GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 417 AIRFOIL (goe417-il) Reynolds number: 200,000 Max Cl/Cd: 82.8 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe417-il-200000.txt Download as CSV file: xf-goe417-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3069 0.09734 0.09420 -0.0152 1.0000 0.0242
-7.000 -0.3186 0.09647 0.09340 -0.0122 1.0000 0.0243
-6.750 -0.3275 0.09526 0.09225 -0.0101 1.0000 0.0246
-6.500 -0.3321 0.09368 0.09072 -0.0092 1.0000 0.0249
-6.250 -0.3343 0.09208 0.08916 -0.0091 1.0000 0.0253
-6.000 -0.2985 0.08891 0.08596 -0.0211 0.9952 0.0260
-5.750 -0.2536 0.08506 0.08200 -0.0348 0.9890 0.0262
-5.500 -0.2191 0.07988 0.07678 -0.0427 0.9848 0.0264
-5.250 -0.2105 0.07471 0.07166 -0.0406 0.9816 0.0269
-5.000 -0.1895 0.07091 0.06785 -0.0430 0.9761 0.0277
-4.750 -0.1558 0.06701 0.06390 -0.0491 0.9720 0.0290
-4.500 -0.1188 0.06328 0.06011 -0.0560 0.9667 0.0315
-4.250 -0.0448 0.06012 0.05663 -0.0720 0.9602 0.0337
-4.000 -0.0114 0.05407 0.05055 -0.0774 0.9568 0.0345
-3.750 0.0107 0.05066 0.04716 -0.0787 0.9492 0.0358
-3.500 0.0555 0.04700 0.04339 -0.0848 0.9443 0.0384
-3.250 0.1302 0.04238 0.03836 -0.0970 0.9414 0.0446
-3.000 0.1519 0.03945 0.03547 -0.0977 0.9324 0.0465
-2.750 0.1970 0.03656 0.03244 -0.1027 0.9291 0.0517
-2.500 0.2653 0.01503 0.01096 -0.1074 0.9122 0.0635
-2.250 0.2977 0.01324 0.00887 -0.1092 0.9031 0.0721
-2.000 0.3298 0.01134 0.00694 -0.1109 0.8984 0.0790
-1.750 0.3579 0.00994 0.00533 -0.1115 0.8890 0.0884
-1.500 0.3915 0.00847 0.00368 -0.1130 0.8835 0.1023
-1.250 0.4165 0.00758 0.00269 -0.1128 0.8725 0.1177
-1.000 0.4436 0.00670 0.00170 -0.1129 0.8626 0.1339
-0.750 0.4727 0.00587 0.00072 -0.1131 0.8534 0.1603
0.250 0.6093 0.01496 0.00814 -0.1163 0.8305 0.0818
0.500 0.6383 0.01398 0.00686 -0.1155 0.8158 0.0716
0.750 0.6660 0.01347 0.00623 -0.1147 0.7994 0.0692
1.000 0.6933 0.01279 0.00545 -0.1140 0.7819 0.0680
1.250 0.7187 0.01234 0.00494 -0.1130 0.7601 0.0677
1.500 0.7446 0.01208 0.00457 -0.1121 0.7373 0.0695
1.750 0.7693 0.01175 0.00420 -0.1110 0.7113 0.0718
2.000 0.7940 0.01160 0.00395 -0.1100 0.6830 0.0731
2.250 0.8181 0.01162 0.00378 -0.1088 0.6519 0.0759
2.500 0.8415 0.01177 0.00372 -0.1076 0.6189 0.0813
2.750 0.8643 0.01190 0.00374 -0.1063 0.5844 0.1070
3.000 0.8934 0.01079 0.00391 -0.1067 0.5481 1.0000
3.250 0.9160 0.01114 0.00401 -0.1055 0.5169 1.0000
3.500 0.9390 0.01149 0.00416 -0.1045 0.4909 1.0000
3.750 0.9623 0.01185 0.00435 -0.1036 0.4688 1.0000
4.000 0.9857 0.01222 0.00459 -0.1027 0.4499 1.0000
4.250 1.0093 0.01259 0.00484 -0.1019 0.4336 1.0000
4.500 1.0331 0.01296 0.00511 -0.1011 0.4193 1.0000
4.750 1.0571 0.01332 0.00541 -0.1004 0.4062 1.0000
5.000 1.0810 0.01369 0.00572 -0.0997 0.3940 1.0000
5.250 1.1047 0.01408 0.00607 -0.0990 0.3825 1.0000
