GOE 692 AIRFOIL (goe692-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 692 AIRFOIL (goe692-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.55 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe692-il-1000000-n5.txt Download as CSV file: xf-goe692-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 692 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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.8026 0.08254 0.07967 -0.0879 1.0000 0.0243
-16.750 -0.8591 0.07203 0.06905 -0.0936 1.0000 0.0243
-16.500 -0.9618 0.05511 0.05190 -0.1038 0.9993 0.0241
-16.250 -1.0248 0.03571 0.03204 -0.1248 0.9943 0.0240
-16.000 -1.0247 0.03106 0.02722 -0.1307 0.9889 0.0241
-15.750 -1.0155 0.02853 0.02455 -0.1333 0.9829 0.0243
-15.500 -1.0061 0.02681 0.02272 -0.1339 0.9736 0.0245
-15.250 -0.9949 0.02546 0.02128 -0.1336 0.9625 0.0246
-15.000 -0.9836 0.02442 0.02012 -0.1325 0.9485 0.0248
-14.750 -0.9699 0.02352 0.01909 -0.1314 0.9329 0.0249
-14.500 -0.9547 0.02270 0.01815 -0.1303 0.9168 0.0251
-14.250 -0.9381 0.02197 0.01728 -0.1293 0.9019 0.0252
-14.000 -0.9200 0.02131 0.01649 -0.1284 0.8891 0.0253
-13.750 -0.9026 0.02055 0.01561 -0.1275 0.8777 0.0254
-13.500 -0.8843 0.01977 0.01473 -0.1267 0.8693 0.0257
-13.250 -0.8644 0.01909 0.01397 -0.1260 0.8616 0.0260
-13.000 -0.8431 0.01849 0.01329 -0.1254 0.8556 0.0262
-12.750 -0.8208 0.01794 0.01266 -0.1249 0.8495 0.0264
-12.500 -0.7980 0.01744 0.01208 -0.1245 0.8434 0.0267
-12.250 -0.7744 0.01697 0.01155 -0.1241 0.8381 0.0270
-12.000 -0.7501 0.01653 0.01105 -0.1237 0.8330 0.0273
-11.750 -0.7256 0.01612 0.01057 -0.1234 0.8281 0.0276
-11.500 -0.7009 0.01573 0.01011 -0.1231 0.8236 0.0279
-11.250 -0.6756 0.01534 0.00966 -0.1229 0.8198 0.0282
-11.000 -0.6501 0.01497 0.00923 -0.1227 0.8156 0.0284
-10.750 -0.6244 0.01462 0.00882 -0.1225 0.8110 0.0287
-10.500 -0.5985 0.01430 0.00843 -0.1222 0.8064 0.0289
-10.250 -0.5722 0.01399 0.00806 -0.1221 0.8026 0.0291
-10.000 -0.5464 0.01358 0.00761 -0.1219 0.7988 0.0296
-9.750 -0.5201 0.01323 0.00723 -0.1218 0.7947 0.0301
-9.500 -0.4935 0.01293 0.00688 -0.1216 0.7905 0.0306
-9.250 -0.4668 0.01265 0.00656 -0.1215 0.7865 0.0310
-9.000 -0.4395 0.01237 0.00625 -0.1215 0.7827 0.0316
-8.750 -0.4122 0.01212 0.00596 -0.1214 0.7781 0.0321
-8.500 -0.3849 0.01189 0.00569 -0.1214 0.7732 0.0327
-8.250 -0.3575 0.01169 0.00543 -0.1213 0.7686 0.0332
-8.000 -0.3300 0.01142 0.00515 -0.1213 0.7646 0.0342
-7.750 -0.3023 0.01118 0.00490 -0.1213 0.7598 0.0353
-7.500 -0.2747 0.01098 0.00466 -0.1213 0.7545 0.0364
-7.250 -0.2470 0.01080 0.00445 -0.1213 0.7494 0.0375
-7.000 -0.2191 0.01059 0.00422 -0.1213 0.7435 0.0391
-6.750 -0.1914 0.01041 0.00402 -0.1213 0.7372 0.0412
