ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 13% AIRFOIL (arad13-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.44 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad13-il-1000000-n5.txt Download as CSV file: xf-arad13-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8353 0.13675 0.13441 0.0112 1.0000 0.0118
-16.250 -0.8547 0.12842 0.12601 0.0066 1.0000 0.0118
-15.750 -1.3070 0.03964 0.03604 -0.0555 1.0000 0.0111
-15.500 -1.3119 0.03650 0.03272 -0.0545 1.0000 0.0112
-15.250 -1.3067 0.03417 0.03024 -0.0535 1.0000 0.0112
-15.000 -1.2960 0.03226 0.02820 -0.0527 1.0000 0.0113
-14.750 -1.2820 0.03062 0.02644 -0.0520 1.0000 0.0114
-14.500 -1.2654 0.02919 0.02489 -0.0513 1.0000 0.0115
-14.250 -1.2470 0.02790 0.02350 -0.0508 1.0000 0.0116
-14.000 -1.2271 0.02673 0.02223 -0.0502 1.0000 0.0117
-13.750 -1.2060 0.02567 0.02108 -0.0498 1.0000 0.0117
-13.500 -1.1838 0.02470 0.02001 -0.0493 1.0000 0.0118
-13.250 -1.1608 0.02380 0.01903 -0.0490 1.0000 0.0119
-13.000 -1.1374 0.02288 0.01803 -0.0486 1.0000 0.0120
-12.750 -1.1139 0.02191 0.01697 -0.0483 1.0000 0.0122
-12.500 -1.0895 0.02105 0.01605 -0.0481 1.0000 0.0124
-12.250 -1.0642 0.02029 0.01523 -0.0478 1.0000 0.0126
-12.000 -1.0384 0.01960 0.01449 -0.0477 1.0000 0.0128
-11.750 -1.0122 0.01896 0.01380 -0.0475 1.0000 0.0130
-11.500 -0.9855 0.01837 0.01316 -0.0474 1.0000 0.0132
-11.250 -0.9585 0.01781 0.01255 -0.0473 1.0000 0.0134
-11.000 -0.9312 0.01728 0.01198 -0.0472 1.0000 0.0137
-10.750 -0.9037 0.01678 0.01143 -0.0472 1.0000 0.0139
-10.500 -0.8759 0.01631 0.01091 -0.0471 1.0000 0.0141
-10.250 -0.8479 0.01586 0.01042 -0.0471 1.0000 0.0144
-10.000 -0.8199 0.01537 0.00990 -0.0471 1.0000 0.0147
-9.750 -0.7893 0.01492 0.00942 -0.0477 0.9841 0.0151
-9.500 -0.7586 0.01455 0.00901 -0.0481 0.9602 0.0156
-9.250 -0.7320 0.01426 0.00865 -0.0476 0.9353 0.0160
-9.000 -0.7059 0.01400 0.00830 -0.0469 0.9114 0.0165
-8.750 -0.6790 0.01376 0.00796 -0.0464 0.8897 0.0170
-8.500 -0.6515 0.01347 0.00759 -0.0461 0.8696 0.0177
-8.250 -0.6235 0.01320 0.00725 -0.0459 0.8514 0.0185
-8.000 -0.5951 0.01297 0.00694 -0.0458 0.8339 0.0194
-7.750 -0.5664 0.01275 0.00664 -0.0457 0.8179 0.0202
-7.500 -0.5376 0.01250 0.00633 -0.0457 0.8022 0.0213
-7.250 -0.5086 0.01230 0.00606 -0.0457 0.7870 0.0225
-7.000 -0.4793 0.01209 0.00580 -0.0457 0.7724 0.0237
-6.750 -0.4501 0.01189 0.00555 -0.0458 0.7589 0.0252
-6.250 -0.3913 0.01153 0.00510 -0.0460 0.7311 0.0283
-6.000 -0.3617 0.01138 0.00490 -0.0461 0.7183 0.0300
-5.750 -0.3321 0.01122 0.00470 -0.0462 0.7053 0.0320
