FX 66-182 AIRFOIL (fx66182-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-182 AIRFOIL (fx66182-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.61 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66182-il-1000000.txt Download as CSV file: xf-fx66182-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6516 0.08967 0.08762 -0.0594 1.0000 0.0079
-15.750 -0.6946 0.07731 0.07506 -0.0667 1.0000 0.0078
-15.500 -0.7222 0.06864 0.06621 -0.0720 1.0000 0.0078
-15.250 -0.7539 0.06028 0.05763 -0.0767 1.0000 0.0077
-15.000 -0.7686 0.05511 0.05232 -0.0793 1.0000 0.0077
-14.750 -0.7748 0.05071 0.04779 -0.0822 0.9994 0.0077
-14.500 -0.7819 0.04542 0.04231 -0.0864 0.9916 0.0077
-14.250 -0.7150 0.03810 0.03453 -0.1081 0.9225 0.0079
-14.000 -0.6868 0.03570 0.03145 -0.1143 0.8000 0.0080
-13.750 -0.6878 0.03395 0.02945 -0.1134 0.7613 0.0080
-13.500 -0.6881 0.03212 0.02740 -0.1127 0.7334 0.0081
-13.250 -0.6856 0.03050 0.02560 -0.1119 0.7123 0.0081
-13.000 -0.6949 0.02791 0.02279 -0.1106 0.6970 0.0083
-12.750 -0.6933 0.02624 0.02098 -0.1096 0.6832 0.0085
-12.500 -0.6843 0.02515 0.01980 -0.1089 0.6708 0.0087
-12.250 -0.6745 0.02412 0.01868 -0.1081 0.6600 0.0089
-12.000 -0.6624 0.02327 0.01775 -0.1075 0.6503 0.0090
-11.750 -0.6520 0.02230 0.01669 -0.1066 0.6423 0.0092
-11.500 -0.6377 0.02165 0.01598 -0.1059 0.6345 0.0095
-11.250 -0.6280 0.02072 0.01495 -0.1047 0.6281 0.0097
-11.000 -0.6170 0.01997 0.01412 -0.1034 0.6220 0.0099
-10.750 -0.6073 0.01932 0.01337 -0.1015 0.6165 0.0102
-10.500 -0.5987 0.01872 0.01269 -0.0992 0.6121 0.0104
-10.250 -0.5823 0.01826 0.01216 -0.0979 0.6078 0.0106
-10.000 -0.5707 0.01740 0.01121 -0.0961 0.6037 0.0110
-9.750 -0.5532 0.01690 0.01066 -0.0950 0.5995 0.0113
-9.500 -0.5314 0.01658 0.01031 -0.0944 0.5964 0.0117
-9.250 -0.5088 0.01630 0.01001 -0.0939 0.5930 0.0123
-9.000 -0.4874 0.01592 0.00957 -0.0932 0.5897 0.0127
-8.750 -0.4645 0.01565 0.00922 -0.0927 0.5863 0.0134
-8.500 -0.4445 0.01514 0.00863 -0.0918 0.5829 0.0142
-8.250 -0.4219 0.01474 0.00824 -0.0913 0.5804 0.0151
-8.000 -0.3976 0.01446 0.00794 -0.0910 0.5777 0.0162
-7.750 -0.3712 0.01436 0.00780 -0.0909 0.5750 0.0173
-7.500 -0.3513 0.01372 0.00708 -0.0901 0.5724 0.0184
-7.250 -0.3285 0.01334 0.00667 -0.0896 0.5697 0.0195
-7.000 -0.3037 0.01309 0.00638 -0.0893 0.5672 0.0205
-6.750 -0.2780 0.01285 0.00611 -0.0892 0.5654 0.0215
-6.500 -0.2518 0.01266 0.00590 -0.0891 0.5633 0.0220
-6.250 -0.2293 0.01208 0.00526 -0.0885 0.5612 0.0233
