FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 73-CL2-152 (fx73cl2152-il) Reynolds number: 1,000,000 Max Cl/Cd: 135.31 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73cl2152-il-1000000-n5.txt Download as CSV file: xf-fx73cl2152-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-CL2-152
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.5191 0.08444 0.08189 -0.0910 0.9873 0.0211
-14.250 -0.5351 0.07692 0.07429 -0.0975 0.9865 0.0213
-14.000 -0.5462 0.06999 0.06728 -0.1043 0.9857 0.0215
-13.750 -0.5694 0.06409 0.06131 -0.1072 0.9818 0.0216
-13.500 -0.5873 0.05743 0.05457 -0.1133 0.9790 0.0218
-13.250 -0.6039 0.04995 0.04697 -0.1220 0.9763 0.0219
-13.000 -0.6367 0.04403 0.04095 -0.1253 0.9688 0.0219
-12.750 -0.6562 0.03644 0.03324 -0.1338 0.9615 0.0220
-12.500 -0.6496 0.02923 0.02586 -0.1454 0.9549 0.0221
-12.250 -0.6242 0.02359 0.02004 -0.1570 0.9484 0.0223
-12.000 -0.5897 0.02081 0.01710 -0.1641 0.9420 0.0227
-11.750 -0.5590 0.01944 0.01564 -0.1671 0.9368 0.0229
-11.500 -0.5287 0.01835 0.01447 -0.1694 0.9300 0.0232
-11.250 -0.4902 0.01732 0.01336 -0.1727 0.9246 0.0236
-11.000 -0.4487 0.01642 0.01236 -0.1764 0.9145 0.0240
-10.750 -0.3684 0.01533 0.01107 -0.1877 0.8913 0.0244
-10.500 -0.2965 0.01456 0.00989 -0.1978 0.8166 0.0251
-10.250 -0.2780 0.01451 0.00944 -0.1964 0.7326 0.0253
-10.000 -0.2549 0.01434 0.00902 -0.1960 0.6790 0.0257
-9.750 -0.2284 0.01415 0.00862 -0.1961 0.6373 0.0260
-9.500 -0.2001 0.01394 0.00822 -0.1965 0.6045 0.0264
-9.250 -0.1706 0.01371 0.00784 -0.1971 0.5776 0.0268
-9.000 -0.1406 0.01347 0.00747 -0.1977 0.5572 0.0272
-8.750 -0.1103 0.01325 0.00713 -0.1984 0.5406 0.0277
-8.500 -0.0800 0.01306 0.00682 -0.1990 0.5262 0.0281
-8.250 -0.0489 0.01279 0.00645 -0.1998 0.5126 0.0286
-8.000 -0.0178 0.01252 0.00612 -0.2006 0.5017 0.0292
-7.750 0.0129 0.01233 0.00584 -0.2012 0.4914 0.0297
-7.500 0.0434 0.01214 0.00559 -0.2017 0.4826 0.0302
-7.000 0.1042 0.01182 0.00513 -0.2027 0.4670 0.0314
-6.750 0.1344 0.01169 0.00492 -0.2031 0.4593 0.0319
-6.500 0.1646 0.01156 0.00473 -0.2034 0.4530 0.0324
-6.250 0.1955 0.01137 0.00450 -0.2040 0.4481 0.0334
-6.000 0.2257 0.01124 0.00434 -0.2044 0.4433 0.0342
-5.750 0.2559 0.01114 0.00418 -0.2047 0.4385 0.0350
-5.500 0.2860 0.01105 0.00404 -0.2050 0.4344 0.0359
-5.250 0.3161 0.01094 0.00390 -0.2053 0.4314 0.0366
-5.000 0.3466 0.01082 0.00375 -0.2057 0.4281 0.0376
-4.750 0.3769 0.01073 0.00363 -0.2061 0.4247 0.0388
-4.500 0.4068 0.01067 0.00354 -0.2063 0.4211 0.0402
-4.000 0.4668 0.01055 0.00335 -0.2068 0.4147 0.0430
-3.750 0.4969 0.01048 0.00327 -0.2071 0.4125 0.0448
-3.500 0.5267 0.01043 0.00321 -0.2073 0.4102 0.0466
-3.250 0.5567 0.01038 0.00314 -0.2075 0.4078 0.0489
-3.000 0.5865 0.01034 0.00309 -0.2077 0.4053 0.0519
-2.750 0.6162 0.01032 0.00305 -0.2079 0.4026 0.0554
-2.500 0.6458 0.01031 0.00302 -0.2081 0.3995 0.0597
-2.250 0.6756 0.01028 0.00300 -0.2083 0.3972 0.0660
-2.000 0.7059 0.01022 0.00297 -0.2086 0.3957 0.0761
-1.750 0.7366 0.01013 0.00294 -0.2091 0.3937 0.0964
-1.500 0.7673 0.01006 0.00294 -0.2095 0.3910 0.1220
-1.250 0.7971 0.01004 0.00296 -0.2098 0.3884 0.1411
-1.000 0.8265 0.01005 0.00299 -0.2099 0.3861 0.1565
-0.750 0.8555 0.01008 0.00303 -0.2100 0.3836 0.1695
-0.500 0.8841 0.01014 0.00308 -0.2100 0.3808 0.1804
-0.250 0.9132 0.01016 0.00313 -0.2100 0.3788 0.1920
0.000 0.9421 0.01019 0.00318 -0.2100 0.3773 0.2024
0.250 0.9711 0.01021 0.00323 -0.2101 0.3754 0.2182
0.500 1.0001 0.01024 0.00330 -0.2101 0.3735 0.2357
