ARA-D 20% AIRFOIL (arad20-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 20% AIRFOIL (arad20-il) Reynolds number: 200,000 Max Cl/Cd: 56.67 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad20-il-200000-n5.txt Download as CSV file: xf-arad20-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 20% 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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.8718 0.11443 0.10942 -0.0062 1.0000 0.0271
-16.750 -0.9123 0.10217 0.09687 -0.0139 1.0000 0.0272
-16.500 -0.9390 0.09309 0.08754 -0.0195 1.0000 0.0273
-16.250 -0.9599 0.08544 0.07968 -0.0241 1.0000 0.0275
-16.000 -0.9750 0.07912 0.07319 -0.0276 1.0000 0.0277
-15.750 -0.9831 0.07419 0.06817 -0.0302 1.0000 0.0278
-15.500 -0.9904 0.06947 0.06335 -0.0327 1.0000 0.0280
-15.250 -0.9964 0.06498 0.05877 -0.0349 1.0000 0.0282
-15.000 -1.0013 0.06080 0.05449 -0.0369 1.0000 0.0285
-14.750 -1.0048 0.05692 0.05050 -0.0386 1.0000 0.0287
-14.500 -1.0069 0.05334 0.04682 -0.0400 1.0000 0.0291
-14.250 -1.0077 0.05008 0.04344 -0.0411 1.0000 0.0294
-14.000 -1.0073 0.04709 0.04033 -0.0418 1.0000 0.0298
-13.750 -1.0059 0.04435 0.03747 -0.0421 1.0000 0.0303
-13.500 -1.0033 0.04188 0.03486 -0.0420 1.0000 0.0308
-13.250 -0.9998 0.03965 0.03250 -0.0416 1.0000 0.0313
-13.000 -0.9955 0.03773 0.03054 -0.0408 1.0000 0.0317
-12.750 -0.9906 0.03605 0.02881 -0.0396 1.0000 0.0321
-12.500 -0.9862 0.03457 0.02728 -0.0378 1.0000 0.0327
-12.250 -0.9797 0.03330 0.02594 -0.0358 1.0000 0.0334
-12.000 -0.9677 0.03213 0.02467 -0.0344 1.0000 0.0343
-11.750 -0.9534 0.03102 0.02347 -0.0331 1.0000 0.0353
-11.500 -0.9374 0.03003 0.02249 -0.0320 1.0000 0.0361
-11.250 -0.9193 0.02911 0.02154 -0.0311 1.0000 0.0371
-11.000 -0.8997 0.02821 0.02058 -0.0302 1.0000 0.0384
-10.750 -0.8793 0.02732 0.01965 -0.0295 1.0000 0.0396
-10.500 -0.8520 0.02654 0.01884 -0.0301 0.9299 0.0409
-10.250 -0.8297 0.02601 0.01805 -0.0290 0.8251 0.0423
-10.000 -0.8110 0.02558 0.01727 -0.0271 0.7456 0.0439
-9.750 -0.7898 0.02512 0.01659 -0.0260 0.6911 0.0453
-9.250 -0.7418 0.02416 0.01524 -0.0249 0.6299 0.0493
-9.000 -0.7165 0.02369 0.01465 -0.0246 0.6098 0.0514
-8.750 -0.6905 0.02322 0.01406 -0.0243 0.5939 0.0539
-8.500 -0.6643 0.02278 0.01352 -0.0242 0.5809 0.0565
-8.250 -0.6373 0.02233 0.01299 -0.0241 0.5698 0.0594
-8.000 -0.6103 0.02193 0.01250 -0.0240 0.5604 0.0625
-7.750 -0.5826 0.02150 0.01203 -0.0240 0.5516 0.0660
-7.500 -0.5547 0.02113 0.01158 -0.0240 0.5432 0.0699
-7.250 -0.5268 0.02076 0.01116 -0.0241 0.5363 0.0741
-7.000 -0.4982 0.02039 0.01076 -0.0242 0.5296 0.0789
-6.750 -0.4695 0.02006 0.01038 -0.0243 0.5228 0.0845
