FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il) Reynolds number: 500,000 Max Cl/Cd: 116.01 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66s161-il-500000.txt Download as CSV file: xf-fx66s161-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3764 0.06081 0.05841 -0.0908 0.9105 0.0157
-11.000 -0.3965 0.04925 0.04620 -0.1068 0.8359 0.0155
-10.750 -0.4353 0.04294 0.03945 -0.1093 0.7925 0.0147
-10.500 -0.5235 0.03369 0.02928 -0.1067 0.7656 0.0134
-10.250 -0.5258 0.03158 0.02686 -0.1048 0.7469 0.0134
-10.000 -0.5210 0.02975 0.02478 -0.1033 0.7317 0.0136
-9.750 -0.5126 0.02791 0.02269 -0.1020 0.7188 0.0138
-9.500 -0.5005 0.02623 0.02077 -0.1009 0.7075 0.0139
-9.250 -0.4855 0.02481 0.01913 -0.0999 0.6976 0.0142
-9.000 -0.4674 0.02376 0.01792 -0.0991 0.6878 0.0145
-8.750 -0.4471 0.02306 0.01709 -0.0985 0.6789 0.0153
-8.500 -0.4276 0.02188 0.01570 -0.0977 0.6708 0.0157
-8.250 -0.4070 0.02069 0.01431 -0.0970 0.6630 0.0161
-8.000 -0.3857 0.01965 0.01308 -0.0963 0.6561 0.0165
-7.750 -0.3627 0.01889 0.01217 -0.0957 0.6494 0.0169
-7.500 -0.3438 0.01737 0.01051 -0.0947 0.6433 0.0177
-7.250 -0.3220 0.01655 0.00962 -0.0941 0.6377 0.0185
-7.000 -0.2982 0.01599 0.00902 -0.0937 0.6318 0.0196
-6.750 -0.2743 0.01546 0.00838 -0.0933 0.6266 0.0208
-6.500 -0.2491 0.01506 0.00788 -0.0930 0.6216 0.0220
-6.250 -0.2267 0.01421 0.00701 -0.0925 0.6166 0.0247
-6.000 -0.2010 0.01388 0.00661 -0.0923 0.6121 0.0273
-5.750 -0.1764 0.01334 0.00596 -0.0920 0.6079 0.0304
-5.500 -0.1504 0.01293 0.00553 -0.0919 0.6034 0.0342
-5.250 -0.1241 0.01258 0.00510 -0.0917 0.5991 0.0386
-5.000 -0.0978 0.01227 0.00473 -0.0916 0.5953 0.0459
-4.750 -0.0714 0.01185 0.00434 -0.0916 0.5917 0.0599
-4.500 -0.0457 0.01127 0.00394 -0.0916 0.5881 0.1032
-4.250 -0.0214 0.01045 0.00352 -0.0916 0.5847 0.2067
-4.000 0.0032 0.00976 0.00325 -0.0916 0.5813 0.3346
-3.750 0.0302 0.00955 0.00318 -0.0917 0.5780 0.3921
-3.500 0.0583 0.00949 0.00318 -0.0917 0.5745 0.4284
-3.250 0.0867 0.00950 0.00316 -0.0918 0.5712 0.4489
-3.000 0.1152 0.00956 0.00317 -0.0919 0.5683 0.4671
-2.750 0.1437 0.00967 0.00319 -0.0920 0.5656 0.4820
-2.500 0.1722 0.00973 0.00322 -0.0921 0.5630 0.4932
-2.250 0.2006 0.00977 0.00325 -0.0922 0.5602 0.5056
-2.000 0.2291 0.00983 0.00327 -0.0923 0.5574 0.5172
-1.750 0.2575 0.00989 0.00330 -0.0924 0.5546 0.5274
-1.500 0.2859 0.00992 0.00330 -0.0925 0.5522 0.5350
-1.250 0.3146 0.01002 0.00333 -0.0927 0.5498 0.5411
-1.000 0.3433 0.01005 0.00332 -0.0929 0.5477 0.5459
-0.750 0.3717 0.01003 0.00332 -0.0931 0.5454 0.5501
-0.500 0.4003 0.01005 0.00333 -0.0933 0.5430 0.5547
-0.250 0.4289 0.01009 0.00332 -0.0935 0.5407 0.5593
0.000 0.4573 0.01009 0.00331 -0.0937 0.5382 0.5635
0.250 0.4858 0.01017 0.00334 -0.0939 0.5354 0.5682
0.500 0.5141 0.01020 0.00338 -0.0940 0.5328 0.5732
0.750 0.5424 0.01021 0.00340 -0.0942 0.5302 0.5777
1.000 0.5706 0.01022 0.00345 -0.0943 0.5278 0.5823
1.250 0.5991 0.01027 0.00348 -0.0945 0.5255 0.5873
