WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.43 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66a175-il-1000000.txt Download as CSV file: xf-fx66a175-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 66-17A-175 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.1519 0.09119 0.08807 -0.0749 0.5763 0.0096
-12.000 -0.3649 0.05681 0.05338 -0.1017 0.6097 0.0052
-11.750 -0.3973 0.04970 0.04610 -0.1057 0.6065 0.0052
-11.500 -0.4153 0.04509 0.04135 -0.1080 0.6018 0.0051
-11.250 -0.4392 0.04010 0.03615 -0.1099 0.5977 0.0052
-11.000 -0.4645 0.03518 0.03101 -0.1111 0.5939 0.0050
-10.750 -0.4762 0.03198 0.02762 -0.1115 0.5891 0.0052
-10.500 -0.4901 0.02917 0.02460 -0.1107 0.5845 0.0051
-10.250 -0.4988 0.02713 0.02236 -0.1080 0.5804 0.0051
-10.000 -0.4933 0.02542 0.02045 -0.1066 0.5758 0.0054
-9.750 -0.4840 0.02381 0.01863 -0.1053 0.5714 0.0054
-9.500 -0.4685 0.02276 0.01742 -0.1044 0.5671 0.0057
-9.250 -0.4503 0.02190 0.01643 -0.1037 0.5630 0.0059
-9.000 -0.4297 0.02137 0.01576 -0.1031 0.5586 0.0060
-8.750 -0.4187 0.01911 0.01323 -0.1016 0.5550 0.0062
-8.500 -0.4021 0.01776 0.01180 -0.1006 0.5517 0.0067
-8.250 -0.3809 0.01701 0.01097 -0.1000 0.5480 0.0068
-8.000 -0.3578 0.01652 0.01042 -0.0996 0.5441 0.0072
-7.750 -0.3351 0.01598 0.00979 -0.0991 0.5402 0.0074
-7.500 -0.3121 0.01535 0.00910 -0.0987 0.5370 0.0078
-7.250 -0.2884 0.01481 0.00849 -0.0982 0.5335 0.0082
-7.000 -0.2632 0.01448 0.00808 -0.0980 0.5300 0.0087
-6.750 -0.2390 0.01405 0.00756 -0.0976 0.5265 0.0092
-6.500 -0.2183 0.01308 0.00650 -0.0969 0.5239 0.0100
-6.250 -0.1929 0.01269 0.00607 -0.0967 0.5210 0.0107
-6.000 -0.1674 0.01230 0.00562 -0.0964 0.5181 0.0112
-5.750 -0.1417 0.01197 0.00522 -0.0962 0.5151 0.0120
-5.500 -0.1157 0.01169 0.00485 -0.0960 0.5119 0.0126
-5.250 -0.0896 0.01133 0.00442 -0.0959 0.5096 0.0137
-5.000 -0.0632 0.01095 0.00399 -0.0957 0.5073 0.0156
-4.750 -0.0361 0.01071 0.00372 -0.0957 0.5048 0.0176
-4.500 -0.0092 0.01044 0.00341 -0.0956 0.5023 0.0228
-4.250 0.0167 0.01005 0.00311 -0.0954 0.4998 0.0526
-4.000 0.0415 0.00955 0.00282 -0.0953 0.4969 0.1214
-3.750 0.0657 0.00877 0.00247 -0.0952 0.4952 0.2398
-3.500 0.0896 0.00799 0.00219 -0.0950 0.4932 0.3863
-3.250 0.1180 0.00795 0.00222 -0.0952 0.4911 0.4266
-3.000 0.1469 0.00800 0.00223 -0.0954 0.4888 0.4436
-2.750 0.1755 0.00806 0.00226 -0.0955 0.4866 0.4550
-2.500 0.2041 0.00815 0.00228 -0.0956 0.4843 0.4629
-2.250 0.2326 0.00827 0.00235 -0.0957 0.4819 0.4705
-2.000 0.2615 0.00832 0.00239 -0.0959 0.4803 0.4784
-1.750 0.2903 0.00839 0.00245 -0.0961 0.4785 0.4839
-1.500 0.3192 0.00849 0.00249 -0.0963 0.4765 0.4885
-1.250 0.3477 0.00846 0.00244 -0.0965 0.4745 0.4914
-1.000 0.3761 0.00848 0.00243 -0.0966 0.4723 0.4936
-0.750 0.4042 0.00854 0.00245 -0.0967 0.4698 0.4959
-0.500 0.4326 0.00859 0.00246 -0.0969 0.4675 0.4979
-0.250 0.4613 0.00859 0.00246 -0.0971 0.4656 0.4995
0.000 0.4900 0.00861 0.00245 -0.0974 0.4637 0.5008
0.250 0.5185 0.00863 0.00245 -0.0976 0.4618 0.5020
0.500 0.5469 0.00867 0.00246 -0.0978 0.4598 0.5031
