GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 630 AIRFOIL (goe630-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.97 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe630-il-1000000.txt Download as CSV file: xf-goe630-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 630 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
------ -------- --------- --------- -------- -------- --------
-11.250 0.0993 0.09089 0.08841 -0.1073 0.8041 0.0212
-11.000 0.0759 0.09665 0.09434 -0.1172 0.8669 0.0211
-10.750 0.0748 0.09314 0.09069 -0.1200 0.8430 0.0213
-10.500 0.0855 0.09038 0.08786 -0.1198 0.8273 0.0215
-10.250 0.0943 0.08821 0.08562 -0.1203 0.8136 0.0216
-10.000 0.1054 0.08661 0.08396 -0.1204 0.8016 0.0218
-9.750 0.1139 0.08467 0.08196 -0.1208 0.7908 0.0221
-9.500 0.1223 0.08266 0.07992 -0.1213 0.7809 0.0223
-9.250 0.1304 0.08072 0.07793 -0.1218 0.7720 0.0230
-9.000 0.1251 0.07734 0.07454 -0.1243 0.7640 0.0248
-8.750 0.1403 0.06196 0.05924 -0.1143 0.7359 0.0250
-8.500 0.1499 0.05957 0.05683 -0.1142 0.7300 0.0252
-8.250 0.1365 0.06936 0.06649 -0.1258 0.7433 0.0252
-8.000 0.1465 0.06767 0.06479 -0.1256 0.7371 0.0254
-7.750 0.1544 0.06598 0.06309 -0.1255 0.7309 0.0255
-7.500 0.1601 0.06435 0.06144 -0.1251 0.7247 0.0258
-7.250 0.1617 0.06253 0.05963 -0.1247 0.7190 0.0259
-7.000 0.1661 0.06087 0.05796 -0.1248 0.7131 0.0264
-6.750 0.1735 0.05881 0.05588 -0.1258 0.7076 0.0271
-6.250 0.1830 0.04839 0.04539 -0.1374 0.6975 0.0292
-6.000 0.1979 0.04663 0.04359 -0.1379 0.6924 0.0294
-5.750 0.2154 0.04512 0.04206 -0.1386 0.6875 0.0297
-5.500 0.2338 0.04318 0.04009 -0.1399 0.6819 0.0300
-5.250 0.2529 0.04127 0.03811 -0.1412 0.6765 0.0305
-5.000 0.2804 0.03380 0.03037 -0.1482 0.6721 0.0335
-4.750 0.2943 0.02907 0.02548 -0.1498 0.6673 0.0341
-4.500 0.3161 0.02786 0.02420 -0.1499 0.6615 0.0344
-4.250 0.3385 0.02662 0.02287 -0.1500 0.6557 0.0348
-4.000 0.3442 0.01534 0.01045 -0.1494 0.6521 0.0319
-3.750 0.3661 0.01349 0.00823 -0.1485 0.6460 0.0321
-3.500 0.3900 0.01247 0.00696 -0.1477 0.6397 0.0324
-3.250 0.4158 0.01182 0.00616 -0.1473 0.6333 0.0328
-3.000 0.4413 0.01139 0.00558 -0.1467 0.6261 0.0332
-2.750 0.4679 0.01112 0.00521 -0.1463 0.6188 0.0335
-2.500 0.4922 0.01037 0.00434 -0.1456 0.6103 0.0344
-2.250 0.5183 0.01015 0.00408 -0.1452 0.6015 0.0350
-1.750 0.5700 0.00982 0.00364 -0.1442 0.5827 0.0362
-1.500 0.5954 0.00967 0.00341 -0.1436 0.5731 0.0368
-1.250 0.6209 0.00955 0.00323 -0.1430 0.5625 0.0376
-1.000 0.6465 0.00946 0.00307 -0.1425 0.5520 0.0383
-0.750 0.6716 0.00946 0.00300 -0.1418 0.5407 0.0388
-0.500 0.6957 0.00921 0.00270 -0.1410 0.5293 0.0402
-0.250 0.7210 0.00921 0.00267 -0.1405 0.5184 0.0416
0.000 0.7458 0.00924 0.00264 -0.1398 0.5080 0.0430
0.250 0.7707 0.00925 0.00261 -0.1392 0.4975 0.0443
0.500 0.7955 0.00922 0.00252 -0.1385 0.4881 0.0459
1.000 0.8448 0.00927 0.00250 -0.1372 0.4692 0.0506
1.250 0.8689 0.00933 0.00252 -0.1364 0.4602 0.0533
1.500 0.8934 0.00935 0.00252 -0.1357 0.4514 0.0581
1.750 0.9175 0.00943 0.00256 -0.1349 0.4433 0.0627
2.000 0.9419 0.00946 0.00260 -0.1343 0.4359 0.0713
2.250 0.9648 0.00949 0.00270 -0.1333 0.4286 0.1164
