GOE 288 AIRFOIL (goe288-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 288 AIRFOIL (goe288-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.1 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe288-il-1000000.txt Download as CSV file: xf-goe288-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 288 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7330 0.08507 0.08242 -0.0700 1.0000 0.0278
-16.000 -0.7622 0.07648 0.07368 -0.0758 1.0000 0.0279
-15.750 -0.7815 0.06987 0.06695 -0.0804 1.0000 0.0279
-15.500 -0.7974 0.06416 0.06114 -0.0844 1.0000 0.0280
-15.250 -0.8115 0.05907 0.05595 -0.0880 1.0000 0.0280
-15.000 -0.8232 0.05444 0.05123 -0.0912 1.0000 0.0281
-14.750 -0.8336 0.05017 0.04688 -0.0940 1.0000 0.0282
-14.500 -0.8438 0.04626 0.04289 -0.0964 1.0000 0.0282
-14.250 -0.8578 0.04278 0.03935 -0.0974 1.0000 0.0283
-14.000 -0.8673 0.03923 0.03573 -0.0994 0.9984 0.0284
-13.750 -0.8508 0.03508 0.03147 -0.1069 0.9937 0.0285
-13.500 -0.8286 0.03079 0.02705 -0.1160 0.9868 0.0287
-13.250 -0.8000 0.02785 0.02396 -0.1230 0.9812 0.0290
-13.000 -0.7783 0.02622 0.02223 -0.1253 0.9721 0.0292
-12.750 -0.7553 0.02489 0.02080 -0.1269 0.9635 0.0294
-12.500 -0.7340 0.02374 0.01955 -0.1276 0.9530 0.0296
-12.250 -0.7131 0.02276 0.01847 -0.1278 0.9409 0.0298
-12.000 -0.6912 0.02190 0.01750 -0.1278 0.9287 0.0299
-11.750 -0.6685 0.02114 0.01663 -0.1278 0.9158 0.0300
-11.500 -0.6451 0.02049 0.01586 -0.1277 0.9020 0.0302
-11.250 -0.6253 0.01909 0.01435 -0.1276 0.8877 0.0305
-11.000 -0.6025 0.01815 0.01332 -0.1276 0.8737 0.0308
-10.750 -0.5781 0.01745 0.01253 -0.1276 0.8589 0.0311
-10.500 -0.5528 0.01687 0.01186 -0.1276 0.8427 0.0314
-10.250 -0.5270 0.01636 0.01125 -0.1276 0.8251 0.0317
-10.000 -0.5008 0.01589 0.01068 -0.1276 0.8063 0.0320
-9.750 -0.4743 0.01546 0.01014 -0.1277 0.7861 0.0324
-9.500 -0.4476 0.01507 0.00963 -0.1277 0.7647 0.0327
-9.250 -0.4206 0.01472 0.00915 -0.1277 0.7430 0.0331
-9.000 -0.3932 0.01441 0.00872 -0.1278 0.7224 0.0335
-8.750 -0.3655 0.01412 0.00831 -0.1279 0.7041 0.0339
-8.500 -0.3376 0.01383 0.00791 -0.1280 0.6882 0.0342
-8.250 -0.3095 0.01358 0.00756 -0.1281 0.6739 0.0344
-8.000 -0.2818 0.01303 0.00691 -0.1284 0.6615 0.0350
-7.750 -0.2535 0.01263 0.00643 -0.1286 0.6510 0.0356
-7.500 -0.2248 0.01234 0.00608 -0.1288 0.6411 0.0362
-7.250 -0.1958 0.01209 0.00577 -0.1291 0.6328 0.0368
-7.000 -0.1667 0.01187 0.00549 -0.1293 0.6242 0.0374
-6.750 -0.1375 0.01167 0.00522 -0.1295 0.6161 0.0381
-6.500 -0.1081 0.01149 0.00497 -0.1298 0.6084 0.0388
