FX 66-182 AIRFOIL (fx66182-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-182 AIRFOIL (fx66182-il) Reynolds number: 200,000 Max Cl/Cd: 67.91 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66182-il-200000-n5.txt Download as CSV file: xf-fx66182-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-182 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4347 0.06313 0.05844 -0.1020 0.7861 0.0141
-12.750 -0.4549 0.05734 0.05234 -0.1057 0.7674 0.0141
-12.500 -0.4692 0.05309 0.04783 -0.1078 0.7499 0.0142
-12.250 -0.4817 0.04945 0.04394 -0.1089 0.7356 0.0143
-12.000 -0.4926 0.04617 0.04040 -0.1094 0.7232 0.0143
-11.750 -0.4968 0.04376 0.03780 -0.1095 0.7118 0.0145
-11.500 -0.5010 0.04135 0.03517 -0.1093 0.7018 0.0147
-11.250 -0.5024 0.03932 0.03293 -0.1089 0.6929 0.0149
-11.000 -0.5023 0.03741 0.03082 -0.1082 0.6843 0.0152
-10.750 -0.5014 0.03576 0.02894 -0.1071 0.6771 0.0158
-10.500 -0.4999 0.03396 0.02689 -0.1056 0.6699 0.0162
-10.250 -0.4981 0.03252 0.02512 -0.1036 0.6637 0.0169
-10.000 -0.4934 0.03115 0.02340 -0.1015 0.6580 0.0175
-9.750 -0.4792 0.02966 0.02182 -0.1005 0.6525 0.0180
-9.500 -0.4641 0.02854 0.02058 -0.0996 0.6478 0.0186
-9.250 -0.4480 0.02750 0.01942 -0.0986 0.6433 0.0193
-9.000 -0.4304 0.02645 0.01823 -0.0977 0.6386 0.0200
-8.750 -0.4121 0.02545 0.01705 -0.0968 0.6344 0.0210
-8.250 -0.3756 0.02361 0.01500 -0.0949 0.6265 0.0231
-8.000 -0.3568 0.02296 0.01431 -0.0941 0.6223 0.0244
-7.750 -0.3370 0.02238 0.01362 -0.0933 0.6187 0.0261
-7.500 -0.3168 0.02179 0.01289 -0.0925 0.6157 0.0274
-7.250 -0.2986 0.02104 0.01212 -0.0916 0.6127 0.0290
-7.000 -0.2779 0.02051 0.01157 -0.0910 0.6094 0.0308
-6.750 -0.2569 0.02001 0.01099 -0.0903 0.6063 0.0326
-6.500 -0.2356 0.01951 0.01039 -0.0896 0.6034 0.0340
-6.250 -0.2161 0.01887 0.00968 -0.0887 0.6007 0.0354
-6.000 -0.1944 0.01839 0.00911 -0.0882 0.5981 0.0370
-5.750 -0.1716 0.01797 0.00863 -0.0877 0.5950 0.0393
-5.250 -0.1253 0.01714 0.00769 -0.0868 0.5894 0.0465
-5.000 -0.1014 0.01676 0.00726 -0.0864 0.5870 0.0537
-4.750 -0.0781 0.01630 0.00684 -0.0861 0.5849 0.0751
-4.500 -0.0557 0.01572 0.00644 -0.0858 0.5829 0.1243
-4.250 -0.0340 0.01504 0.00606 -0.0854 0.5805 0.1994
-4.000 -0.0137 0.01418 0.00567 -0.0850 0.5778 0.3139
-3.750 0.0065 0.01361 0.00574 -0.0841 0.5753 0.4607
-3.500 0.0330 0.01373 0.00592 -0.0838 0.5728 0.5181
-3.250 0.0605 0.01392 0.00605 -0.0836 0.5707 0.5435
-3.000 0.0884 0.01414 0.00613 -0.0836 0.5688 0.5645
-2.750 0.1158 0.01441 0.00635 -0.0833 0.5669 0.5814
-2.500 0.1429 0.01466 0.00657 -0.0831 0.5646 0.5954
-2.250 0.1700 0.01485 0.00677 -0.0828 0.5621 0.6043
-2.000 0.1978 0.01491 0.00671 -0.0829 0.5596 0.6109
-1.750 0.2257 0.01493 0.00666 -0.0830 0.5574 0.6141
-1.500 0.2538 0.01496 0.00662 -0.0832 0.5555 0.6168
-1.250 0.2820 0.01500 0.00657 -0.0834 0.5538 0.6199
-1.000 0.3105 0.01506 0.00652 -0.0837 0.5520 0.6233
-0.750 0.3380 0.01509 0.00651 -0.0839 0.5497 0.6270
-0.500 0.3654 0.01513 0.00654 -0.0840 0.5472 0.6297
-0.250 0.3929 0.01517 0.00657 -0.0841 0.5450 0.6321
0.000 0.4207 0.01523 0.00660 -0.0843 0.5430 0.6349
0.250 0.4486 0.01529 0.00661 -0.0845 0.5412 0.6378
0.500 0.4769 0.01535 0.00661 -0.0848 0.5394 0.6408
0.750 0.5054 0.01543 0.00660 -0.0852 0.5377 0.6437
1.000 0.5329 0.01550 0.00667 -0.0853 0.5359 0.6458
1.250 0.5595 0.01558 0.00680 -0.0853 0.5335 0.6481