-6.500 -0.1635 0.01025 0.00383 -0.1213 0.7316 0.0434
-6.250 -0.1355 0.01007 0.00366 -0.1213 0.7247 0.0466
-6.000 -0.1078 0.00994 0.00350 -0.1212 0.7173 0.0497
-5.750 -0.0796 0.00980 0.00336 -0.1213 0.7100 0.0534
-5.500 -0.0518 0.00969 0.00322 -0.1213 0.7019 0.0567
-5.250 -0.0238 0.00959 0.00311 -0.1213 0.6943 0.0602
-5.000 0.0040 0.00950 0.00299 -0.1212 0.6854 0.0631
-4.750 0.0320 0.00942 0.00288 -0.1212 0.6774 0.0661
-4.500 0.0599 0.00937 0.00279 -0.1212 0.6684 0.0683
-4.250 0.0879 0.00930 0.00269 -0.1212 0.6606 0.0707
-4.000 0.1157 0.00923 0.00260 -0.1212 0.6528 0.0734
-3.750 0.1437 0.00918 0.00252 -0.1212 0.6464 0.0759
-3.500 0.1722 0.00913 0.00245 -0.1213 0.6404 0.0779
-3.250 0.2001 0.00906 0.00237 -0.1213 0.6345 0.0816
-3.000 0.2281 0.00901 0.00231 -0.1213 0.6293 0.0852
-2.750 0.2566 0.00894 0.00224 -0.1214 0.6246 0.0900
-2.500 0.2847 0.00887 0.00219 -0.1214 0.6195 0.0974
-2.250 0.3124 0.00881 0.00216 -0.1214 0.6144 0.1089
-2.000 0.3407 0.00874 0.00213 -0.1215 0.6105 0.1209
-1.750 0.3692 0.00868 0.00210 -0.1217 0.6062 0.1314
-1.500 0.3974 0.00866 0.00209 -0.1217 0.6015 0.1394
-1.250 0.4253 0.00865 0.00208 -0.1217 0.5969 0.1475
-1.000 0.4538 0.00864 0.00207 -0.1218 0.5933 0.1529
-0.750 0.4823 0.00860 0.00207 -0.1220 0.5891 0.1606
-0.500 0.5106 0.00860 0.00207 -0.1220 0.5844 0.1676
-0.250 0.5384 0.00860 0.00208 -0.1220 0.5799 0.1748
0.000 0.5665 0.00860 0.00209 -0.1221 0.5760 0.1823
0.250 0.5950 0.00859 0.00210 -0.1222 0.5716 0.1895
0.500 0.6229 0.00859 0.00212 -0.1223 0.5666 0.2000
0.750 0.6503 0.00861 0.00215 -0.1222 0.5615 0.2122
1.000 0.6781 0.00859 0.00218 -0.1222 0.5550 0.2285
1.250 0.7044 0.00862 0.00223 -0.1220 0.5441 0.2504
1.500 0.7311 0.00863 0.00227 -0.1218 0.5325 0.2773
1.750 0.7570 0.00863 0.00234 -0.1215 0.5210 0.3167
2.000 0.7825 0.00856 0.00242 -0.1212 0.5102 0.3890
2.250 0.8085 0.00843 0.00251 -0.1211 0.5011 0.4796
2.500 0.8335 0.00837 0.00262 -0.1207 0.4914 0.5632
2.750 0.8586 0.00826 0.00274 -0.1202 0.4809 0.6592
3.000 0.8819 0.00819 0.00289 -0.1194 0.4685 0.7570
3.250 0.9038 0.00819 0.00306 -0.1182 0.4557 0.8367
3.500 0.9247 0.00826 0.00323 -0.1167 0.4433 0.8959
3.750 0.9465 0.00838 0.00339 -0.1153 0.4319 0.9454
4.000 0.9798 0.00859 0.00356 -0.1166 0.4206 0.9863
4.250 1.0109 0.00883 0.00373 -0.1176 0.4082 1.0000
4.500 1.0332 0.00902 0.00387 -0.1165 0.3970 1.0000
4.750 1.0549 0.00925 0.00404 -0.1154 0.3863 1.0000
5.000 1.0754 0.00951 0.00423 -0.1141 0.3733 1.0000
5.250 1.0954 0.00977 0.00443 -0.1127 0.3597 1.0000
5.500 1.1150 0.01002 0.00462 -0.1112 0.3487 1.0000
5.750 1.1338 0.01031 0.00485 -0.1095 0.3370 1.0000
6.000 1.1524 0.01064 0.00511 -0.1079 0.3239 1.0000
6.250 1.1712 0.01097 0.00539 -0.1064 0.3103 1.0000