5.500 1.1283 0.01450 0.00642 -0.0982 0.3715 1.0000
5.750 1.1520 0.01483 0.00678 -0.0975 0.3599 1.0000
6.000 1.1756 0.01521 0.00718 -0.0968 0.3488 1.0000
6.250 1.1988 0.01563 0.00761 -0.0960 0.3379 1.0000
6.500 1.2217 0.01608 0.00804 -0.0952 0.3271 1.0000
6.750 1.2440 0.01646 0.00846 -0.0943 0.3141 1.0000
7.000 1.2652 0.01683 0.00885 -0.0932 0.2992 1.0000
7.250 1.2857 0.01715 0.00922 -0.0920 0.2820 1.0000
7.500 1.3061 0.01743 0.00956 -0.0908 0.2629 1.0000
7.750 1.3266 0.01780 0.00996 -0.0896 0.2461 1.0000
8.000 1.3466 0.01822 0.01040 -0.0884 0.2299 1.0000
8.250 1.3658 0.01868 0.01087 -0.0871 0.2106 1.0000
8.500 1.3845 0.01922 0.01140 -0.0858 0.1900 1.0000
8.750 1.4007 0.01996 0.01206 -0.0841 0.1630 1.0000
9.000 1.4059 0.02178 0.01329 -0.0811 0.0712 1.0000
9.250 1.4042 0.02421 0.01541 -0.0770 0.0405 1.0000
9.500 1.4111 0.02559 0.01693 -0.0738 0.0349 1.0000
9.750 1.4185 0.02683 0.01831 -0.0708 0.0320 1.0000
10.000 1.4214 0.02833 0.01997 -0.0674 0.0299 1.0000
10.250 1.4161 0.03038 0.02216 -0.0634 0.0283 1.0000
10.500 1.4192 0.03194 0.02385 -0.0606 0.0274 1.0000
10.750 1.4218 0.03361 0.02566 -0.0580 0.0259 1.0000
11.000 1.4216 0.03560 0.02777 -0.0555 0.0250 1.0000
11.250 1.4208 0.03780 0.03008 -0.0532 0.0244 1.0000
11.500 1.4201 0.04015 0.03253 -0.0511 0.0238 1.0000
11.750 1.4199 0.04264 0.03511 -0.0494 0.0232 1.0000
12.000 1.4208 0.04521 0.03777 -0.0478 0.0228 1.0000
12.250 1.4235 0.04785 0.04050 -0.0464 0.0223 1.0000
12.500 1.4301 0.05044 0.04316 -0.0450 0.0220 1.0000
12.750 1.4410 0.05331 0.04613 -0.0436 0.0214 1.0000
13.000 1.4517 0.05705 0.05005 -0.0424 0.0208 1.0000
13.250 1.4486 0.05985 0.05308 -0.0416 0.0204 1.0000
13.500 1.4474 0.06312 0.05658 -0.0409 0.0202 1.0000
13.750 1.4465 0.06688 0.06057 -0.0404 0.0202 1.0000
14.000 1.4421 0.07101 0.06494 -0.0402 0.0202 1.0000
14.250 1.4349 0.07557 0.06974 -0.0403 0.0202 1.0000
14.500 1.4249 0.08053 0.07494 -0.0410 0.0203 1.0000
14.750 1.4131 0.08595 0.08059 -0.0421 0.0204 1.0000
15.000 1.4008 0.09196 0.08681 -0.0436 0.0207 1.0000
15.250 1.3930 0.09781 0.09289 -0.0449 0.0210 1.0000
15.500 1.3811 0.10289 0.09815 -0.0474 0.0211 1.0000
15.750 1.3682 0.10844 0.10389 -0.0505 0.0213 1.0000
16.000 1.3538 0.11464 0.11029 -0.0544 0.0215 1.0000
16.250 1.3373 0.12175 0.11761 -0.0591 0.0217 1.0000
16.500 1.3172 0.13028 0.12637 -0.0651 0.0221 1.0000
16.750 1.2927 0.14062 0.13695 -0.0726 0.0226 1.0000
17.000 1.2631 0.15314 0.14970 -0.0819 0.0230 1.0000
17.250 1.2275 0.16900 0.16577 -0.0935 0.0236 1.0000
17.500 1.1793 0.19272 0.18954 -0.1088 0.0257 1.0000
17.750 1.1705 0.20233 0.19913 -0.1139 0.0274 1.0000
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Polar data table (+)
Polar graphs
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