FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il) Reynolds number: 1,000,000 Max Cl/Cd: 148.74 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66s161-il-1000000.txt Download as CSV file: xf-fx66s161-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-161 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6261 0.07463 0.07267 -0.0586 1.0000 0.0075
-13.750 -0.6646 0.06352 0.06130 -0.0660 1.0000 0.0073
-13.500 -0.6928 0.05572 0.05335 -0.0712 1.0000 0.0074
-13.250 -0.6968 0.05195 0.04954 -0.0737 1.0000 0.0076
-13.000 -0.7239 0.04529 0.04266 -0.0776 1.0000 0.0075
-12.750 -0.7335 0.04133 0.03859 -0.0797 1.0000 0.0075
-12.500 -0.7352 0.03612 0.03314 -0.0853 0.9603 0.0075
-12.250 -0.6276 0.03136 0.02801 -0.1112 0.8981 0.0080
-12.000 -0.6383 0.02828 0.02434 -0.1113 0.8122 0.0079
-11.750 -0.6403 0.02677 0.02259 -0.1100 0.7755 0.0080
-11.500 -0.6372 0.02590 0.02157 -0.1085 0.7492 0.0082
-11.000 -0.6334 0.02368 0.01899 -0.1038 0.7148 0.0083
-10.750 -0.6238 0.02246 0.01759 -0.1022 0.7016 0.0084
-10.500 -0.6103 0.02144 0.01643 -0.1010 0.6900 0.0086
-10.250 -0.5948 0.02051 0.01535 -0.0999 0.6794 0.0087
-10.000 -0.5775 0.01969 0.01438 -0.0990 0.6694 0.0089
-9.750 -0.5592 0.01882 0.01338 -0.0981 0.6602 0.0091
-9.500 -0.5400 0.01802 0.01244 -0.0973 0.6519 0.0092
-9.250 -0.5194 0.01732 0.01162 -0.0966 0.6441 0.0094
-9.000 -0.4979 0.01669 0.01088 -0.0959 0.6372 0.0095
-8.750 -0.4761 0.01603 0.01012 -0.0953 0.6306 0.0098
-8.500 -0.4582 0.01492 0.00886 -0.0943 0.6243 0.0102
-8.250 -0.4344 0.01441 0.00831 -0.0940 0.6185 0.0107
-8.000 -0.4100 0.01401 0.00785 -0.0937 0.6124 0.0112
-7.750 -0.3852 0.01362 0.00739 -0.0934 0.6070 0.0117
-7.500 -0.3598 0.01324 0.00695 -0.0932 0.6014 0.0123
-7.250 -0.3346 0.01289 0.00651 -0.0929 0.5961 0.0127
-7.000 -0.3105 0.01229 0.00582 -0.0925 0.5914 0.0136
-6.750 -0.2847 0.01190 0.00539 -0.0924 0.5866 0.0147
-6.500 -0.2584 0.01165 0.00509 -0.0923 0.5820 0.0159
-6.250 -0.2313 0.01146 0.00484 -0.0922 0.5778 0.0171
-6.000 -0.2055 0.01100 0.00435 -0.0920 0.5737 0.0199
-5.750 -0.1782 0.01081 0.00412 -0.0920 0.5695 0.0219
-5.500 -0.1518 0.01053 0.00378 -0.0919 0.5654 0.0252
-5.250 -0.1241 0.01035 0.00358 -0.0920 0.5621 0.0282
-5.000 -0.0968 0.01009 0.00332 -0.0920 0.5588 0.0333
-4.750 -0.0692 0.00988 0.00309 -0.0920 0.5552 0.0403
-4.500 -0.0422 0.00963 0.00288 -0.0920 0.5515 0.0559
-4.250 -0.0153 0.00933 0.00267 -0.0921 0.5482 0.0866
