GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 655 AIRFOIL (goe655-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.68 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe655-il-1000000.txt Download as CSV file: xf-goe655-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 655 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7321 0.08339 0.08114 -0.0623 1.0000 0.0185
-15.500 -0.8316 0.06418 0.06166 -0.0749 1.0000 0.0183
-15.250 -0.8821 0.05329 0.05060 -0.0823 1.0000 0.0182
-15.000 -0.9161 0.04470 0.04183 -0.0885 1.0000 0.0182
-14.750 -0.9390 0.03766 0.03462 -0.0945 1.0000 0.0183
-14.500 -0.9555 0.03339 0.03020 -0.0971 1.0000 0.0183
-14.250 -0.9833 0.03083 0.02752 -0.0944 1.0000 0.0183
-14.000 -1.0133 0.02996 0.02660 -0.0871 1.0000 0.0184
-13.750 -0.9969 0.02909 0.02563 -0.0869 0.9988 0.0186
-13.500 -0.9794 0.02647 0.02282 -0.0892 0.9957 0.0191
-13.250 -0.9519 0.02543 0.02174 -0.0908 0.9940 0.0195
-13.000 -0.9252 0.02476 0.02104 -0.0916 0.9917 0.0199
-12.750 -0.8975 0.02415 0.02040 -0.0924 0.9893 0.0202
-12.500 -0.8692 0.02344 0.01962 -0.0935 0.9871 0.0206
-12.250 -0.8403 0.02259 0.01868 -0.0947 0.9853 0.0211
-12.000 -0.8097 0.02183 0.01782 -0.0961 0.9839 0.0216
-11.750 -0.7775 0.02119 0.01707 -0.0976 0.9828 0.0220
-11.500 -0.7521 0.02065 0.01645 -0.0976 0.9792 0.0222
-11.250 -0.7296 0.01906 0.01475 -0.0980 0.9756 0.0230
-11.000 -0.6978 0.01857 0.01426 -0.0992 0.9738 0.0235
-10.750 -0.6643 0.01815 0.01381 -0.1006 0.9724 0.0240
-10.500 -0.6298 0.01760 0.01321 -0.1023 0.9711 0.0246
-10.250 -0.5955 0.01702 0.01255 -0.1039 0.9695 0.0252
-10.000 -0.5711 0.01653 0.01199 -0.1034 0.9632 0.0257
-9.750 -0.5395 0.01623 0.01161 -0.1042 0.9592 0.0261
-9.500 -0.5104 0.01503 0.01030 -0.1051 0.9555 0.0269
-9.250 -0.4876 0.01454 0.00980 -0.1042 0.9478 0.0274
-9.000 -0.4585 0.01413 0.00935 -0.1045 0.9420 0.0280
-8.750 -0.4330 0.01377 0.00894 -0.1040 0.9340 0.0285
-8.500 -0.4056 0.01343 0.00854 -0.1039 0.9254 0.0292
-8.250 -0.3809 0.01313 0.00818 -0.1032 0.9147 0.0298
-8.000 -0.3549 0.01282 0.00778 -0.1026 0.9042 0.0304
-7.750 -0.3292 0.01257 0.00743 -0.1020 0.8917 0.0307
-7.500 -0.3083 0.01181 0.00658 -0.1007 0.8772 0.0315
-7.250 -0.2846 0.01144 0.00616 -0.0998 0.8612 0.0323
-7.000 -0.2601 0.01122 0.00586 -0.0990 0.8434 0.0330
-6.750 -0.2357 0.01100 0.00555 -0.0981 0.8255 0.0337
-6.500 -0.2113 0.01078 0.00524 -0.0972 0.8083 0.0344
-6.250 -0.1867 0.01059 0.00495 -0.0964 0.7917 0.0350