-6.250 -0.0790 0.01127 0.00467 -0.1300 0.6004 0.0396
-6.000 -0.0494 0.01100 0.00438 -0.1303 0.5948 0.0410
-5.750 -0.0198 0.01081 0.00417 -0.1306 0.5893 0.0425
-5.500 0.0097 0.01069 0.00399 -0.1308 0.5837 0.0439
-5.250 0.0393 0.01047 0.00375 -0.1311 0.5783 0.0467
-5.000 0.0692 0.01027 0.00354 -0.1314 0.5730 0.0506
-4.750 0.0988 0.01002 0.00331 -0.1317 0.5678 0.0616
-4.500 0.1281 0.00972 0.00313 -0.1321 0.5626 0.0912
-4.250 0.1581 0.00957 0.00303 -0.1325 0.5587 0.1065
-4.000 0.1880 0.00945 0.00294 -0.1328 0.5539 0.1168
-3.750 0.2177 0.00938 0.00285 -0.1330 0.5489 0.1252
-3.500 0.2473 0.00935 0.00279 -0.1332 0.5439 0.1333
-3.250 0.2772 0.00924 0.00272 -0.1336 0.5407 0.1437
-3.000 0.3073 0.00914 0.00265 -0.1339 0.5374 0.1541
-2.750 0.3371 0.00906 0.00258 -0.1342 0.5336 0.1666
-2.500 0.3668 0.00895 0.00252 -0.1345 0.5297 0.1850
-2.250 0.3962 0.00884 0.00248 -0.1348 0.5251 0.2164
-2.000 0.4261 0.00871 0.00246 -0.1351 0.5219 0.2504
-1.750 0.4560 0.00864 0.00246 -0.1355 0.5181 0.2750
-1.500 0.4857 0.00862 0.00247 -0.1357 0.5141 0.2916
-1.250 0.5152 0.00865 0.00248 -0.1359 0.5100 0.3048
-1.000 0.5446 0.00870 0.00253 -0.1361 0.5057 0.3172
-0.750 0.5746 0.00869 0.00254 -0.1364 0.5027 0.3264
-0.500 0.6043 0.00870 0.00256 -0.1366 0.4986 0.3337
-0.250 0.6338 0.00876 0.00258 -0.1368 0.4940 0.3392
0.000 0.6628 0.00881 0.00262 -0.1369 0.4886 0.3467
0.250 0.6926 0.00883 0.00265 -0.1372 0.4846 0.3532
0.500 0.7221 0.00888 0.00267 -0.1374 0.4796 0.3575
0.750 0.7512 0.00891 0.00270 -0.1375 0.4741 0.3638
1.000 0.7802 0.00898 0.00276 -0.1377 0.4688 0.3695
1.250 0.8097 0.00902 0.00279 -0.1379 0.4631 0.3748
1.500 0.8385 0.00909 0.00284 -0.1380 0.4561 0.3807
1.750 0.8673 0.00915 0.00291 -0.1381 0.4492 0.3886
2.000 0.8960 0.00926 0.00298 -0.1382 0.4400 0.3956
2.250 0.9243 0.00934 0.00305 -0.1383 0.4300 0.4027
2.500 0.9521 0.00948 0.00314 -0.1383 0.4169 0.4083
2.750 0.9794 0.00966 0.00324 -0.1382 0.4015 0.4131
3.000 1.0064 0.00986 0.00337 -0.1381 0.3852 0.4181
3.250 1.0330 0.01008 0.00353 -0.1379 0.3697 0.4245
3.500 1.0598 0.01029 0.00369 -0.1377 0.3572 0.4311
3.750 1.0863 0.01051 0.00386 -0.1375 0.3471 0.4377
4.000 1.1129 0.01070 0.00404 -0.1373 0.3388 0.4457
4.250 1.1395 0.01090 0.00422 -0.1372 0.3319 0.4536
4.500 1.1665 0.01104 0.00439 -0.1370 0.3265 0.4648
4.750 1.1926 0.01125 0.00459 -0.1368 0.3209 0.4784
5.000 1.2189 0.01142 0.00480 -0.1366 0.3161 0.4972
5.250 1.2459 0.01151 0.00497 -0.1365 0.3131 0.5257
5.500 1.2724 0.01161 0.00518 -0.1364 0.3097 0.5734
5.750 1.2983 0.01161 0.00545 -0.1363 0.3063 0.6883
