GOE 692 AIRFOIL (goe692-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 692 AIRFOIL (goe692-il) Reynolds number: 500,000 Max Cl/Cd: 99.21 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe692-il-500000-n5.txt Download as CSV file: xf-goe692-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6981 0.08544 0.08204 -0.0848 1.0000 0.0287
-15.750 -0.7495 0.07516 0.07161 -0.0902 1.0000 0.0287
-15.500 -0.7954 0.06637 0.06269 -0.0944 1.0000 0.0287
-15.250 -0.8335 0.05681 0.05298 -0.1013 0.9983 0.0287
-15.000 -0.8533 0.04664 0.04256 -0.1124 0.9943 0.0288
-14.750 -0.8581 0.03885 0.03451 -0.1229 0.9884 0.0289
-14.500 -0.8517 0.03429 0.02973 -0.1296 0.9824 0.0290
-14.250 -0.8459 0.03149 0.02677 -0.1322 0.9726 0.0292
-14.000 -0.8390 0.02935 0.02452 -0.1331 0.9614 0.0294
-13.750 -0.8300 0.02776 0.02282 -0.1327 0.9488 0.0296
-13.500 -0.8174 0.02647 0.02143 -0.1322 0.9366 0.0298
-13.250 -0.8018 0.02536 0.02020 -0.1317 0.9253 0.0301
-13.000 -0.7858 0.02441 0.01913 -0.1309 0.9143 0.0304
-12.750 -0.7681 0.02356 0.01817 -0.1302 0.9052 0.0307
-12.500 -0.7494 0.02278 0.01729 -0.1295 0.8963 0.0310
-12.250 -0.7299 0.02206 0.01645 -0.1289 0.8883 0.0314
-12.000 -0.7096 0.02136 0.01564 -0.1282 0.8807 0.0318
-11.750 -0.6886 0.02070 0.01486 -0.1276 0.8745 0.0321
-11.500 -0.6671 0.02007 0.01413 -0.1271 0.8679 0.0325
-11.250 -0.6448 0.01948 0.01342 -0.1265 0.8616 0.0328
-11.000 -0.6219 0.01894 0.01276 -0.1261 0.8560 0.0331
-10.750 -0.5993 0.01834 0.01209 -0.1256 0.8501 0.0335
-10.500 -0.5763 0.01776 0.01145 -0.1251 0.8448 0.0340
-10.250 -0.5523 0.01727 0.01088 -0.1248 0.8402 0.0345
-10.000 -0.5278 0.01680 0.01036 -0.1245 0.8354 0.0350
-9.750 -0.5029 0.01638 0.00987 -0.1242 0.8303 0.0356
-9.500 -0.4777 0.01599 0.00940 -0.1239 0.8254 0.0362
-9.250 -0.4521 0.01562 0.00894 -0.1236 0.8208 0.0369
-9.000 -0.4261 0.01526 0.00853 -0.1234 0.8160 0.0376
-8.750 -0.4005 0.01487 0.00809 -0.1232 0.8113 0.0385
-8.500 -0.3744 0.01452 0.00769 -0.1230 0.8069 0.0395
-8.250 -0.3479 0.01420 0.00733 -0.1229 0.8028 0.0405
-8.000 -0.3213 0.01390 0.00699 -0.1227 0.7980 0.0417
-7.750 -0.2945 0.01363 0.00665 -0.1226 0.7928 0.0430
-7.500 -0.2678 0.01334 0.00633 -0.1225 0.7880 0.0446
-7.250 -0.2407 0.01308 0.00605 -0.1224 0.7834 0.0466
-7.000 -0.2134 0.01285 0.00578 -0.1223 0.7783 0.0487
-6.750 -0.1862 0.01261 0.00553 -0.1222 0.7733 0.0514
-6.500 -0.1586 0.01244 0.00530 -0.1222 0.7684 0.0544
-6.250 -0.1312 0.01223 0.00511 -0.1221 0.7628 0.0577
-6.000 -0.1035 0.01207 0.00491 -0.1221 0.7568 0.0609
-5.750 -0.0760 0.01190 0.00471 -0.1220 0.7515 0.0640
-5.500 -0.0482 0.01175 0.00454 -0.1220 0.7457 0.0671
-5.250 -0.0205 0.01161 0.00436 -0.1219 0.7391 0.0698
-5.000 0.0069 0.01145 0.00418 -0.1219 0.7331 0.0729
-4.750 0.0348 0.01132 0.00402 -0.1218 0.7263 0.0759
-4.500 0.0624 0.01120 0.00386 -0.1218 0.7194 0.0787
-4.250 0.0899 0.01105 0.00370 -0.1217 0.7125 0.0823
-4.000 0.1175 0.01094 0.00357 -0.1216 0.7049 0.0858
-3.750 0.1449 0.01085 0.00343 -0.1215 0.6976 0.0892
-3.500 0.1724 0.01073 0.00331 -0.1214 0.6897 0.0940
-3.250 0.1996 0.01065 0.00321 -0.1213 0.6824 0.1006
-3.000 0.2272 0.01055 0.00313 -0.1212 0.6751 0.1098
-2.750 0.2545 0.01047 0.00306 -0.1211 0.6683 0.1198