-5.500 -0.3024 0.01109 0.00453 -0.0463 0.6919 0.0341
-5.250 -0.2727 0.01094 0.00435 -0.0465 0.6791 0.0363
-5.000 -0.2430 0.01084 0.00419 -0.0466 0.6659 0.0384
-4.750 -0.2133 0.01072 0.00403 -0.0468 0.6512 0.0405
-4.500 -0.1835 0.01063 0.00389 -0.0469 0.6343 0.0428
-4.250 -0.1537 0.01054 0.00375 -0.0471 0.6166 0.0454
-4.000 -0.1238 0.01046 0.00362 -0.0473 0.6008 0.0486
-3.750 -0.0940 0.01036 0.00350 -0.0475 0.5867 0.0528
-3.500 -0.0641 0.01029 0.00339 -0.0477 0.5726 0.0566
-3.000 -0.0042 0.01016 0.00320 -0.0481 0.5441 0.0656
-2.750 0.0257 0.01010 0.00312 -0.0483 0.5303 0.0708
-2.500 0.0557 0.01007 0.00305 -0.0485 0.5158 0.0763
-2.250 0.0856 0.01004 0.00299 -0.0488 0.5002 0.0828
-2.000 0.1155 0.01002 0.00294 -0.0490 0.4839 0.0893
-1.750 0.1455 0.01001 0.00290 -0.0493 0.4687 0.0960
-1.500 0.1755 0.01000 0.00286 -0.0495 0.4551 0.1032
-1.250 0.2054 0.00999 0.00284 -0.0498 0.4416 0.1112
-1.000 0.2353 0.01002 0.00282 -0.0500 0.4256 0.1182
-0.750 0.2652 0.01004 0.00281 -0.0503 0.4093 0.1277
-0.500 0.2951 0.01008 0.00281 -0.0505 0.3942 0.1362
-0.250 0.3249 0.01012 0.00282 -0.0508 0.3781 0.1458
0.000 0.3547 0.01018 0.00284 -0.0511 0.3597 0.1583
0.250 0.3844 0.01024 0.00287 -0.0514 0.3414 0.1719
0.500 0.4142 0.01030 0.00291 -0.0517 0.3257 0.1866
0.750 0.4439 0.01036 0.00296 -0.0519 0.3105 0.2053
1.000 0.4735 0.01041 0.00301 -0.0522 0.2951 0.2294
1.250 0.5032 0.01044 0.00307 -0.0526 0.2814 0.2656
1.500 0.5328 0.01036 0.00314 -0.0530 0.2701 0.3409
2.000 0.5907 0.00953 0.00335 -0.0539 0.2495 0.7356
2.250 0.6124 0.00915 0.00347 -0.0521 0.2402 0.9164
2.500 0.6405 0.00901 0.00338 -0.0518 0.2331 0.9970
2.750 0.6702 0.00918 0.00346 -0.0521 0.2247 1.0000
3.000 0.6998 0.00933 0.00356 -0.0523 0.2174 1.0000
3.250 0.7292 0.00951 0.00368 -0.0526 0.2096 1.0000
3.500 0.7586 0.00967 0.00379 -0.0529 0.2040 1.0000
3.750 0.7880 0.00984 0.00390 -0.0531 0.1980 1.0000
4.250 0.8466 0.01019 0.00416 -0.0536 0.1867 1.0000
4.500 0.8757 0.01037 0.00430 -0.0539 0.1814 1.0000
4.750 0.9047 0.01058 0.00445 -0.0541 0.1759 1.0000
5.000 0.9338 0.01073 0.00459 -0.0543 0.1722 1.0000
5.250 0.9627 0.01092 0.00475 -0.0546 0.1679 1.0000
5.500 0.9914 0.01115 0.00492 -0.0548 0.1629 1.0000
5.750 1.0202 0.01132 0.00508 -0.0550 0.1598 1.0000
6.000 1.0490 0.01150 0.00525 -0.0552 0.1567 1.0000
6.250 1.0774 0.01171 0.00543 -0.0553 0.1531 1.0000
6.500 1.1056 0.01196 0.00564 -0.0555 0.1488 1.0000
6.750 1.1341 0.01214 0.00582 -0.0557 0.1463 1.0000
7.000 1.1624 0.01234 0.00602 -0.0558 0.1435 1.0000
7.250 1.1904 0.01257 0.00623 -0.0560 0.1403 1.0000