-6.000 -0.2042 0.01177 0.00491 -0.0882 0.5589 0.0242
-5.750 -0.1784 0.01154 0.00464 -0.0881 0.5566 0.0251
-5.500 -0.1523 0.01136 0.00440 -0.0880 0.5540 0.0260
-5.250 -0.1258 0.01119 0.00420 -0.0879 0.5517 0.0269
-5.000 -0.0988 0.01100 0.00398 -0.0879 0.5503 0.0275
-4.750 -0.0721 0.01075 0.00371 -0.0878 0.5486 0.0296
-4.500 -0.0450 0.01057 0.00352 -0.0879 0.5467 0.0310
-4.250 -0.0176 0.01040 0.00334 -0.0879 0.5446 0.0331
-4.000 0.0094 0.01022 0.00316 -0.0879 0.5426 0.0405
-3.750 0.0340 0.00973 0.00290 -0.0877 0.5406 0.0992
-3.500 0.0581 0.00918 0.00265 -0.0876 0.5385 0.1897
-3.250 0.0822 0.00858 0.00241 -0.0875 0.5364 0.2964
-3.000 0.1059 0.00782 0.00216 -0.0873 0.5350 0.4392
-2.750 0.1335 0.00765 0.00213 -0.0875 0.5334 0.4917
-2.500 0.1622 0.00762 0.00213 -0.0877 0.5316 0.5170
-2.250 0.1911 0.00763 0.00214 -0.0880 0.5299 0.5326
-2.000 0.2200 0.00768 0.00217 -0.0882 0.5282 0.5480
-1.750 0.2487 0.00774 0.00223 -0.0884 0.5265 0.5599
-1.500 0.2774 0.00781 0.00227 -0.0887 0.5245 0.5682
-1.250 0.3061 0.00794 0.00236 -0.0889 0.5222 0.5761
-1.000 0.3350 0.00801 0.00240 -0.0892 0.5206 0.5823
-0.750 0.3639 0.00803 0.00244 -0.0894 0.5192 0.5871
-0.500 0.3928 0.00806 0.00247 -0.0897 0.5177 0.5905
-0.250 0.4218 0.00812 0.00250 -0.0900 0.5161 0.5945
0.000 0.4506 0.00815 0.00251 -0.0903 0.5145 0.5980
0.250 0.4794 0.00816 0.00252 -0.0906 0.5129 0.6002
0.500 0.5081 0.00819 0.00255 -0.0909 0.5113 0.6024
0.750 0.5366 0.00825 0.00258 -0.0912 0.5094 0.6048
1.000 0.5652 0.00835 0.00265 -0.0915 0.5072 0.6072
1.250 0.5939 0.00841 0.00270 -0.0918 0.5055 0.6093
1.500 0.6227 0.00844 0.00273 -0.0921 0.5042 0.6111
1.750 0.6514 0.00846 0.00276 -0.0925 0.5027 0.6128
2.000 0.6798 0.00845 0.00278 -0.0927 0.5010 0.6151
2.250 0.7082 0.00847 0.00282 -0.0930 0.4991 0.6171
2.500 0.7366 0.00850 0.00285 -0.0933 0.4971 0.6191
2.750 0.7649 0.00855 0.00291 -0.0935 0.4953 0.6210
3.000 0.7931 0.00864 0.00298 -0.0938 0.4935 0.6231
3.250 0.8213 0.00878 0.00310 -0.0941 0.4912 0.6251
3.500 0.8497 0.00881 0.00316 -0.0944 0.4900 0.6270
3.750 0.8778 0.00884 0.00322 -0.0946 0.4884 0.6288
4.000 0.9058 0.00885 0.00328 -0.0949 0.4866 0.6311
4.250 0.9338 0.00888 0.00336 -0.0951 0.4848 0.6333
4.500 0.9618 0.00894 0.00344 -0.0953 0.4830 0.6355
4.750 0.9895 0.00899 0.00352 -0.0955 0.4812 0.6377
5.000 1.0167 0.00908 0.00360 -0.0956 0.4780 0.6398
5.250 1.0440 0.00913 0.00367 -0.0957 0.4744 0.6419
5.500 1.0714 0.00914 0.00372 -0.0958 0.4710 0.6437
5.750 1.0985 0.00914 0.00379 -0.0959 0.4679 0.6465
