WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Reynolds number: 500,000 Max Cl/Cd: 109.22 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx6617ai-il-500000.txt Download as CSV file: xf-fx6617ai-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT N
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 -0.5321 0.07361 0.06990 -0.0704 0.6656 0.0225
-12.500 -0.5344 0.06997 0.06621 -0.0723 0.6587 0.0228
-12.250 -0.5390 0.06622 0.06238 -0.0747 0.6529 0.0230
-12.000 -0.5444 0.06258 0.05867 -0.0771 0.6473 0.0232
-11.750 -0.5487 0.05934 0.05534 -0.0792 0.6422 0.0235
-11.500 -0.5523 0.05645 0.05236 -0.0811 0.6376 0.0240
-11.250 -0.6863 0.03621 0.03066 -0.0845 0.6409 0.0179
-11.000 -0.6771 0.03460 0.02894 -0.0841 0.6356 0.0182
-10.750 -0.6619 0.03356 0.02781 -0.0840 0.6304 0.0186
-10.500 -0.6463 0.03246 0.02659 -0.0838 0.6259 0.0191
-10.250 -0.6308 0.03107 0.02504 -0.0836 0.6218 0.0196
-10.000 -0.6142 0.02952 0.02330 -0.0833 0.6178 0.0202
-9.750 -0.5963 0.02796 0.02151 -0.0829 0.6140 0.0206
-9.500 -0.5766 0.02660 0.01993 -0.0826 0.6104 0.0210
-9.250 -0.5552 0.02549 0.01863 -0.0824 0.6071 0.0214
-9.000 -0.5325 0.02463 0.01761 -0.0822 0.6036 0.0218
-8.750 -0.5101 0.02335 0.01618 -0.0819 0.6001 0.0221
-8.500 -0.4884 0.02164 0.01439 -0.0815 0.5969 0.0226
-8.250 -0.4655 0.02077 0.01345 -0.0813 0.5938 0.0233
-8.000 -0.4415 0.02013 0.01279 -0.0813 0.5911 0.0240
-7.750 -0.4172 0.01948 0.01210 -0.0812 0.5883 0.0246
-7.500 -0.3929 0.01882 0.01138 -0.0810 0.5855 0.0252
-7.250 -0.3684 0.01823 0.01073 -0.0809 0.5828 0.0260
-7.000 -0.3438 0.01766 0.01009 -0.0808 0.5803 0.0266
-6.750 -0.3192 0.01714 0.00945 -0.0806 0.5776 0.0271
-6.500 -0.2938 0.01665 0.00892 -0.0806 0.5753 0.0276
-6.250 -0.2715 0.01568 0.00791 -0.0804 0.5729 0.0288
-6.000 -0.2464 0.01511 0.00732 -0.0804 0.5703 0.0302
-5.750 -0.2201 0.01469 0.00686 -0.0806 0.5679 0.0319
-5.500 -0.1934 0.01435 0.00645 -0.0807 0.5657 0.0339
-5.250 -0.1673 0.01388 0.00590 -0.0808 0.5636 0.0374
-5.000 -0.1403 0.01361 0.00556 -0.0810 0.5612 0.0425
-4.750 -0.1142 0.01302 0.00509 -0.0811 0.5595 0.0633
-4.500 -0.0915 0.01188 0.00453 -0.0813 0.5576 0.1863
-4.250 -0.0685 0.01080 0.00405 -0.0815 0.5554 0.3335
-4.000 -0.0427 0.01031 0.00389 -0.0816 0.5532 0.4344
-3.750 -0.0147 0.01018 0.00384 -0.0818 0.5511 0.4752
-3.500 0.0138 0.01017 0.00383 -0.0821 0.5491 0.5031
-3.250 0.0425 0.01024 0.00388 -0.0823 0.5472 0.5242
-3.000 0.0714 0.01038 0.00399 -0.0826 0.5452 0.5420
-2.750 0.1004 0.01044 0.00406 -0.0828 0.5436 0.5559
-2.500 0.1295 0.01055 0.00413 -0.0831 0.5418 0.5686
-2.250 0.1586 0.01071 0.00425 -0.0833 0.5399 0.5815
-2.000 0.1875 0.01076 0.00431 -0.0836 0.5380 0.5879
-1.750 0.2168 0.01081 0.00430 -0.0840 0.5361 0.5933
-1.500 0.2460 0.01086 0.00429 -0.0843 0.5342 0.5990
-1.250 0.2751 0.01095 0.00435 -0.0846 0.5325 0.6046
-1.000 0.3044 0.01111 0.00444 -0.0850 0.5307 0.6107
-0.750 0.3334 0.01118 0.00450 -0.0854 0.5292 0.6155
-0.500 0.3624 0.01120 0.00454 -0.0858 0.5277 0.6194
-0.250 0.3915 0.01124 0.00458 -0.0861 0.5260 0.6235
0.000 0.4207 0.01131 0.00461 -0.0866 0.5243 0.6279
0.250 0.4497 0.01132 0.00462 -0.0870 0.5225 0.6316
0.500 0.4787 0.01136 0.00466 -0.0873 0.5207 0.6352
