FX 66-H-80 (fx66h80-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-H-80 (fx66h80-il) Reynolds number: 100,000 Max Cl/Cd: 47.37 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66h80-il-100000-n5.txt Download as CSV file: xf-fx66h80-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-H-80
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5400 0.09296 0.08880 0.0178 1.0000 0.0392
-7.500 -0.5394 0.08928 0.08518 0.0153 1.0000 0.0398
-7.250 -0.5375 0.08548 0.08141 0.0127 1.0000 0.0404
-7.000 -0.5326 0.08143 0.07738 0.0097 1.0000 0.0412
-6.750 -0.5257 0.07732 0.07327 0.0068 1.0000 0.0420
-6.500 -0.5168 0.07314 0.06905 0.0040 1.0000 0.0429
-6.000 -0.4871 0.06608 0.06144 -0.0034 1.0000 0.0474
-5.500 -0.4630 0.05622 0.05176 -0.0034 1.0000 0.0418
-5.000 -0.4111 0.04482 0.03943 -0.0057 0.8862 0.0225
-4.500 -0.3782 0.03858 0.03243 -0.0044 0.7817 0.0259
-4.250 -0.3585 0.03609 0.02948 -0.0033 0.7512 0.0272
-4.000 -0.3363 0.03267 0.02546 -0.0018 0.7271 0.0258
-3.750 -0.3124 0.02962 0.02171 -0.0002 0.7061 0.0247
-3.500 -0.2877 0.02727 0.01880 0.0011 0.6865 0.0242
-3.250 -0.2624 0.02526 0.01629 0.0021 0.6693 0.0241
-3.000 -0.2363 0.02344 0.01403 0.0030 0.6536 0.0243
-2.750 -0.2096 0.02181 0.01206 0.0037 0.6392 0.0248
-2.500 -0.1829 0.02042 0.01042 0.0044 0.6261 0.0257
-2.250 -0.1564 0.01927 0.00903 0.0051 0.6141 0.0272
-2.000 -0.1303 0.01848 0.00807 0.0057 0.6025 0.0318
-1.750 -0.1053 0.01758 0.00704 0.0066 0.5921 0.0368
-1.500 -0.0806 0.01683 0.00615 0.0075 0.5829 0.0434
-1.250 -0.0554 0.01618 0.00543 0.0083 0.5738 0.0637
-1.000 0.0572 0.01278 0.00473 -0.0077 0.5598 1.0000
-0.750 0.0820 0.01282 0.00450 -0.0071 0.5514 1.0000
-0.250 0.1320 0.01296 0.00416 -0.0060 0.5362 1.0000
0.000 0.1568 0.01306 0.00401 -0.0054 0.5298 1.0000
0.250 0.1820 0.01316 0.00396 -0.0049 0.5224 1.0000
0.500 0.2068 0.01328 0.00389 -0.0043 0.5165 1.0000
0.750 0.2321 0.01339 0.00392 -0.0039 0.5095 1.0000
1.000 0.2570 0.01353 0.00390 -0.0033 0.5039 1.0000
1.250 0.2824 0.01367 0.00398 -0.0029 0.4975 1.0000
1.500 0.3075 0.01382 0.00403 -0.0024 0.4918 1.0000
1.750 0.3328 0.01399 0.00414 -0.0019 0.4862 1.0000
2.000 0.3581 0.01416 0.00429 -0.0015 0.4803 1.0000
2.250 0.3831 0.01435 0.00439 -0.0009 0.4757 1.0000
2.500 0.4086 0.01455 0.00462 -0.0006 0.4695 1.0000
2.750 0.4338 0.01475 0.00479 -0.0001 0.4644 1.0000
3.000 0.4591 0.01497 0.00502 0.0003 0.4592 1.0000
3.250 0.4845 0.01520 0.00534 0.0007 0.4536 1.0000
3.500 0.5097 0.01544 0.00556 0.0012 0.4492 1.0000
3.750 0.5351 0.01570 0.00592 0.0015 0.4435 1.0000
4.000 0.5604 0.01596 0.00624 0.0019 0.4382 1.0000
4.250 0.5855 0.01623 0.00653 0.0024 0.4341 1.0000
4.500 0.6109 0.01655 0.00708 0.0027 0.4279 1.0000
4.750 0.6361 0.01683 0.00745 0.0032 0.4231 1.0000
5.000 0.6613 0.01717 0.00791 0.0036 0.4182 1.0000
5.250 0.6864 0.01751 0.00845 0.0039 0.4124 1.0000
5.500 0.7115 0.01782 0.00885 0.0044 0.4080 1.0000
5.750 0.7366 0.01823 0.00959 0.0047 0.4019 1.0000
6.000 0.7616 0.01858 0.01014 0.0052 0.3965 1.0000
6.250 0.7862 0.01868 0.01046 0.0059 0.3852 1.0000
6.500 0.8097 0.01789 0.00971 0.0071 0.3533 1.0000
6.750 0.8332 0.01759 0.00949 0.0079 0.3005 1.0000
7.000 0.8470 0.01949 0.01038 0.0083 0.1177 1.0000
7.250 0.8583 0.02241 0.01284 0.0087 0.0451 1.0000
7.500 0.8749 0.02412 0.01471 0.0094 0.0366 1.0000
7.750 0.8905 0.02575 0.01657 0.0102 0.0317 1.0000
8.000 0.9023 0.02764 0.01861 0.0111 0.0274 1.0000
8.250 0.9154 0.02919 0.02035 0.0121 0.0246 1.0000
8.500 0.9260 0.03090 0.02219 0.0135 0.0229 1.0000
8.750 0.9362 0.03264 0.02401 0.0150 0.0216 1.0000
9.000 0.9468 0.03452 0.02592 0.0166 0.0204 1.0000
9.250 0.9582 0.03714 0.02852 0.0184 0.0186 1.0000
9.500 0.9720 0.03876 0.03039 0.0195 0.0173 1.0000
9.750 0.9847 0.04089 0.03283 0.0207 0.0161 1.0000
10.000 0.9961 0.04348 0.03567 0.0219 0.0156 1.0000
10.250 1.0034 0.04627 0.03873 0.0230 0.0152 1.0000
10.500 1.0045 0.04915 0.04188 0.0242 0.0150 1.0000
10.750 1.0012 0.05231 0.04529 0.0247 0.0149 1.0000
11.000 0.9951 0.05584 0.04907 0.0244 0.0147 1.0000
11.250 0.9874 0.05966 0.05313 0.0233 0.0147 1.0000
11.500 0.9774 0.06399 0.05769 0.0216 0.0147 1.0000
11.750 0.9654 0.06881 0.06272 0.0193 0.0147 1.0000
12.000 0.9531 0.07384 0.06794 0.0166 0.0148 1.0000
12.250 0.9388 0.07945 0.07373 0.0133 0.0148 1.0000
12.500 0.9234 0.08555 0.07999 0.0096 0.0150 1.0000
12.750 0.9076 0.09204 0.08662 0.0056 0.0151 1.0000
13.000 0.8898 0.09936 0.09407 0.0010 0.0153 1.0000
13.250 0.8718 0.10733 0.10215 -0.0040 0.0155 1.0000
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Polar data table (+)
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