-6.500 -0.4409 0.01973 0.01002 -0.0245 0.5167 0.0907
-6.250 -0.4118 0.01941 0.00969 -0.0247 0.5112 0.0980
-6.000 -0.3825 0.01908 0.00938 -0.0249 0.5055 0.1065
-5.750 -0.3531 0.01879 0.00908 -0.0252 0.4998 0.1163
-5.500 -0.3238 0.01853 0.00880 -0.0254 0.4945 0.1278
-5.250 -0.2941 0.01827 0.00855 -0.0257 0.4897 0.1411
-5.000 -0.2642 0.01799 0.00833 -0.0261 0.4847 0.1567
-4.750 -0.2343 0.01772 0.00811 -0.0264 0.4794 0.1743
-4.500 -0.2044 0.01747 0.00790 -0.0268 0.4745 0.1951
-4.250 -0.1746 0.01728 0.00772 -0.0272 0.4701 0.2187
-4.000 -0.1443 0.01700 0.00757 -0.0276 0.4655 0.2453
-3.750 -0.1140 0.01677 0.00744 -0.0281 0.4604 0.2758
-3.500 -0.0838 0.01653 0.00732 -0.0285 0.4556 0.3096
-3.250 -0.0537 0.01634 0.00721 -0.0290 0.4512 0.3451
-3.000 -0.0234 0.01619 0.00714 -0.0294 0.4470 0.3806
-2.750 0.0071 0.01601 0.00710 -0.0298 0.4422 0.4156
-2.500 0.0376 0.01587 0.00707 -0.0302 0.4374 0.4491
-2.250 0.0679 0.01577 0.00704 -0.0305 0.4329 0.4822
-2.000 0.0981 0.01572 0.00702 -0.0308 0.4287 0.5132
-1.750 0.1285 0.01565 0.00705 -0.0311 0.4242 0.5438
-1.500 0.1589 0.01560 0.00708 -0.0314 0.4194 0.5738
-1.250 0.1891 0.01556 0.00711 -0.0316 0.4146 0.6014
-1.000 0.2191 0.01556 0.00712 -0.0318 0.4103 0.6268
-0.750 0.2490 0.01558 0.00717 -0.0319 0.4061 0.6511
-0.500 0.2790 0.01559 0.00725 -0.0321 0.4013 0.6741
-0.250 0.3089 0.01561 0.00731 -0.0322 0.3964 0.6957
0.000 0.3386 0.01565 0.00735 -0.0323 0.3918 0.7165
0.250 0.3679 0.01572 0.00739 -0.0324 0.3878 0.7362
0.500 0.3972 0.01576 0.00751 -0.0324 0.3830 0.7546
0.750 0.4263 0.01581 0.00759 -0.0323 0.3781 0.7723
1.000 0.4553 0.01588 0.00764 -0.0323 0.3735 0.7894
1.250 0.4840 0.01598 0.00769 -0.0323 0.3694 0.8066
1.500 0.5121 0.01604 0.00782 -0.0320 0.3647 0.8225
1.750 0.5402 0.01611 0.00792 -0.0318 0.3598 0.8383
2.000 0.5680 0.01619 0.00797 -0.0315 0.3552 0.8543
2.250 0.5950 0.01630 0.00802 -0.0311 0.3511 0.8704
2.500 0.6217 0.01636 0.00814 -0.0306 0.3464 0.8862
2.750 0.6484 0.01643 0.00822 -0.0301 0.3417 0.9026
3.000 0.6753 0.01651 0.00826 -0.0297 0.3373 0.9198
3.250 0.7029 0.01660 0.00829 -0.0295 0.3332 0.9382
3.500 0.7332 0.01667 0.00841 -0.0299 0.3283 0.9579
4.000 0.7994 0.01687 0.00852 -0.0323 0.3190 1.0000
4.250 0.8296 0.01712 0.00871 -0.0331 0.3148 1.0000
4.500 0.8598 0.01736 0.00895 -0.0338 0.3100 1.0000
4.750 0.8896 0.01761 0.00916 -0.0344 0.3056 1.0000
5.000 0.9190 0.01790 0.00937 -0.0350 0.3016 1.0000
5.250 0.9483 0.01819 0.00964 -0.0355 0.2976 1.0000
5.500 0.9777 0.01846 0.00993 -0.0361 0.2931 1.0000
5.750 1.0065 0.01876 0.01020 -0.0366 0.2889 1.0000
6.000 1.0348 0.01909 0.01046 -0.0370 0.2853 1.0000