0.750 0.5751 0.00870 0.00247 -0.0979 0.4578 0.5042
1.000 0.6028 0.00874 0.00249 -0.0980 0.4553 0.5058
1.250 0.6308 0.00878 0.00253 -0.0982 0.4533 0.5073
1.500 0.6592 0.00880 0.00256 -0.0984 0.4518 0.5086
1.750 0.6875 0.00883 0.00260 -0.0986 0.4501 0.5100
2.000 0.7157 0.00886 0.00265 -0.0988 0.4485 0.5114
2.250 0.7438 0.00891 0.00270 -0.0990 0.4468 0.5129
2.500 0.7718 0.00897 0.00276 -0.0991 0.4451 0.5144
2.750 0.7995 0.00904 0.00283 -0.0992 0.4434 0.5160
3.000 0.8271 0.00915 0.00292 -0.0993 0.4415 0.5174
3.250 0.8547 0.00928 0.00304 -0.0995 0.4395 0.5189
3.500 0.8826 0.00929 0.00310 -0.0996 0.4385 0.5209
3.750 0.9104 0.00933 0.00318 -0.0998 0.4373 0.5226
4.000 0.9382 0.00938 0.00327 -0.0999 0.4360 0.5244
4.250 0.9659 0.00944 0.00337 -0.1001 0.4346 0.5262
4.500 0.9935 0.00951 0.00347 -0.1002 0.4332 0.5282
4.750 1.0211 0.00959 0.00358 -0.1004 0.4318 0.5305
5.000 1.0485 0.00968 0.00369 -0.1005 0.4305 0.5326
5.250 1.0756 0.00976 0.00381 -0.1005 0.4291 0.5352
5.500 1.1026 0.00987 0.00396 -0.1006 0.4276 0.5378
5.750 1.1296 0.01005 0.00416 -0.1007 0.4258 0.5404
6.000 1.1567 0.01010 0.00429 -0.1008 0.4243 0.5432
6.250 1.1835 0.01004 0.00430 -0.1007 0.4203 0.5460
6.500 1.2102 0.01004 0.00434 -0.1007 0.4166 0.5488
6.750 1.2354 0.01015 0.00445 -0.1004 0.4113 0.5523
7.000 1.2625 0.01011 0.00452 -0.1005 0.4069 0.5559
7.250 1.2883 0.01016 0.00460 -0.1003 0.4007 0.5597
7.500 1.3138 0.01023 0.00470 -0.1001 0.3912 0.5638
7.750 1.3349 0.01049 0.00488 -0.0991 0.3696 0.5686
8.000 1.3246 0.01246 0.00616 -0.0931 0.2497 0.5726
8.250 1.2991 0.01464 0.00782 -0.0846 0.1605 0.5760
8.500 1.2633 0.01685 0.00966 -0.0746 0.0875 0.5795
8.750 1.2418 0.01876 0.01140 -0.0680 0.0450 0.5844
9.000 1.2117 0.02160 0.01414 -0.0619 0.0093 0.5894
9.250 1.2119 0.02328 0.01591 -0.0599 0.0067 0.5972
9.500 1.2139 0.02510 0.01782 -0.0585 0.0059 0.6075
10.000 1.2140 0.02956 0.02256 -0.0563 0.0050 0.6407
10.250 1.2149 0.03176 0.02492 -0.0554 0.0048 0.6733
10.500 1.2325 0.03374 0.02766 -0.0582 0.0045 1.0000
10.750 1.2315 0.03639 0.03037 -0.0576 0.0040 1.0000
11.000 1.2294 0.03913 0.03317 -0.0570 0.0038 1.0000
11.250 1.2280 0.04183 0.03594 -0.0564 0.0039 1.0000
11.500 1.2232 0.04485 0.03903 -0.0557 0.0037 1.0000
11.750 1.2212 0.04766 0.04190 -0.0552 0.0038 1.0000
12.000 1.2036 0.05219 0.04656 -0.0546 0.0033 1.0000
12.250 1.2127 0.05401 0.04840 -0.0545 0.0035 1.0000
12.500 1.2017 0.05811 0.05260 -0.0543 0.0034 1.0000
12.750 1.2005 0.06117 0.05573 -0.0542 0.0032 1.0000
13.000 1.2005 0.06414 0.05877 -0.0541 0.0032 1.0000
13.250 1.2011 0.06714 0.06182 -0.0542 0.0031 1.0000
13.500 1.2001 0.07031 0.06507 -0.0542 0.0030 1.0000
13.750 1.1985 0.07363 0.06845 -0.0544 0.0030 1.0000
14.000 1.1988 0.07673 0.07161 -0.0546 0.0030 1.0000
14.250 1.1969 0.08018 0.07514 -0.0548 0.0029 1.0000
14.500 1.1997 0.08301 0.07801 -0.0551 0.0030 1.0000
14.750 1.1991 0.08633 0.08140 -0.0554 0.0029 1.0000
15.000 1.1993 0.08953 0.08466 -0.0557 0.0030 1.0000
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