.0509 0.7385 0.0986
-3.000 0.0049 0.01475 0.00616 -0.0507 0.7234 0.1060
-2.750 0.0335 0.01461 0.00597 -0.0506 0.7073 0.1137
-2.500 0.0622 0.01448 0.00579 -0.0505 0.6908 0.1220
-2.250 0.0912 0.01438 0.00562 -0.0505 0.6745 0.1313
-2.000 0.1202 0.01425 0.00549 -0.0505 0.6592 0.1411
-1.750 0.1492 0.01415 0.00535 -0.0505 0.6442 0.1518
-1.500 0.1782 0.01409 0.00523 -0.0505 0.6294 0.1639
-1.250 0.2072 0.01400 0.00512 -0.0505 0.6144 0.1777
-1.000 0.2364 0.01390 0.00503 -0.0506 0.5990 0.1934
-0.750 0.2655 0.01382 0.00495 -0.0507 0.5838 0.2125
0.000 0.3519 0.01324 0.00477 -0.0512 0.5371 0.3768
0.250 0.3763 0.01237 0.00482 -0.0505 0.5216 0.6523
0.500 0.3941 0.01173 0.00480 -0.0470 0.5069 0.9041
0.750 0.4328 0.01163 0.00461 -0.0489 0.4889 1.0000
1.000 0.4614 0.01179 0.00462 -0.0489 0.4723 1.0000
1.250 0.4899 0.01197 0.00465 -0.0489 0.4549 1.0000
1.500 0.5184 0.01216 0.00469 -0.0490 0.4372 1.0000
1.750 0.5469 0.01236 0.00475 -0.0490 0.4196 1.0000
2.000 0.5753 0.01259 0.00484 -0.0491 0.4015 1.0000
2.250 0.6036 0.01283 0.00494 -0.0491 0.3828 1.0000
2.500 0.6318 0.01308 0.00505 -0.0492 0.3647 1.0000
2.750 0.6600 0.01335 0.00519 -0.0492 0.3477 1.0000
3.000 0.6881 0.01363 0.00535 -0.0493 0.3314 1.0000
3.250 0.7160 0.01393 0.00553 -0.0493 0.3161 1.0000
3.500 0.7439 0.01424 0.00573 -0.0494 0.3024 1.0000
3.750 0.7716 0.01456 0.00594 -0.0494 0.2900 1.0000
4.000 0.7995 0.01486 0.00618 -0.0495 0.2785 1.0000
4.250 0.8270 0.01519 0.00642 -0.0495 0.2683 1.0000
4.500 0.8545 0.01552 0.00668 -0.0495 0.2586 1.0000
4.750 0.8819 0.01585 0.00696 -0.0495 0.2504 1.0000
5.000 0.9091 0.01619 0.00724 -0.0495 0.2421 1.0000
5.250 0.9362 0.01655 0.00755 -0.0495 0.2349 1.0000
5.500 0.9632 0.01689 0.00786 -0.0494 0.2278 1.0000
5.750 0.9896 0.01730 0.00820 -0.0493 0.2217 1.0000
6.000 1.0166 0.01762 0.00854 -0.0493 0.2155 1.0000
6.250 1.0428 0.01801 0.00890 -0.0491 0.2096 1.0000
6.500 1.0687 0.01843 0.00928 -0.0490 0.2046 1.0000
6.750 1.0951 0.01879 0.00967 -0.0488 0.1994 1.0000
7.000 1.1206 0.01921 0.01007 -0.0486 0.1944 1.0000
7.250 1.1454 0.01969 0.01051 -0.0483 0.1901 1.0000
7.500 1.1711 0.02007 0.01094 -0.0481 0.1857 1.0000
7.750 1.1960 0.02051 0.01139 -0.0478 0.1813 1.0000
8.000 1.2197 0.02102 0.01187 -0.0474 0.1774 1.0000
8.250 1.2440 0.02149 0.01238 -0.0470 0.1738 1.0000
8.500 1.2681 0.02195 0.01289 -0.0466 0.1700 1.0000
8.750 1.2913 0.02245 0.01341 -0.0461 0.1663 1.0000
9.000 1.3131 0.02305 0.01398 -0.0455 0.1630 1.0000
9.250 1.3355 0.02358 0.01458 -0.0449 0.1598 1.0000
9.500 1.3577 0.02411 0.01518 -0.0443 0.1565 1.0000
9.750 1.3787 0.02468 0.01580 -0.0435 0.1533 1.0000
10.000 1.3980 0.02533 0.01645 -0.0425 0.1503 1.0000
10.250 1.4166 0.02602 0.01716 -0.0414 0.1476 1.0000
10.500 1.4359 0.02663 0.01788 -0.0404 0.1447 1.0000
10.750 1.4536 0.02730 0.01863 -0.0393 0.1419 1.0000
11.000 1.4693 0.02804 0.01941 -0.0378 0.1393 1.0000
11.250 1.4821 0.02889 0.02028 -0.0361 0.1369 1.0000
11.500 1.4928 0.02978 0.02123 -0.0340 0.1347 1.0000
11.750 1.5048 0.03067 0.02225 -0.0322 0.1324 1.0000
12.000 1.5160 0.03167 0.02335 -0.0305 0.1300 1.0000
12.250 1.5260 0.03278 0.02454 -0.0289 0.1278 1.0000
12.500 1.5347 0.03406 0.02586 -0.0275 0.1257 1.0000
12.750 1.5422 0.03552 0.02732 -0.0261 0.1238 1.0000
13.000 1.5524 0.03686 0.02882 -0.0251 0.1218 1.0000
13.250 1.5614 0.03836 0.03044 -0.0242 0.1197 1.0000
13.500 1.5691 0.04000 0.03220 -0.0233 0.1177 1.0000
13.750 1.5754 0.04181 0.03409 -0.0226 0.1158 1.0000
14.000 1.5803 0.04380 0.03613 -0.0220 0.1141 1.0000
14.250 1.5845 0.04593 0.03829 -0.0215 0.1125 1.0000
14.500 1.5896 0.04808 0.04062 -0.0212 0.1107 1.0000
14.750 1.5932 0.05043 0.04311 -0.0210 0.1089 1.0000
15.000 1.5956 0.05296 0.04577 -0.0209 0.1072 1.0000
15.250 1.5966 0.05568 0.04859 -0.0210 0.1055 1.0000
15.500 1.5965 0.05855 0.05154 -0.0212 0.1041 1.0000
15.750 1.5958 0.06150 0.05452 -0.0214 0.1027 1.0000
16.000 1.5940 0.06470 0.05786 -0.0218 0.1014 1.0000
16.250 1.5906 0.06825 0.06158 -0.0225 0.0999 1.0000
16.500 1.5862 0.07201 0.06549 -0.0234 0.0983 1.0000
16.750 1.5811 0.07597 0.06959 -0.0245 0.0969 1.0000
17.000 1.5755 0.08007 0.07380 -0.0257 0.0955 1.0000
17.250 1.5703 0.08416 0.07797 -0.0270 0.0942 1.0000
17.500 1.5666 0.08796 0.08180 -0.0282 0.0930 1.0000
17.750 1.5578 0.09275 0.08674 -0.0299 0.0918 1.0000
18.000 1.5444 0.09850 0.09269 -0.0323 0.0905 1.0000
18.250 1.5303 0.10445 0.09882 -0.0349 0.0891 1.0000
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