0.750 1.0289 0.01027 0.00337 -0.2102 0.3716 0.2509
1.000 1.0572 0.01034 0.00344 -0.2101 0.3697 0.2600
1.250 1.0855 0.01040 0.00351 -0.2100 0.3676 0.2713
1.500 1.1136 0.01048 0.00360 -0.2099 0.3655 0.2843
1.750 1.1415 0.01057 0.00370 -0.2097 0.3632 0.2988
2.000 1.1696 0.01063 0.00380 -0.2096 0.3615 0.3144
2.250 1.1980 0.01068 0.00389 -0.2096 0.3600 0.3323
2.500 1.2261 0.01073 0.00400 -0.2095 0.3581 0.3523
2.750 1.2540 0.01080 0.00410 -0.2093 0.3559 0.3705
3.000 1.2815 0.01088 0.00421 -0.2091 0.3537 0.3882
3.250 1.3089 0.01096 0.00433 -0.2089 0.3515 0.4091
3.500 1.3360 0.01106 0.00447 -0.2086 0.3492 0.4297
3.750 1.3628 0.01118 0.00460 -0.2083 0.3467 0.4485
4.000 1.3896 0.01128 0.00475 -0.2080 0.3446 0.4696
4.250 1.4167 0.01136 0.00489 -0.2077 0.3431 0.4945
4.500 1.4436 0.01144 0.00503 -0.2074 0.3411 0.5173
4.750 1.4702 0.01155 0.00518 -0.2071 0.3385 0.5383
5.000 1.4966 0.01166 0.00534 -0.2067 0.3356 0.5621
5.250 1.5227 0.01179 0.00551 -0.2063 0.3325 0.5881
5.500 1.5483 0.01195 0.00570 -0.2058 0.3294 0.6118
5.750 1.5743 0.01207 0.00588 -0.2053 0.3273 0.6357
6.000 1.6004 0.01219 0.00606 -0.2049 0.3251 0.6599
6.250 1.6263 0.01232 0.00625 -0.2045 0.3223 0.6861
6.500 1.6518 0.01246 0.00646 -0.2040 0.3193 0.7160
6.750 1.6769 0.01262 0.00669 -0.2034 0.3159 0.7531
7.000 1.7014 0.01280 0.00693 -0.2028 0.3122 0.7970
7.250 1.7253 0.01287 0.00715 -0.2019 0.3096 0.8589
7.500 1.7401 0.01286 0.00728 -0.1991 0.3067 1.0000
7.750 1.7636 0.01309 0.00750 -0.1983 0.3023 1.0000
8.000 1.7857 0.01340 0.00777 -0.1972 0.2961 1.0000
8.250 1.8084 0.01366 0.00802 -0.1962 0.2889 1.0000
8.500 1.8290 0.01405 0.00835 -0.1950 0.2803 1.0000
8.750 1.8510 0.01435 0.00864 -0.1939 0.2738 1.0000
9.000 1.8712 0.01476 0.00901 -0.1926 0.2669 1.0000
9.250 1.8927 0.01507 0.00933 -0.1915 0.2622 1.0000
9.500 1.9130 0.01544 0.00969 -0.1901 0.2563 1.0000
9.750 1.9314 0.01591 0.01013 -0.1885 0.2501 1.0000
10.000 1.9519 0.01624 0.01048 -0.1873 0.2465 1.0000
10.250 1.9715 0.01662 0.01088 -0.1859 0.2420 1.0000
10.500 1.9892 0.01713 0.01137 -0.1843 0.2366 1.0000
10.750 2.0076 0.01756 0.01182 -0.1827 0.2322 1.0000
11.000 2.0254 0.01802 0.01230 -0.1811 0.2272 1.0000
11.250 2.0411 0.01862 0.01289 -0.1792 0.2215 1.0000
11.500 2.0578 0.01914 0.01343 -0.1775 0.2168 1.0000
11.750 2.0724 0.01978 0.01408 -0.1755 0.2098 1.0000
12.000 2.0853 0.02054 0.01482 -0.1734 0.2025 1.0000
12.250 2.0938 0.02156 0.01580 -0.1706 0.1911 1.0000
12.500 2.0994 0.02277 0.01696 -0.1675 0.1781 1.0000
12.750 2.1009 0.02426 0.01839 -0.1641 0.1637 1.0000
13.000 2.0993 0.02600 0.02009 -0.1605 0.1501 1.0000
13.250 2.0965 0.02791 0.02197 -0.1569 0.1387 1.0000
13.500 2.0946 0.02984 0.02390 -0.1538 0.1296 1.0000
13.750 2.0919 0.03196 0.02603 -0.1509 0.1223 1.0000
14.000 2.0866 0.03442 0.02852 -0.1481 0.1155 1.0000
14.250 2.0831 0.03693 0.03107 -0.1459 0.1101 1.0000
14.500 2.0743 0.04014 0.03432 -0.1437 0.1042 1.0000
14.750 2.0687 0.04328 0.03753 -0.1422 0.1003 1.0000
15.000 2.0614 0.04687 0.04120 -0.1411 0.0964 1.0000
15.250 2.0493 0.05130 0.04570 -0.1404 0.0928 1.0000
15.500 2.0393 0.05577 0.05027 -0.1401 0.0901 1.0000
15.750 2.0276 0.06069 0.05529 -0.1402 0.0875 1.0000
16.000 2.0120 0.06636 0.06106 -0.1407 0.0850 1.0000
16.250 1.9930 0.07271 0.06752 -0.1415 0.0827 1.0000
16.500 1.9762 0.07890 0.07383 -0.1425 0.0808 1.0000
16.750 1.9602 0.08506 0.08011 -0.1437 0.0789 1.0000
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Polar data table (+)
Polar graphs
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