GOE 701 AIRFOIL (goe701-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 701 AIRFOIL (goe701-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.32 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe701-il-1000000-n5.txt Download as CSV file: xf-goe701-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 701 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6630 0.09863 0.09642 -0.0630 1.0000 0.0196
-15.250 -1.0313 0.02863 0.02517 -0.1227 0.9838 0.0146
-15.000 -1.0238 0.02598 0.02235 -0.1229 0.9797 0.0152
-14.750 -1.0079 0.02419 0.02042 -0.1232 0.9764 0.0160
-14.500 -0.9867 0.02274 0.01886 -0.1239 0.9742 0.0168
-14.250 -0.9632 0.02132 0.01733 -0.1248 0.9726 0.0179
-14.000 -0.9365 0.02012 0.01604 -0.1261 0.9714 0.0195
-13.750 -0.9174 0.01926 0.01510 -0.1253 0.9670 0.0208
-13.500 -0.8939 0.01841 0.01419 -0.1253 0.9636 0.0223
-13.250 -0.8664 0.01771 0.01341 -0.1259 0.9611 0.0237
-13.000 -0.8376 0.01701 0.01266 -0.1268 0.9588 0.0250
-12.750 -0.8134 0.01646 0.01205 -0.1265 0.9550 0.0262
-12.500 -0.7898 0.01599 0.01152 -0.1260 0.9502 0.0273
-12.250 -0.7623 0.01553 0.01098 -0.1262 0.9462 0.0282
-12.000 -0.7342 0.01501 0.01042 -0.1266 0.9426 0.0293
-11.750 -0.7122 0.01464 0.01001 -0.1256 0.9366 0.0304
-11.500 -0.6862 0.01428 0.00959 -0.1254 0.9311 0.0314
-11.250 -0.6593 0.01393 0.00916 -0.1253 0.9260 0.0322
-11.000 -0.6353 0.01363 0.00879 -0.1246 0.9187 0.0327
-10.750 -0.6096 0.01323 0.00833 -0.1243 0.9118 0.0337
-10.500 -0.5852 0.01291 0.00797 -0.1237 0.9035 0.0345
-10.250 -0.5591 0.01264 0.00764 -0.1233 0.8950 0.0355
-10.000 -0.5341 0.01238 0.00732 -0.1227 0.8851 0.0363
-9.750 -0.5085 0.01216 0.00701 -0.1222 0.8754 0.0372
-9.500 -0.4832 0.01195 0.00672 -0.1217 0.8647 0.0378
-9.250 -0.4584 0.01171 0.00639 -0.1210 0.8542 0.0385
-9.000 -0.4339 0.01145 0.00608 -0.1203 0.8444 0.0398
-8.750 -0.4088 0.01127 0.00585 -0.1197 0.8342 0.0410
-8.500 -0.3836 0.01108 0.00559 -0.1190 0.8252 0.0417
-8.000 -0.3332 0.01071 0.00508 -0.1178 0.8081 0.0430
-7.750 -0.3079 0.01056 0.00486 -0.1171 0.7998 0.0436
-7.500 -0.2819 0.01041 0.00464 -0.1166 0.7927 0.0441
-7.250 -0.2569 0.01019 0.00436 -0.1160 0.7849 0.0449
-7.000 -0.2315 0.00998 0.00410 -0.1154 0.7785 0.0460
-6.750 -0.2057 0.00980 0.00389 -0.1148 0.7714 0.0469
-6.500 -0.1801 0.00965 0.00369 -0.1142 0.7649 0.0478
-6.250 -0.1537 0.00950 0.00351 -0.1138 0.7586 0.0488
-6.000 -0.1276 0.00938 0.00334 -0.1133 0.7519 0.0498
-5.750 -0.1014 0.00927 0.00318 -0.1128 0.7460 0.0507
-5.500 -0.0748 0.00916 0.00303 -0.1124 0.7398 0.0513
-5.250 -0.0490 0.00901 0.00284 -0.1118 0.7334 0.0528