1.500 0.5864 0.01567 0.00692 -0.0854 0.5313 0.6505
1.750 0.6137 0.01577 0.00703 -0.0855 0.5293 0.6533
2.000 0.6412 0.01588 0.00713 -0.0857 0.5274 0.6563
2.250 0.6690 0.01598 0.00721 -0.0860 0.5255 0.6591
2.500 0.6967 0.01606 0.00729 -0.0862 0.5238 0.6611
2.750 0.7247 0.01615 0.00737 -0.0864 0.5221 0.6635
3.000 0.7513 0.01628 0.00756 -0.0865 0.5202 0.6662
3.250 0.7769 0.01644 0.00780 -0.0864 0.5179 0.6692
3.500 0.8031 0.01660 0.00800 -0.0864 0.5157 0.6720
3.750 0.8296 0.01675 0.00819 -0.0865 0.5134 0.6748
4.000 0.8562 0.01686 0.00835 -0.0865 0.5113 0.6771
4.250 0.8832 0.01696 0.00850 -0.0866 0.5094 0.6798
4.500 0.9107 0.01708 0.00865 -0.0868 0.5077 0.6830
4.750 0.9388 0.01722 0.00880 -0.0871 0.5062 0.6864
5.000 0.9620 0.01746 0.00917 -0.0867 0.5035 0.6896
5.250 0.9861 0.01767 0.00951 -0.0864 0.5010 0.6924
5.500 1.0109 0.01787 0.00981 -0.0862 0.4988 0.6953
5.750 1.0363 0.01805 0.01007 -0.0861 0.4967 0.6987
6.000 1.0626 0.01820 0.01030 -0.0861 0.4947 0.7028
6.250 1.0896 0.01834 0.01049 -0.0862 0.4929 0.7068
6.500 1.1171 0.01847 0.01068 -0.0864 0.4913 0.7106
6.750 1.1378 0.01881 0.01120 -0.0856 0.4887 0.7147
7.000 1.1594 0.01914 0.01169 -0.0850 0.4860 0.7193
7.250 1.1820 0.01941 0.01210 -0.0845 0.4836 0.7237
7.500 1.2060 0.01953 0.01234 -0.0841 0.4808 0.7285
7.750 1.2328 0.01951 0.01239 -0.0841 0.4778 0.7344
8.000 1.2536 0.01968 0.01270 -0.0832 0.4740 0.7406
8.250 1.2701 0.01988 0.01309 -0.0815 0.4688 0.7480
8.500 1.2930 0.01985 0.01315 -0.0809 0.4644 0.7562
8.750 1.3135 0.01986 0.01329 -0.0798 0.4592 0.7660
9.000 1.3263 0.01995 0.01357 -0.0775 0.4515 0.7780
9.250 1.3448 0.01988 0.01361 -0.0760 0.4451 0.7946
9.500 1.3501 0.02000 0.01395 -0.0723 0.4359 0.8247
9.750 1.3575 0.01999 0.01419 -0.0692 0.4225 1.0000
10.000 1.3594 0.02041 0.01459 -0.0655 0.4054 1.0000
10.250 1.3589 0.02119 0.01534 -0.0621 0.3863 1.0000
10.500 1.3572 0.02232 0.01644 -0.0590 0.3672 1.0000
10.750 1.3521 0.02387 0.01793 -0.0560 0.3468 1.0000
11.000 1.3448 0.02585 0.01987 -0.0534 0.3265 1.0000
11.250 1.3322 0.02847 0.02241 -0.0509 0.3040 1.0000
11.500 1.3118 0.03197 0.02579 -0.0486 0.2752 1.0000
11.750 1.2914 0.03576 0.02947 -0.0466 0.2519 1.0000
12.000 1.2696 0.03987 0.03346 -0.0449 0.2285 1.0000
12.250 1.2501 0.04393 0.03742 -0.0435 0.2058 1.0000
12.500 1.2319 0.04808 0.04147 -0.0425 0.1831 1.0000
12.750 1.2170 0.05211 0.04541 -0.0418 0.1614 1.0000
13.000 1.2029 0.05620 0.04939 -0.0412 0.1387 1.0000
13.250 1.1918 0.06013 0.05322 -0.0409 0.1178 1.0000
13.500 1.1814 0.06409 0.05706 -0.0407 0.0959 1.0000
13.750 1.1731 0.06792 0.06080 -0.0407 0.0768 1.0000
14.000 1.1684 0.07144 0.06424 -0.0407 0.0620 1.0000
14.250 1.1642 0.07496 0.06770 -0.0409 0.0488 1.0000
14.500 1.1625 0.07825 0.07097 -0.0411 0.0398 1.0000
14.750 1.1616 0.08151 0.07421 -0.0414 0.0329 1.0000
15.000 1.1627 0.08458 0.07733 -0.0417 0.0282 1.0000
15.250 1.1633 0.08776 0.08054 -0.0421 0.0249 1.0000
15.500 1.1664 0.09066 0.08351 -0.0425 0.0224 1.0000
15.750 1.1678 0.09380 0.08669 -0.0430 0.0202 1.0000
16.000 1.1701 0.09686 0.08982 -0.0436 0.0189 1.0000
16.250 1.1725 0.09996 0.09301 -0.0443 0.0178 1.0000
16.500 1.1745 0.10312 0.09624 -0.0450 0.0170 1.0000
16.750 1.1748 0.10655 0.09973 -0.0458 0.0161 1.0000
17.000 1.1751 0.11000 0.10324 -0.0467 0.0153 1.0000
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