-5.750 -0.1371 0.01022 0.00440 -0.0948 0.7622 0.0363
-5.500 -0.1134 0.00985 0.00397 -0.0939 0.7494 0.0375
-5.250 -0.0882 0.00969 0.00374 -0.0932 0.7375 0.0386
-4.750 -0.0365 0.00941 0.00335 -0.0920 0.7165 0.0407
-4.500 -0.0104 0.00931 0.00319 -0.0914 0.7071 0.0416
-4.250 0.0154 0.00909 0.00292 -0.0909 0.6976 0.0434
-4.000 0.0414 0.00894 0.00275 -0.0903 0.6886 0.0455
-3.750 0.0678 0.00884 0.00261 -0.0898 0.6787 0.0476
-3.500 0.0943 0.00873 0.00245 -0.0893 0.6689 0.0499
-3.250 0.1199 0.00859 0.00229 -0.0887 0.6580 0.0542
-3.000 0.1463 0.00848 0.00216 -0.0882 0.6458 0.0595
-2.750 0.1723 0.00836 0.00203 -0.0877 0.6338 0.0689
-2.500 0.1975 0.00818 0.00190 -0.0870 0.6207 0.0915
-2.250 0.2218 0.00794 0.00181 -0.0863 0.6066 0.1435
-2.000 0.2468 0.00782 0.00175 -0.0856 0.5913 0.1797
-1.750 0.2720 0.00775 0.00171 -0.0850 0.5752 0.2111
-1.500 0.2971 0.00770 0.00169 -0.0843 0.5587 0.2417
-1.250 0.3223 0.00767 0.00168 -0.0837 0.5420 0.2719
-1.000 0.3474 0.00766 0.00168 -0.0830 0.5244 0.3013
-0.750 0.3724 0.00769 0.00170 -0.0823 0.5051 0.3298
-0.500 0.3972 0.00770 0.00172 -0.0816 0.4856 0.3617
-0.250 0.4217 0.00771 0.00176 -0.0809 0.4667 0.4006
0.000 0.4457 0.00771 0.00181 -0.0801 0.4479 0.4493
0.250 0.4695 0.00770 0.00186 -0.0792 0.4303 0.5021
0.500 0.4922 0.00761 0.00192 -0.0781 0.4142 0.5763
0.750 0.5127 0.00742 0.00201 -0.0765 0.4006 0.6883
1.000 0.5324 0.00727 0.00209 -0.0747 0.3891 0.7875
1.250 0.5545 0.00713 0.00222 -0.0731 0.3786 0.8985
1.500 0.6256 0.00732 0.00240 -0.0825 0.3659 0.9663
2.000 0.7080 0.00768 0.00261 -0.0882 0.3495 0.9923
2.250 0.7501 0.00783 0.00270 -0.0912 0.3430 0.9983
2.500 0.7836 0.00795 0.00277 -0.0925 0.3375 1.0000
2.750 0.8053 0.00810 0.00286 -0.0912 0.3320 1.0000
3.000 0.8279 0.00821 0.00295 -0.0900 0.3282 1.0000
3.250 0.8511 0.00830 0.00302 -0.0890 0.3246 1.0000
3.500 0.8739 0.00842 0.00312 -0.0879 0.3205 1.0000
3.750 0.8963 0.00857 0.00322 -0.0868 0.3167 1.0000
4.000 0.9188 0.00871 0.00334 -0.0856 0.3128 1.0000
4.250 0.9426 0.00880 0.00343 -0.0848 0.3102 1.0000
4.500 0.9660 0.00891 0.00354 -0.0838 0.3070 1.0000
4.750 0.9891 0.00905 0.00365 -0.0828 0.3035 1.0000
5.000 1.0114 0.00922 0.00379 -0.0817 0.2995 1.0000
5.250 1.0346 0.00935 0.00392 -0.0808 0.2960 1.0000
5.500 1.0585 0.00945 0.00403 -0.0800 0.2927 1.0000
5.750 1.0817 0.00958 0.00415 -0.0790 0.2889 1.0000
6.000 1.1040 0.00975 0.00430 -0.0779 0.2847 1.0000