-4.000 0.0114 0.00888 0.00244 -0.0922 0.5454 0.1445
-3.750 0.0373 0.00828 0.00216 -0.0923 0.5427 0.2366
-3.500 0.0637 0.00783 0.00200 -0.0924 0.5399 0.3271
-3.250 0.0912 0.00766 0.00191 -0.0924 0.5371 0.3697
-3.000 0.1191 0.00756 0.00188 -0.0925 0.5342 0.4053
-2.750 0.1478 0.00751 0.00186 -0.0927 0.5319 0.4292
-2.500 0.1766 0.00748 0.00185 -0.0929 0.5295 0.4471
-2.250 0.2053 0.00749 0.00185 -0.0931 0.5271 0.4597
-2.000 0.2340 0.00752 0.00185 -0.0932 0.5248 0.4720
-1.750 0.2626 0.00758 0.00187 -0.0934 0.5224 0.4832
-1.500 0.2910 0.00764 0.00191 -0.0935 0.5198 0.4927
-1.250 0.3200 0.00767 0.00192 -0.0937 0.5180 0.5007
-1.000 0.3487 0.00765 0.00192 -0.0939 0.5159 0.5072
-0.750 0.3775 0.00768 0.00193 -0.0941 0.5135 0.5125
-0.500 0.4062 0.00770 0.00192 -0.0943 0.5112 0.5165
-0.250 0.4346 0.00772 0.00193 -0.0945 0.5087 0.5203
0.000 0.4628 0.00780 0.00197 -0.0946 0.5060 0.5240
0.250 0.4916 0.00783 0.00199 -0.0948 0.5043 0.5276
0.500 0.5204 0.00785 0.00201 -0.0951 0.5026 0.5310
0.750 0.5490 0.00785 0.00204 -0.0953 0.5008 0.5349
1.000 0.5776 0.00787 0.00207 -0.0955 0.4987 0.5390
1.250 0.6062 0.00791 0.00210 -0.0957 0.4967 0.5430
1.500 0.6346 0.00795 0.00214 -0.0959 0.4947 0.5470
1.750 0.6627 0.00801 0.00219 -0.0960 0.4924 0.5511
2.000 0.6908 0.00811 0.00228 -0.0962 0.4900 0.5554
2.250 0.7195 0.00813 0.00233 -0.0964 0.4886 0.5596
2.500 0.7479 0.00814 0.00238 -0.0966 0.4869 0.5644
2.750 0.7763 0.00816 0.00244 -0.0968 0.4850 0.5694
3.000 0.8046 0.00820 0.00250 -0.0970 0.4831 0.5746
3.250 0.8328 0.00823 0.00257 -0.0972 0.4811 0.5805
3.500 0.8607 0.00829 0.00265 -0.0973 0.4789 0.5874
3.750 0.8884 0.00839 0.00276 -0.0974 0.4762 0.5945
4.000 0.9164 0.00842 0.00285 -0.0976 0.4741 0.6034
4.250 0.9445 0.00843 0.00293 -0.0977 0.4719 0.6130
4.500 0.9724 0.00845 0.00302 -0.0979 0.4694 0.6246
4.750 1.0002 0.00848 0.00311 -0.0980 0.4669 0.6383
5.000 1.0276 0.00853 0.00321 -0.0981 0.4645 0.6532
5.250 1.0546 0.00862 0.00335 -0.0981 0.4617 0.6707
5.500 1.0820 0.00864 0.00349 -0.0982 0.4595 0.6925
5.750 1.1093 0.00863 0.00362 -0.0982 0.4572 0.7201
6.000 1.1360 0.00861 0.00375 -0.0981 0.4544 0.7590
6.250 1.1613 0.00855 0.00389 -0.0977 0.4514 0.8174
6.500 1.1901 0.00838 0.00403 -0.0980 0.4483 1.0000
6.750 1.2171 0.00847 0.00415 -0.0980 0.4440 1.0000
7.000 1.2441 0.00851 0.00423 -0.0980 0.4376 1.0000
7.250 1.2699 0.00861 0.00433 -0.0978 0.4287 1.0000
7.500 1.2955 0.00871 0.00440 -0.0976 0.4132 1.0000