6.000 1.1250 0.00920 0.00386 -0.0959 0.4643 0.6491
6.250 1.1515 0.00931 0.00399 -0.0959 0.4610 0.6517
6.500 1.1787 0.00934 0.00410 -0.0960 0.4581 0.6543
6.750 1.2056 0.00939 0.00419 -0.0961 0.4544 0.6569
7.000 1.2314 0.00948 0.00429 -0.0960 0.4498 0.6592
7.250 1.2570 0.00956 0.00442 -0.0958 0.4452 0.6623
7.500 1.2831 0.00960 0.00452 -0.0957 0.4385 0.6654
7.750 1.3071 0.00971 0.00464 -0.0953 0.4279 0.6685
8.000 1.3291 0.00991 0.00480 -0.0945 0.4094 0.6719
8.250 1.3475 0.01028 0.00507 -0.0931 0.3867 0.6752
8.500 1.3637 0.01071 0.00544 -0.0914 0.3618 0.6792
8.750 1.3736 0.01138 0.00596 -0.0886 0.3296 0.6832
9.000 1.3676 0.01238 0.00674 -0.0829 0.2848 0.6873
9.250 1.3564 0.01362 0.00776 -0.0766 0.2437 0.6915
9.500 1.3397 0.01510 0.00906 -0.0700 0.2036 0.6965
9.750 1.3254 0.01668 0.01052 -0.0645 0.1739 0.7022
10.000 1.3104 0.01862 0.01237 -0.0598 0.1477 0.7084
10.250 1.2915 0.02121 0.01489 -0.0556 0.1208 0.7162
10.500 1.2832 0.02353 0.01720 -0.0531 0.1046 0.7252
10.750 1.2657 0.02674 0.02038 -0.0504 0.0820 0.7373
11.000 1.2540 0.02967 0.02332 -0.0483 0.0652 0.7560
11.250 1.2440 0.03240 0.02617 -0.0463 0.0520 0.8004
11.500 1.2398 0.03558 0.02966 -0.0467 0.0358 1.0000
11.750 1.2379 0.03807 0.03216 -0.0457 0.0295 1.0000
12.000 1.2357 0.04064 0.03473 -0.0448 0.0230 1.0000
12.250 1.2338 0.04326 0.03733 -0.0441 0.0177 1.0000
12.500 1.2359 0.04558 0.03967 -0.0435 0.0156 1.0000
12.750 1.2391 0.04785 0.04198 -0.0431 0.0149 1.0000
13.000 1.2415 0.05022 0.04440 -0.0427 0.0140 1.0000
13.250 1.2438 0.05269 0.04690 -0.0423 0.0132 1.0000
13.500 1.2462 0.05517 0.04943 -0.0421 0.0125 1.0000
13.750 1.2495 0.05760 0.05192 -0.0419 0.0122 1.0000
14.000 1.2552 0.05979 0.05416 -0.0418 0.0119 1.0000
14.250 1.2583 0.06234 0.05677 -0.0417 0.0114 1.0000
14.500 1.2626 0.06475 0.05924 -0.0417 0.0110 1.0000
14.750 1.2643 0.06752 0.06205 -0.0417 0.0106 1.0000
15.000 1.2649 0.07043 0.06503 -0.0418 0.0102 1.0000
15.250 1.2611 0.07398 0.06865 -0.0420 0.0097 1.0000
15.500 1.2609 0.07712 0.07186 -0.0422 0.0095 1.0000
15.750 1.2682 0.07938 0.07417 -0.0425 0.0092 1.0000
16.000 1.2721 0.08208 0.07693 -0.0428 0.0090 1.0000
16.250 1.2778 0.08457 0.07947 -0.0432 0.0086 1.0000
16.500 1.2808 0.08746 0.08241 -0.0437 0.0083 1.0000
16.750 1.2843 0.09031 0.08531 -0.0442 0.0080 1.0000
17.000 1.2839 0.09370 0.08875 -0.0449 0.0076 1.0000
17.250 1.2785 0.09782 0.09294 -0.0457 0.0073 1.0000
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