-5.000 -0.0228 0.00887 0.00268 -0.1114 0.7278 0.0545
-4.750 0.0036 0.00875 0.00255 -0.1109 0.7216 0.0562
-4.500 0.0297 0.00866 0.00242 -0.1104 0.7155 0.0578
-4.250 0.0564 0.00857 0.00230 -0.1100 0.7100 0.0593
-4.000 0.0827 0.00846 0.00219 -0.1096 0.7036 0.0626
-3.750 0.1086 0.00837 0.00209 -0.1090 0.6976 0.0665
-3.500 0.1354 0.00827 0.00200 -0.1086 0.6916 0.0713
-3.250 0.1615 0.00820 0.00194 -0.1082 0.6850 0.0777
-3.000 0.1878 0.00814 0.00189 -0.1077 0.6791 0.0839
-2.750 0.2144 0.00810 0.00184 -0.1073 0.6717 0.0888
-2.500 0.2402 0.00808 0.00179 -0.1067 0.6628 0.0923
-2.250 0.2664 0.00804 0.00175 -0.1062 0.6541 0.0965
-2.000 0.2922 0.00803 0.00171 -0.1056 0.6453 0.0996
-1.750 0.3179 0.00804 0.00168 -0.1050 0.6344 0.1016
-1.500 0.3437 0.00805 0.00164 -0.1044 0.6234 0.1029
-1.250 0.3689 0.00806 0.00161 -0.1037 0.6124 0.1056
-1.000 0.3936 0.00808 0.00159 -0.1029 0.5991 0.1091
-0.750 0.4185 0.00810 0.00158 -0.1022 0.5850 0.1120
-0.500 0.4431 0.00815 0.00157 -0.1014 0.5701 0.1145
-0.250 0.4680 0.00819 0.00158 -0.1007 0.5568 0.1167
0.000 0.4928 0.00824 0.00158 -0.0999 0.5451 0.1200
0.250 0.5174 0.00828 0.00160 -0.0992 0.5342 0.1251
0.500 0.5427 0.00830 0.00162 -0.0985 0.5241 0.1299
0.750 0.5674 0.00835 0.00165 -0.0978 0.5137 0.1355
1.000 0.5917 0.00839 0.00169 -0.0970 0.5026 0.1461
1.250 0.6161 0.00843 0.00174 -0.0962 0.4913 0.1587
1.500 0.6398 0.00851 0.00180 -0.0953 0.4774 0.1706
1.750 0.6633 0.00860 0.00187 -0.0943 0.4641 0.1815
2.000 0.6865 0.00870 0.00194 -0.0933 0.4496 0.1924
2.250 0.7096 0.00881 0.00202 -0.0923 0.4357 0.2012
2.500 0.7326 0.00892 0.00211 -0.0912 0.4214 0.2111
2.750 0.7550 0.00904 0.00220 -0.0901 0.4061 0.2219
3.000 0.7765 0.00919 0.00231 -0.0888 0.3887 0.2351
3.250 0.7966 0.00937 0.00245 -0.0872 0.3681 0.2551
3.500 0.8163 0.00949 0.00260 -0.0856 0.3491 0.2970
3.750 0.8348 0.00959 0.00276 -0.0838 0.3314 0.3592
4.000 0.8513 0.00965 0.00292 -0.0815 0.3147 0.4324
4.500 0.9747 0.00962 0.00391 -0.0974 0.2609 0.9981
4.750 1.0050 0.00993 0.00413 -0.0982 0.2465 1.0000
5.000 1.0221 0.01013 0.00429 -0.0960 0.2392 1.0000
5.250 1.0391 0.01031 0.00445 -0.0938 0.2324 1.0000
5.500 1.0523 0.01054 0.00462 -0.0908 0.2235 1.0000
5.750 1.0672 0.01073 0.00478 -0.0882 0.2166 1.0000
6.000 1.0819 0.01097 0.00498 -0.0855 0.2091 1.0000
6.250 1.0995 0.01115 0.00516 -0.0835 0.2045 1.0000
6.500 1.1174 0.01135 0.00535 -0.0816 0.2005 1.0000
6.750 1.1344 0.01160 0.00557 -0.0795 0.1953 1.0000
7.000 1.1532 0.01181 0.00578 -0.0779 0.1912 1.0000
7.250 1.1720 0.01204 0.00600 -0.0762 0.1871 1.0000