7.500 1.2180 0.01284 0.00647 -0.0561 0.1365 1.0000
7.750 1.2459 0.01305 0.00668 -0.0562 0.1340 1.0000
8.000 1.2736 0.01328 0.00691 -0.0563 0.1314 1.0000
8.250 1.3010 0.01353 0.00715 -0.0563 0.1285 1.0000
8.500 1.3279 0.01382 0.00742 -0.0563 0.1252 1.0000
8.750 1.3550 0.01408 0.00768 -0.0564 0.1226 1.0000
9.000 1.3820 0.01433 0.00794 -0.0564 0.1201 1.0000
9.250 1.4085 0.01462 0.00822 -0.0563 0.1175 1.0000
9.500 1.4346 0.01494 0.00853 -0.0562 0.1144 1.0000
9.750 1.4606 0.01525 0.00884 -0.0561 0.1118 1.0000
10.000 1.4866 0.01554 0.00914 -0.0560 0.1097 1.0000
10.250 1.5121 0.01586 0.00947 -0.0559 0.1072 1.0000
10.500 1.5369 0.01623 0.00983 -0.0556 0.1044 1.0000
10.750 1.5613 0.01661 0.01021 -0.0553 0.1018 1.0000
11.000 1.5860 0.01693 0.01056 -0.0550 0.1001 1.0000
11.250 1.6100 0.01729 0.01094 -0.0546 0.0980 1.0000
11.500 1.6331 0.01771 0.01136 -0.0541 0.0956 1.0000
11.750 1.6552 0.01817 0.01183 -0.0535 0.0930 1.0000
12.000 1.6778 0.01856 0.01225 -0.0529 0.0915 1.0000
12.250 1.6996 0.01898 0.01270 -0.0522 0.0898 1.0000
12.500 1.7202 0.01945 0.01319 -0.0513 0.0877 1.0000
12.750 1.7393 0.01999 0.01374 -0.0503 0.0856 1.0000
13.000 1.7571 0.02057 0.01434 -0.0491 0.0836 1.0000
13.250 1.7753 0.02107 0.01489 -0.0479 0.0824 1.0000
13.500 1.7916 0.02165 0.01551 -0.0464 0.0808 1.0000
13.750 1.8025 0.02235 0.01625 -0.0440 0.0793 1.0000
14.000 1.8112 0.02320 0.01714 -0.0415 0.0778 1.0000
14.250 1.8200 0.02419 0.01816 -0.0394 0.0762 1.0000
14.500 1.8304 0.02518 0.01921 -0.0377 0.0749 1.0000
14.750 1.8414 0.02620 0.02030 -0.0362 0.0738 1.0000
15.000 1.8514 0.02738 0.02153 -0.0349 0.0725 1.0000
15.250 1.8602 0.02874 0.02294 -0.0337 0.0712 1.0000
15.500 1.8675 0.03029 0.02454 -0.0326 0.0698 1.0000
15.750 1.8735 0.03204 0.02635 -0.0316 0.0684 1.0000
16.000 1.8805 0.03380 0.02818 -0.0309 0.0675 1.0000
16.250 1.8875 0.03561 0.03007 -0.0303 0.0665 1.0000
16.500 1.8928 0.03764 0.03217 -0.0298 0.0654 1.0000
16.750 1.8957 0.03998 0.03457 -0.0294 0.0640 1.0000
17.000 1.8957 0.04269 0.03735 -0.0292 0.0626 1.0000
17.250 1.8936 0.04572 0.04044 -0.0291 0.0612 1.0000
17.500 1.8933 0.04858 0.04340 -0.0291 0.0603 1.0000
17.750 1.8913 0.05168 0.04659 -0.0293 0.0594 1.0000
18.000 1.8870 0.05513 0.05013 -0.0296 0.0584 1.0000
18.250 1.8806 0.05893 0.05402 -0.0301 0.0575 1.0000
18.500 1.8711 0.06322 0.05840 -0.0308 0.0565 1.0000
18.750 1.8588 0.06799 0.06326 -0.0318 0.0556 1.0000
19.000 1.8445 0.07313 0.06850 -0.0331 0.0547 1.0000
19.250 1.8326 0.07801 0.07349 -0.0343 0.0540 1.0000
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