6.250 1.0631 0.01943 0.01079 -0.0374 0.2816 1.0000
6.500 1.0914 0.01976 0.01115 -0.0378 0.2774 1.0000
6.750 1.1190 0.02010 0.01148 -0.0381 0.2734 1.0000
7.000 1.1461 0.02048 0.01181 -0.0383 0.2699 1.0000
7.250 1.1730 0.02088 0.01220 -0.0385 0.2667 1.0000
7.500 1.2000 0.02126 0.01263 -0.0388 0.2629 1.0000
7.750 1.2263 0.02166 0.01305 -0.0389 0.2591 1.0000
8.000 1.2519 0.02209 0.01346 -0.0389 0.2557 1.0000
8.250 1.2767 0.02258 0.01389 -0.0389 0.2528 1.0000
8.500 1.3019 0.02302 0.01441 -0.0389 0.2495 1.0000
8.750 1.3264 0.02349 0.01494 -0.0388 0.2460 1.0000
9.000 1.3498 0.02399 0.01545 -0.0386 0.2427 1.0000
9.250 1.3721 0.02453 0.01598 -0.0382 0.2398 1.0000
9.500 1.3937 0.02512 0.01655 -0.0378 0.2372 1.0000
9.750 1.4151 0.02569 0.01722 -0.0373 0.2341 1.0000
10.000 1.4351 0.02631 0.01790 -0.0367 0.2310 1.0000
10.250 1.4534 0.02696 0.01859 -0.0358 0.2281 1.0000
10.500 1.4698 0.02769 0.01931 -0.0347 0.2256 1.0000
10.750 1.4846 0.02849 0.02009 -0.0335 0.2232 1.0000
11.000 1.4962 0.02935 0.02108 -0.0318 0.2206 1.0000
11.250 1.5042 0.03038 0.02221 -0.0298 0.2180 1.0000
11.500 1.5120 0.03157 0.02347 -0.0281 0.2155 1.0000
11.750 1.5194 0.03290 0.02485 -0.0267 0.2131 1.0000
12.000 1.5267 0.03437 0.02633 -0.0257 0.2110 1.0000
12.250 1.5336 0.03602 0.02803 -0.0249 0.2088 1.0000
12.500 1.5383 0.03801 0.03016 -0.0244 0.2063 1.0000
12.750 1.5421 0.04021 0.03249 -0.0243 0.2038 1.0000
13.000 1.5454 0.04257 0.03493 -0.0243 0.2013 1.0000
13.250 1.5486 0.04501 0.03741 -0.0245 0.1991 1.0000
13.500 1.5528 0.04733 0.03973 -0.0246 0.1970 1.0000
13.750 1.5518 0.05040 0.04294 -0.0251 0.1947 1.0000
14.000 1.5477 0.05393 0.04662 -0.0259 0.1922 1.0000
14.250 1.5432 0.05748 0.05028 -0.0266 0.1897 1.0000
14.500 1.5405 0.06079 0.05366 -0.0273 0.1874 1.0000
14.750 1.5407 0.06367 0.05655 -0.0278 0.1853 1.0000
15.000 1.5405 0.06659 0.05950 -0.0282 0.1833 1.0000
15.250 1.5251 0.07169 0.06480 -0.0296 0.1807 1.0000
15.500 1.5126 0.07651 0.06976 -0.0309 0.1780 1.0000
15.750 1.5047 0.08076 0.07409 -0.0321 0.1756 1.0000
16.000 1.5056 0.08378 0.07713 -0.0329 0.1736 1.0000
16.250 1.5156 0.08546 0.07877 -0.0332 0.1717 1.0000
16.500 1.4837 0.09347 0.08704 -0.0360 0.1687 1.0000
16.750 1.4622 0.10002 0.09375 -0.0383 0.1657 1.0000
17.000 1.4546 0.10456 0.09836 -0.0399 0.1633 1.0000
17.250 1.4624 0.10671 0.10050 -0.0406 0.1615 1.0000
17.500 1.4656 0.10956 0.10336 -0.0416 0.1596 1.0000
17.750 1.3928 0.12477 0.11893 -0.0480 0.1544 1.0000
18.000 1.3880 0.12913 0.12335 -0.0500 0.1519 1.0000
18.250 1.4038 0.13004 0.12423 -0.0505 0.1504 1.0000
18.500 1.4268 0.12969 0.12383 -0.0503 0.1494 1.0000
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