7.500 1.1900 0.01230 0.00625 -0.0745 0.1824 1.0000
7.750 1.2082 0.01258 0.00653 -0.0728 0.1780 1.0000
8.000 1.2271 0.01284 0.00679 -0.0713 0.1735 1.0000
8.250 1.2446 0.01316 0.00709 -0.0696 0.1675 1.0000
8.500 1.2623 0.01350 0.00741 -0.0679 0.1617 1.0000
8.750 1.2790 0.01388 0.00777 -0.0662 0.1537 1.0000
9.000 1.2956 0.01429 0.00815 -0.0645 0.1461 1.0000
9.250 1.3097 0.01483 0.00862 -0.0624 0.1346 1.0000
9.500 1.3233 0.01542 0.00915 -0.0604 0.1237 1.0000
9.750 1.3359 0.01607 0.00974 -0.0583 0.1121 1.0000
10.000 1.3462 0.01687 0.01046 -0.0559 0.0979 1.0000
10.250 1.3581 0.01761 0.01116 -0.0538 0.0888 1.0000
10.500 1.3706 0.01834 0.01186 -0.0520 0.0808 1.0000
10.750 1.3829 0.01912 0.01262 -0.0501 0.0732 1.0000
11.000 1.3837 0.02062 0.01396 -0.0470 0.0481 1.0000
11.250 1.3851 0.02216 0.01542 -0.0442 0.0315 1.0000
11.500 1.3961 0.02313 0.01640 -0.0425 0.0284 1.0000
11.750 1.4074 0.02410 0.01740 -0.0410 0.0263 1.0000
12.000 1.4205 0.02498 0.01831 -0.0397 0.0252 1.0000
12.250 1.4320 0.02599 0.01936 -0.0383 0.0238 1.0000
12.500 1.4422 0.02712 0.02051 -0.0369 0.0224 1.0000
12.750 1.4535 0.02818 0.02162 -0.0357 0.0215 1.0000
13.000 1.4649 0.02926 0.02274 -0.0345 0.0206 1.0000
13.250 1.4753 0.03046 0.02397 -0.0334 0.0196 1.0000
13.500 1.4843 0.03178 0.02533 -0.0322 0.0186 1.0000
13.750 1.4929 0.03316 0.02675 -0.0310 0.0178 1.0000
14.000 1.5023 0.03452 0.02816 -0.0301 0.0170 1.0000
14.250 1.5110 0.03596 0.02965 -0.0291 0.0163 1.0000
14.500 1.5182 0.03757 0.03130 -0.0281 0.0155 1.0000
14.750 1.5244 0.03930 0.03307 -0.0272 0.0148 1.0000
15.000 1.5308 0.04106 0.03488 -0.0264 0.0143 1.0000
15.250 1.5371 0.04284 0.03672 -0.0257 0.0136 1.0000
15.500 1.5423 0.04480 0.03873 -0.0250 0.0130 1.0000
15.750 1.5466 0.04689 0.04087 -0.0244 0.0126 1.0000
16.000 1.5494 0.04916 0.04320 -0.0238 0.0121 1.0000
16.250 1.5513 0.05158 0.04568 -0.0233 0.0117 1.0000
16.500 1.5541 0.05397 0.04814 -0.0230 0.0113 1.0000
16.750 1.5558 0.05652 0.05077 -0.0227 0.0110 1.0000
17.000 1.5563 0.05927 0.05359 -0.0226 0.0107 1.0000
17.250 1.5556 0.06219 0.05658 -0.0225 0.0104 1.0000
17.500 1.5539 0.06530 0.05976 -0.0226 0.0100 1.0000
17.750 1.5507 0.06865 0.06319 -0.0227 0.0098 1.0000
18.000 1.5464 0.07221 0.06683 -0.0231 0.0096 1.0000
18.250 1.5397 0.07614 0.07085 -0.0235 0.0093 1.0000
18.500 1.5335 0.08006 0.07486 -0.0241 0.0091 1.0000
18.750 1.5269 0.08410 0.07900 -0.0248 0.0090 1.0000
19.000 1.5183 0.08851 0.08350 -0.0257 0.0089 1.0000
19.250 1.5099 0.09290 0.08799 -0.0267 0.0087 1.0000
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