6.500 1.1897 0.01135 0.00570 -0.1048 0.2965 1.0000
6.750 1.2076 0.01175 0.00604 -0.1032 0.2828 1.0000
7.000 1.2252 0.01218 0.00640 -0.1016 0.2697 1.0000
7.250 1.2425 0.01264 0.00680 -0.1000 0.2573 1.0000
7.500 1.2601 0.01310 0.00720 -0.0985 0.2459 1.0000
7.750 1.2782 0.01354 0.00762 -0.0971 0.2365 1.0000
8.250 1.3136 0.01451 0.00852 -0.0943 0.2192 1.0000
8.750 1.3483 0.01556 0.00952 -0.0916 0.2043 1.0000
9.000 1.3639 0.01620 0.01012 -0.0900 0.1961 1.0000
9.250 1.3811 0.01676 0.01067 -0.0888 0.1887 1.0000
9.500 1.3955 0.01749 0.01137 -0.0872 0.1802 1.0000
9.750 1.4117 0.01814 0.01200 -0.0859 0.1727 1.0000
10.000 1.4252 0.01897 0.01279 -0.0843 0.1637 1.0000
10.250 1.4374 0.01989 0.01367 -0.0826 0.1536 1.0000
10.500 1.4509 0.02076 0.01452 -0.0811 0.1459 1.0000
10.750 1.4624 0.02177 0.01549 -0.0795 0.1385 1.0000
11.000 1.4766 0.02264 0.01636 -0.0783 0.1338 1.0000
11.250 1.4895 0.02360 0.01732 -0.0769 0.1293 1.0000
11.500 1.5014 0.02464 0.01837 -0.0755 0.1249 1.0000
11.750 1.5155 0.02555 0.01930 -0.0744 0.1221 1.0000
12.000 1.5279 0.02659 0.02036 -0.0732 0.1192 1.0000
12.250 1.5393 0.02774 0.02151 -0.0719 0.1158 1.0000
12.500 1.5501 0.02895 0.02273 -0.0706 0.1126 1.0000
12.750 1.5641 0.02993 0.02376 -0.0697 0.1115 1.0000
13.000 1.5764 0.03107 0.02493 -0.0686 0.1096 1.0000
13.250 1.5876 0.03230 0.02619 -0.0676 0.1069 1.0000
13.500 1.5974 0.03368 0.02759 -0.0664 0.1045 1.0000
13.750 1.6061 0.03517 0.02910 -0.0653 0.1015 1.0000
14.000 1.6173 0.03648 0.03045 -0.0644 0.0997 1.0000
14.250 1.6282 0.03782 0.03184 -0.0635 0.0973 1.0000
14.500 1.6363 0.03943 0.03347 -0.0625 0.0935 1.0000
14.750 1.6420 0.04129 0.03533 -0.0614 0.0892 1.0000
15.000 1.6493 0.04304 0.03709 -0.0605 0.0833 1.0000
15.250 1.6481 0.04559 0.03959 -0.0592 0.0725 1.0000
15.500 1.6401 0.04885 0.04277 -0.0577 0.0601 1.0000
15.750 1.6352 0.05191 0.04582 -0.0565 0.0524 1.0000
16.000 1.6327 0.05481 0.04874 -0.0555 0.0470 1.0000
16.250 1.6300 0.05776 0.05170 -0.0546 0.0419 1.0000
16.500 1.6268 0.06080 0.05475 -0.0538 0.0366 1.0000
16.750 1.6214 0.06416 0.05812 -0.0531 0.0309 1.0000
17.000 1.6148 0.06771 0.06169 -0.0525 0.0255 1.0000
17.250 1.6092 0.07121 0.06521 -0.0520 0.0215 1.0000
17.500 1.6061 0.07444 0.06849 -0.0517 0.0192 1.0000
17.750 1.6033 0.07773 0.07183 -0.0515 0.0177 1.0000
18.000 1.6006 0.08104 0.07520 -0.0514 0.0165 1.0000
18.250 1.5984 0.08432 0.07853 -0.0513 0.0156 1.0000
18.500 1.5964 0.08762 0.08190 -0.0514 0.0151 1.0000
18.750 1.5936 0.09102 0.08538 -0.0516 0.0145 1.0000
19.000 1.5907 0.09449 0.08891 -0.0519 0.0140 1.0000
19.250 1.5861 0.09823 0.09272 -0.0523 0.0135 1.0000
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