2.500 0.9884 0.00939 0.00283 -0.1326 0.4226 0.2224
2.750 1.0093 0.00925 0.00302 -0.1314 0.4161 0.4012
3.000 1.0779 0.00846 0.00340 -0.1410 0.4083 1.0000
3.250 1.1014 0.00862 0.00350 -0.1401 0.4024 1.0000
3.500 1.1238 0.00882 0.00363 -0.1391 0.3964 1.0000
3.750 1.1482 0.00894 0.00373 -0.1385 0.3916 1.0000
4.000 1.1711 0.00911 0.00386 -0.1375 0.3863 1.0000
4.250 1.1925 0.00933 0.00402 -0.1364 0.3806 1.0000
4.500 1.2166 0.00945 0.00414 -0.1357 0.3770 1.0000
4.750 1.2394 0.00961 0.00428 -0.1348 0.3727 1.0000
5.000 1.2608 0.00981 0.00444 -0.1336 0.3683 1.0000
5.250 1.2817 0.01002 0.00463 -0.1324 0.3640 1.0000
5.500 1.3037 0.01016 0.00477 -0.1313 0.3610 1.0000
5.750 1.3240 0.01032 0.00493 -0.1299 0.3574 1.0000
6.000 1.3432 0.01053 0.00512 -0.1284 0.3537 1.0000
6.250 1.3606 0.01080 0.00536 -0.1265 0.3494 1.0000
6.500 1.3821 0.01096 0.00554 -0.1254 0.3468 1.0000
6.750 1.4035 0.01113 0.00573 -0.1244 0.3440 1.0000
7.000 1.4236 0.01135 0.00595 -0.1231 0.3409 1.0000
7.250 1.4430 0.01160 0.00620 -0.1218 0.3379 1.0000
7.500 1.4609 0.01193 0.00651 -0.1202 0.3345 1.0000
7.750 1.4814 0.01216 0.00676 -0.1191 0.3315 1.0000
8.000 1.5031 0.01236 0.00698 -0.1183 0.3284 1.0000
8.250 1.5228 0.01263 0.00726 -0.1171 0.3246 1.0000
8.500 1.5404 0.01299 0.00761 -0.1157 0.3204 1.0000
8.750 1.5589 0.01333 0.00796 -0.1144 0.3162 1.0000
9.000 1.5801 0.01357 0.00824 -0.1136 0.3123 1.0000
9.250 1.5988 0.01392 0.00859 -0.1125 0.3083 1.0000
9.500 1.6143 0.01442 0.00907 -0.1109 0.3032 1.0000
9.750 1.6346 0.01472 0.00942 -0.1100 0.2993 1.0000
10.000 1.6535 0.01509 0.00982 -0.1090 0.2953 1.0000
10.250 1.6704 0.01557 0.01031 -0.1078 0.2911 1.0000
10.500 1.6856 0.01615 0.01088 -0.1064 0.2861 1.0000
10.750 1.7050 0.01653 0.01131 -0.1055 0.2818 1.0000
11.000 1.7206 0.01711 0.01190 -0.1043 0.2763 1.0000
11.250 1.7352 0.01777 0.01257 -0.1029 0.2700 1.0000
11.500 1.7497 0.01845 0.01325 -0.1017 0.2615 1.0000
11.750 1.7619 0.01930 0.01408 -0.1002 0.2512 1.0000
12.000 1.7710 0.02035 0.01510 -0.0984 0.2390 1.0000
12.250 1.7758 0.02173 0.01641 -0.0963 0.2213 1.0000
12.500 1.7692 0.02395 0.01846 -0.0932 0.1940 1.0000
12.750 1.7530 0.02700 0.02131 -0.0896 0.1631 1.0000
13.000 1.7349 0.03037 0.02452 -0.0862 0.1352 1.0000
13.250 1.7124 0.03436 0.02835 -0.0830 0.1046 1.0000
13.500 1.6896 0.03865 0.03252 -0.0803 0.0805 1.0000
13.750 1.6729 0.04261 0.03642 -0.0782 0.0629 1.0000
14.000 1.6471 0.04772 0.04144 -0.0763 0.0409 1.0000
14.250 1.6275 0.05245 0.04615 -0.0749 0.0280 1.0000
14.500 1.6177 0.05628 0.05002 -0.0741 0.0234 1.0000
14.750 1.6107 0.05992 0.05373 -0.0735 0.0210 1.0000
15.000 1.6067 0.06327 0.05716 -0.0730 0.0198 1.0000
15.250 1.5995 0.06705 0.06101 -0.0727 0.0186 1.0000
15.500 1.5912 0.07107 0.06510 -0.0724 0.0176 1.0000
15.750 1.5877 0.07451 0.06863 -0.0723 0.0172 1.0000
16.000 1.5816 0.07835 0.07255 -0.0722 0.0165 1.0000
16.250 1.5751 0.08223 0.07652 -0.0722 0.0161 1.0000
16.500 1.5667 0.08645 0.08081 -0.0723 0.0157 1.0000
16.750 1.5569 0.09090 0.08535 -0.0726 0.0152 1.0000
17.000 1.5464 0.09547 0.09001 -0.0729 0.0148 1.0000
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