6.250 1.1265 0.00991 0.00445 -0.0769 0.2807 1.0000
6.500 1.1501 0.01002 0.00458 -0.0761 0.2770 1.0000
6.750 1.1727 0.01018 0.00473 -0.0751 0.2721 1.0000
7.000 1.1938 0.01039 0.00491 -0.0738 0.2662 1.0000
7.250 1.2170 0.01052 0.00506 -0.0729 0.2608 1.0000
7.500 1.2375 0.01075 0.00524 -0.0716 0.2520 1.0000
7.750 1.2578 0.01100 0.00544 -0.0703 0.2392 1.0000
8.000 1.2742 0.01135 0.00570 -0.0682 0.2222 1.0000
8.250 1.2885 0.01175 0.00600 -0.0658 0.2044 1.0000
8.500 1.3017 0.01221 0.00637 -0.0632 0.1893 1.0000
8.750 1.3161 0.01265 0.00674 -0.0609 0.1796 1.0000
9.000 1.3328 0.01300 0.00708 -0.0591 0.1737 1.0000
9.250 1.3487 0.01340 0.00747 -0.0572 0.1686 1.0000
9.500 1.3661 0.01375 0.00783 -0.0555 0.1648 1.0000
9.750 1.3846 0.01406 0.00816 -0.0541 0.1622 1.0000
10.000 1.4015 0.01446 0.00856 -0.0525 0.1585 1.0000
10.250 1.4175 0.01490 0.00901 -0.0508 0.1551 1.0000
10.500 1.4332 0.01537 0.00949 -0.0491 0.1516 1.0000
10.750 1.4527 0.01567 0.00983 -0.0480 0.1494 1.0000
11.000 1.4705 0.01606 0.01025 -0.0467 0.1466 1.0000
11.250 1.4860 0.01658 0.01076 -0.0452 0.1427 1.0000
11.500 1.4998 0.01720 0.01139 -0.0435 0.1381 1.0000
11.750 1.5187 0.01757 0.01180 -0.0425 0.1358 1.0000
12.000 1.5350 0.01809 0.01234 -0.0412 0.1312 1.0000
12.250 1.5478 0.01882 0.01305 -0.0396 0.1246 1.0000
12.500 1.5597 0.01963 0.01382 -0.0380 0.1146 1.0000
12.750 1.5632 0.02100 0.01506 -0.0357 0.0948 1.0000
13.000 1.5387 0.02434 0.01811 -0.0312 0.0568 1.0000
13.250 1.5131 0.02821 0.02185 -0.0276 0.0287 1.0000
13.500 1.5049 0.03103 0.02466 -0.0259 0.0197 1.0000
13.750 1.5074 0.03308 0.02677 -0.0249 0.0181 1.0000
14.000 1.5096 0.03522 0.02898 -0.0241 0.0167 1.0000
14.250 1.5120 0.03742 0.03125 -0.0234 0.0160 1.0000
14.500 1.5140 0.03974 0.03364 -0.0229 0.0155 1.0000
14.750 1.5105 0.04271 0.03669 -0.0225 0.0148 1.0000
15.250 1.5064 0.04861 0.04277 -0.0222 0.0139 1.0000
15.500 1.5041 0.05174 0.04599 -0.0223 0.0137 1.0000
15.750 1.5005 0.05509 0.04943 -0.0226 0.0134 1.0000
16.000 1.4943 0.05883 0.05327 -0.0230 0.0131 1.0000
16.250 1.4869 0.06285 0.05739 -0.0235 0.0129 1.0000
16.500 1.4768 0.06730 0.06194 -0.0243 0.0126 1.0000
16.750 1.4650 0.07202 0.06676 -0.0252 0.0124 1.0000
17.000 1.4534 0.07682 0.07167 -0.0263 0.0122 1.0000
17.250 1.4397 0.08198 0.07693 -0.0275 0.0121 1.0000
17.500 1.4199 0.08808 0.08316 -0.0291 0.0119 1.0000
17.750 1.4042 0.09366 0.08884 -0.0305 0.0118 1.0000
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