7.750 1.3196 0.00892 0.00455 -0.0972 0.3949 1.0000
8.000 1.3423 0.00923 0.00480 -0.0965 0.3774 1.0000
8.250 1.3640 0.00960 0.00510 -0.0957 0.3578 1.0000
8.500 1.3822 0.01014 0.00551 -0.0943 0.3290 1.0000
8.750 1.3985 0.01078 0.00602 -0.0926 0.3025 1.0000
9.000 1.4082 0.01172 0.00672 -0.0899 0.2585 1.0000
9.250 1.4048 0.01314 0.00780 -0.0852 0.2006 1.0000
9.500 1.3934 0.01445 0.00886 -0.0789 0.1573 1.0000
9.750 1.3811 0.01586 0.01007 -0.0729 0.1220 1.0000
10.000 1.3683 0.01747 0.01155 -0.0677 0.0916 1.0000
10.250 1.3561 0.01939 0.01335 -0.0634 0.0674 1.0000
10.500 1.3482 0.02145 0.01536 -0.0603 0.0504 1.0000
10.750 1.3408 0.02381 0.01767 -0.0579 0.0356 1.0000
11.000 1.3363 0.02622 0.02006 -0.0562 0.0259 1.0000
11.250 1.3342 0.02859 0.02243 -0.0549 0.0198 1.0000
11.500 1.3350 0.03080 0.02467 -0.0539 0.0165 1.0000
11.750 1.3344 0.03320 0.02711 -0.0529 0.0143 1.0000
12.000 1.3381 0.03525 0.02922 -0.0521 0.0131 1.0000
12.250 1.3392 0.03757 0.03158 -0.0514 0.0122 1.0000
12.500 1.3348 0.04044 0.03451 -0.0505 0.0106 1.0000
12.750 1.3379 0.04265 0.03679 -0.0500 0.0103 1.0000
13.000 1.3407 0.04494 0.03915 -0.0496 0.0095 1.0000
13.250 1.3415 0.04751 0.04176 -0.0492 0.0089 1.0000
13.500 1.3399 0.05039 0.04470 -0.0488 0.0083 1.0000
13.750 1.3378 0.05343 0.04781 -0.0486 0.0076 1.0000
14.000 1.3415 0.05588 0.05032 -0.0485 0.0070 1.0000
14.250 1.3440 0.05851 0.05301 -0.0485 0.0069 1.0000
14.500 1.3458 0.06127 0.05583 -0.0485 0.0066 1.0000
14.750 1.3469 0.06417 0.05878 -0.0486 0.0063 1.0000
15.000 1.3461 0.06735 0.06201 -0.0488 0.0059 1.0000
15.250 1.3387 0.07142 0.06617 -0.0491 0.0056 1.0000
15.500 1.3432 0.07405 0.06887 -0.0495 0.0054 1.0000
15.750 1.3439 0.07723 0.07213 -0.0499 0.0053 1.0000
16.000 1.3461 0.08024 0.07521 -0.0504 0.0051 1.0000
16.250 1.3481 0.08332 0.07835 -0.0509 0.0049 1.0000
16.500 1.3479 0.08676 0.08186 -0.0516 0.0048 1.0000
16.750 1.3493 0.09001 0.08518 -0.0523 0.0047 1.0000
17.000 1.3498 0.09345 0.08868 -0.0531 0.0045 1.0000
17.250 1.3507 0.09685 0.09214 -0.0540 0.0044 1.0000
17.500 1.3510 0.10038 0.09574 -0.0549 0.0043 1.0000
17.750 1.3493 0.10427 0.09970 -0.0560 0.0042 1.0000
18.000 1.3485 0.10806 0.10356 -0.0572 0.0042 1.0000
18.250 1.3393 0.11320 0.10879 -0.0589 0.0040 1.0000
18.500 1.3337 0.11776 0.11345 -0.0604 0.0039 1.0000
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Polar data table (+)
Polar graphs
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