6.000 1.3170 0.01133 0.00571 -0.1343 0.3027 1.0000
6.250 1.3423 0.01157 0.00593 -0.1340 0.2997 1.0000
6.500 1.3688 0.01173 0.00611 -0.1338 0.2980 1.0000
6.750 1.3947 0.01191 0.00630 -0.1335 0.2959 1.0000
7.000 1.4199 0.01213 0.00651 -0.1331 0.2935 1.0000
7.250 1.4443 0.01238 0.00676 -0.1326 0.2910 1.0000
7.500 1.4676 0.01267 0.00703 -0.1319 0.2881 1.0000
7.750 1.4888 0.01305 0.00738 -0.1309 0.2843 1.0000
8.000 1.5133 0.01324 0.00760 -0.1304 0.2825 1.0000
8.250 1.5375 0.01342 0.00781 -0.1299 0.2807 1.0000
8.500 1.5606 0.01365 0.00806 -0.1292 0.2789 1.0000
8.750 1.5819 0.01390 0.00833 -0.1281 0.2770 1.0000
9.000 1.6016 0.01420 0.00864 -0.1268 0.2750 1.0000
9.250 1.6203 0.01455 0.00900 -0.1253 0.2727 1.0000
9.500 1.6376 0.01499 0.00943 -0.1237 0.2701 1.0000
9.750 1.6539 0.01549 0.00994 -0.1220 0.2674 1.0000
10.000 1.6761 0.01573 0.01023 -0.1213 0.2661 1.0000
10.250 1.6978 0.01600 0.01054 -0.1205 0.2639 1.0000
10.500 1.7181 0.01634 0.01091 -0.1195 0.2615 1.0000
10.750 1.7368 0.01677 0.01136 -0.1184 0.2590 1.0000
11.000 1.7534 0.01731 0.01190 -0.1170 0.2560 1.0000
11.250 1.7671 0.01803 0.01261 -0.1152 0.2525 1.0000
11.500 1.7859 0.01849 0.01313 -0.1142 0.2509 1.0000
11.750 1.8054 0.01893 0.01362 -0.1134 0.2493 1.0000
12.000 1.8242 0.01941 0.01415 -0.1125 0.2469 1.0000
12.250 1.8410 0.02003 0.01479 -0.1114 0.2438 1.0000
12.500 1.8553 0.02082 0.01559 -0.1101 0.2405 1.0000
12.750 1.8658 0.02186 0.01664 -0.1084 0.2368 1.0000
13.000 1.8844 0.02242 0.01727 -0.1077 0.2345 1.0000
13.250 1.9007 0.02315 0.01804 -0.1068 0.2312 1.0000
13.500 1.9133 0.02415 0.01906 -0.1056 0.2268 1.0000
13.750 1.9210 0.02554 0.02045 -0.1040 0.2218 1.0000
14.000 1.9363 0.02640 0.02137 -0.1032 0.2181 1.0000
14.250 1.9460 0.02771 0.02270 -0.1020 0.2127 1.0000
14.500 1.9511 0.02944 0.02444 -0.1006 0.2073 1.0000
14.750 1.9606 0.03085 0.02589 -0.0996 0.2015 1.0000
15.000 1.9603 0.03314 0.02816 -0.0980 0.1937 1.0000
15.250 1.9604 0.03547 0.03050 -0.0967 0.1836 1.0000
15.500 1.9522 0.03867 0.03367 -0.0952 0.1709 1.0000
15.750 1.9346 0.04289 0.03785 -0.0935 0.1557 1.0000
16.000 1.9108 0.04792 0.04282 -0.0919 0.1387 1.0000
16.500 1.8479 0.06012 0.05494 -0.0893 0.1062 1.0000
16.750 1.8237 0.06569 0.06052 -0.0886 0.0961 1.0000
17.000 1.8038 0.07093 0.06578 -0.0882 0.0892 1.0000
17.250 1.7894 0.07562 0.07053 -0.0880 0.0844 1.0000
17.500 1.7734 0.08060 0.07556 -0.0879 0.0804 1.0000
17.750 1.7609 0.08521 0.08023 -0.0880 0.0772 1.0000
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