0.750 0.5079 0.01141 0.00469 -0.0878 0.5191 0.6391
1.000 0.5372 0.01150 0.00473 -0.0882 0.5176 0.6431
1.250 0.5663 0.01161 0.00480 -0.0887 0.5160 0.6468
1.500 0.5952 0.01177 0.00497 -0.0891 0.5144 0.6503
1.750 0.6239 0.01181 0.00506 -0.0894 0.5131 0.6542
2.000 0.6527 0.01188 0.00515 -0.0898 0.5116 0.6580
2.250 0.6815 0.01195 0.00522 -0.0902 0.5098 0.6616
2.500 0.7101 0.01198 0.00530 -0.0906 0.5080 0.6650
2.750 0.7388 0.01205 0.00540 -0.0910 0.5064 0.6686
3.000 0.7677 0.01214 0.00549 -0.0914 0.5049 0.6726
3.250 0.7968 0.01224 0.00558 -0.0918 0.5035 0.6763
3.500 0.8256 0.01232 0.00568 -0.0923 0.5021 0.6796
3.750 0.8545 0.01248 0.00585 -0.0927 0.5005 0.6830
4.000 0.8828 0.01266 0.00606 -0.0931 0.4989 0.6870
4.250 0.9109 0.01274 0.00621 -0.0934 0.4973 0.6910
4.500 0.9390 0.01284 0.00637 -0.0937 0.4957 0.6945
4.750 0.9670 0.01294 0.00654 -0.0940 0.4941 0.6979
5.000 0.9951 0.01304 0.00670 -0.0944 0.4924 0.7019
5.250 1.0235 0.01314 0.00684 -0.0947 0.4907 0.7061
5.500 1.0520 0.01323 0.00696 -0.0951 0.4891 0.7100
5.750 1.0804 0.01334 0.00711 -0.0955 0.4877 0.7137
6.000 1.1091 0.01350 0.00730 -0.0960 0.4862 0.7181
6.250 1.1375 0.01378 0.00760 -0.0964 0.4844 0.7227
6.500 1.1641 0.01386 0.00781 -0.0965 0.4828 0.7270
6.750 1.1906 0.01392 0.00799 -0.0966 0.4803 0.7315
7.000 1.2178 0.01391 0.00805 -0.0967 0.4771 0.7367
7.250 1.2457 0.01384 0.00800 -0.0969 0.4739 0.7418
7.500 1.2739 0.01383 0.00801 -0.0972 0.4704 0.7469
7.750 1.2982 0.01372 0.00803 -0.0968 0.4650 0.7530
8.000 1.3243 0.01358 0.00797 -0.0967 0.4599 0.7588
8.250 1.3511 0.01357 0.00798 -0.0968 0.4558 0.7652
8.500 1.3758 0.01360 0.00815 -0.0965 0.4512 0.7722
8.750 1.4006 0.01355 0.00822 -0.0962 0.4456 0.7800
9.000 1.4259 0.01358 0.00827 -0.0960 0.4404 0.7888
9.250 1.4490 0.01357 0.00846 -0.0955 0.4325 0.7992
9.500 1.4714 0.01358 0.00857 -0.0948 0.4229 0.8118
9.750 1.4920 0.01366 0.00875 -0.0939 0.4092 0.8302
10.000 1.5066 0.01384 0.00905 -0.0919 0.3848 0.8723
10.250 1.5114 0.01472 0.00982 -0.0888 0.3397 1.0002
10.500 1.4941 0.01672 0.01152 -0.0829 0.2877 1.0002
10.750 1.4702 0.01965 0.01422 -0.0779 0.2439 1.0002
11.000 1.4409 0.02401 0.01840 -0.0746 0.2024 1.0002
11.250 1.4105 0.02943 0.02369 -0.0728 0.1689 1.0002
11.500 1.3839 0.03471 0.02889 -0.0715 0.1432 1.0002
11.750 1.3581 0.03984 0.03395 -0.0701 0.1189 1.0002
12.000 1.3331 0.04483 0.03885 -0.0687 0.0960 1.0002
12.250 1.3108 0.04957 0.04351 -0.0674 0.0759 1.0002
12.500 1.2945 0.05393 0.04780 -0.0665 0.0596 1.0002
12.750 1.2850 0.05771 0.05156 -0.0659 0.0499 1.0002
13.000 1.2795 0.06115 0.05501 -0.0654 0.0434 1.0002
13.250 1.2756 0.06446 0.05832 -0.0650 0.0387 1.0002
13.500 1.2747 0.06749 0.06140 -0.0647 0.0353 1.0002
13.750 1.2753 0.07035 0.06428 -0.0645 0.0323 1.0002
14.000 1.2715 0.07377 0.06772 -0.0643 0.0297 1.0002
14.250 1.2754 0.07632 0.07033 -0.0641 0.0278 1.0002
14.500 1.2771 0.07916 0.07321 -0.0641 0.0260 1.0002
14.750 1.2762 0.08230 0.07636 -0.0640 0.0242 1.0002
15.000 1.2757 0.08544 0.07955 -0.0640 0.0227 1.0002
15.250 1.2789 0.08814 0.08232 -0.0640 0.0214 1.0002
15.500 1.2811 0.09097 0.08519 -0.0641 0.0201 1.0002
15.750 1.2779 0.09453 0.08878 -0.0642 0.0189 1.0002
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