1.500 0.6275 0.01032 0.00353 -0.0948 0.5233 0.5922
1.750 0.6559 0.01041 0.00361 -0.0950 0.5212 0.5972
2.000 0.6843 0.01052 0.00372 -0.0952 0.5191 0.6031
2.250 0.7121 0.01054 0.00381 -0.0953 0.5169 0.6089
2.500 0.7400 0.01058 0.00390 -0.0954 0.5143 0.6155
2.750 0.7681 0.01063 0.00398 -0.0956 0.5119 0.6232
3.000 0.7961 0.01068 0.00408 -0.0957 0.5096 0.6314
3.250 0.8242 0.01077 0.00418 -0.0959 0.5075 0.6398
3.500 0.8527 0.01094 0.00436 -0.0962 0.5051 0.6490
3.750 0.8797 0.01096 0.00450 -0.0962 0.5031 0.6597
4.000 0.9070 0.01099 0.00464 -0.0962 0.5006 0.6727
4.250 0.9342 0.01103 0.00477 -0.0962 0.4979 0.6876
4.500 0.9615 0.01106 0.00489 -0.0963 0.4952 0.7052
4.750 0.9887 0.01110 0.00501 -0.0963 0.4927 0.7283
5.000 1.0156 0.01121 0.00523 -0.0962 0.4900 0.7613
5.250 1.0392 0.01110 0.00539 -0.0954 0.4873 0.8142
5.500 1.0705 0.01086 0.00552 -0.0961 0.4842 1.0000
5.750 1.0979 0.01097 0.00564 -0.0962 0.4813 1.0000
6.000 1.1255 0.01110 0.00577 -0.0963 0.4786 1.0000
6.250 1.1534 0.01131 0.00597 -0.0966 0.4760 1.0000
6.500 1.1796 0.01145 0.00619 -0.0965 0.4731 1.0000
6.750 1.2057 0.01155 0.00637 -0.0964 0.4698 1.0000
7.000 1.2323 0.01167 0.00653 -0.0963 0.4664 1.0000
7.250 1.2590 0.01178 0.00666 -0.0963 0.4629 1.0000
7.500 1.2840 0.01187 0.00682 -0.0959 0.4579 1.0000
7.750 1.3076 0.01180 0.00680 -0.0952 0.4500 1.0000
8.000 1.3295 0.01172 0.00677 -0.0942 0.4379 1.0000
8.250 1.3513 0.01173 0.00680 -0.0932 0.4235 1.0000
8.500 1.3735 0.01184 0.00694 -0.0924 0.4097 1.0000
8.750 1.3953 0.01204 0.00716 -0.0915 0.3968 1.0000
9.000 1.4145 0.01236 0.00744 -0.0903 0.3796 1.0000
9.250 1.4301 0.01283 0.00785 -0.0884 0.3567 1.0000
9.500 1.4396 0.01356 0.00845 -0.0857 0.3253 1.0000
9.750 1.4406 0.01451 0.00923 -0.0815 0.2913 1.0000
10.000 1.4279 0.01592 0.01039 -0.0754 0.2472 1.0000
10.250 1.4108 0.01770 0.01195 -0.0694 0.2057 1.0000
10.500 1.3905 0.02000 0.01406 -0.0641 0.1691 1.0000
10.750 1.3713 0.02278 0.01670 -0.0602 0.1392 1.0000
11.000 1.3510 0.02618 0.01997 -0.0573 0.1099 1.0000
11.250 1.3331 0.02981 0.02349 -0.0552 0.0846 1.0000
11.500 1.3152 0.03368 0.02726 -0.0535 0.0619 1.0000
11.750 1.3004 0.03741 0.03092 -0.0522 0.0442 1.0000
12.000 1.2883 0.04101 0.03448 -0.0511 0.0324 1.0000
12.250 1.2809 0.04425 0.03773 -0.0503 0.0262 1.0000
12.500 1.2776 0.04720 0.04073 -0.0498 0.0225 1.0000
12.750 1.2724 0.05044 0.04400 -0.0493 0.0200 1.0000
13.000 1.2707 0.05344 0.04708 -0.0490 0.0181 1.0000
13.250 1.2709 0.05629 0.04999 -0.0489 0.0167 1.0000
13.500 1.2682 0.05953 0.05328 -0.0488 0.0154 1.0000
13.750 1.2618 0.06332 0.05716 -0.0489 0.0142 1.0000
14.000 1.2640 0.06614 0.06007 -0.0490 0.0131 1.0000
14.250 1.2641 0.06926 0.06327 -0.0492 0.0128 1.0000
14.500 1.2638 0.07251 0.06657 -0.0495 0.0120 1.0000
14.750 1.2616 0.07604 0.07017 -0.0498 0.0114 1.0000
15.000 1.2548 0.08026 0.07446 -0.0504 0.0109 1.0000
15.250 1.2495 0.08430 0.07858 -0.0509 0.0105 1.0000
15.500 1.2528 0.08728 0.08164 -0.0514 0.0102 1.0000
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