-2.500 0.2822 0.01041 0.00300 -0.1211 0.6623 0.1288
-2.250 0.3100 0.01037 0.00295 -0.1211 0.6560 0.1381
-2.000 0.3374 0.01033 0.00292 -0.1210 0.6501 0.1475
-1.750 0.3652 0.01031 0.00288 -0.1209 0.6448 0.1549
-1.500 0.3930 0.01027 0.00286 -0.1209 0.6393 0.1631
-1.250 0.4206 0.01027 0.00283 -0.1209 0.6338 0.1705
-1.000 0.4482 0.01025 0.00282 -0.1208 0.6291 0.1795
-0.500 0.5037 0.01022 0.00281 -0.1208 0.6189 0.1960
0.000 0.5588 0.01021 0.00283 -0.1207 0.6098 0.2178
0.250 0.5863 0.01018 0.00285 -0.1207 0.6049 0.2334
0.500 0.6135 0.01017 0.00288 -0.1206 0.5998 0.2521
1.000 0.6677 0.01003 0.00297 -0.1205 0.5907 0.3276
1.250 0.6940 0.00985 0.00303 -0.1204 0.5855 0.4064
1.500 0.7193 0.00962 0.00311 -0.1201 0.5804 0.5214
1.750 0.7441 0.00938 0.00321 -0.1196 0.5756 0.6379
2.000 0.7674 0.00914 0.00333 -0.1186 0.5688 0.7527
2.250 0.7875 0.00904 0.00347 -0.1167 0.5602 0.8515
2.500 0.8109 0.00905 0.00359 -0.1154 0.5493 0.9197
2.750 0.8425 0.00918 0.00370 -0.1162 0.5386 0.9572
3.000 0.8759 0.00933 0.00379 -0.1175 0.5292 0.9797
3.250 0.9154 0.00948 0.00390 -0.1202 0.5205 0.9986
3.500 0.9381 0.00963 0.00400 -0.1192 0.5105 1.0000
3.750 0.9603 0.00977 0.00410 -0.1181 0.5008 1.0000
4.000 0.9815 0.00995 0.00422 -0.1169 0.4910 1.0000
4.250 1.0038 0.01012 0.00435 -0.1158 0.4809 1.0000
4.500 1.0248 0.01033 0.00450 -0.1145 0.4701 1.0000
4.750 1.0442 0.01059 0.00468 -0.1130 0.4573 1.0000
5.000 1.0638 0.01084 0.00487 -0.1115 0.4440 1.0000
5.250 1.0828 0.01110 0.00507 -0.1099 0.4321 1.0000
5.500 1.1003 0.01138 0.00530 -0.1079 0.4210 1.0000
5.750 1.1169 0.01172 0.00557 -0.1059 0.4084 1.0000
6.000 1.1360 0.01202 0.00584 -0.1044 0.3967 1.0000
6.250 1.1544 0.01235 0.00613 -0.1028 0.3866 1.0000
6.500 1.1725 0.01272 0.00645 -0.1012 0.3755 1.0000
6.750 1.1913 0.01308 0.00678 -0.0998 0.3643 1.0000
7.000 1.2088 0.01350 0.00716 -0.0982 0.3527 1.0000
7.250 1.2252 0.01398 0.00759 -0.0964 0.3402 1.0000
7.500 1.2421 0.01447 0.00803 -0.0949 0.3269 1.0000
7.750 1.2581 0.01501 0.00852 -0.0932 0.3136 1.0000
8.000 1.2732 0.01561 0.00907 -0.0914 0.3001 1.0000
8.250 1.2877 0.01627 0.00968 -0.0896 0.2868 1.0000
8.500 1.3014 0.01699 0.01034 -0.0878 0.2741 1.0000
8.750 1.3157 0.01771 0.01102 -0.0861 0.2619 1.0000
9.000 1.3299 0.01845 0.01174 -0.0845 0.2513 1.0000
9.250 1.3430 0.01929 0.01253 -0.0828 0.2414 1.0000
9.500 1.3574 0.02007 0.01330 -0.0813 0.2321 1.0000
9.750 1.3704 0.02095 0.01417 -0.0798 0.2240 1.0000
10.000 1.3841 0.02181 0.01502 -0.0783 0.2157 1.0000
10.250 1.3965 0.02278 0.01598 -0.0768 0.2082 1.0000
10.500 1.4093 0.02374 0.01694 -0.0754 0.2001 1.0000
10.750 1.4208 0.02480 0.01799 -0.0739 0.1929 1.0000
11.000 1.4331 0.02583 0.01903 -0.0726 0.1856 1.0000
11.250 1.4433 0.02703 0.02022 -0.0711 0.1783 1.0000
11.500 1.4540 0.02821 0.02140 -0.0697 0.1704 1.0000
11.750 1.4630 0.02955 0.02273 -0.0683 0.1631 1.0000
12.000 1.4722 0.03089 0.02406 -0.0669 0.1557 1.0000
12.250 1.4806 0.03234 0.02551 -0.0655 0.1500 1.0000
12.500 1.4901 0.03373 0.02692 -0.0643 0.1448 1.0000
12.750 1.4973 0.03533 0.02853 -0.0630 0.1398 1.0000
13.000 1.5060 0.03685 0.03008 -0.0619 0.1358 1.0000
13.250 1.5147 0.03839 0.03165 -0.0608 0.1319 1.0000
13.500 1.5217 0.04011 0.03340 -0.0598 0.1284 1.0000
13.750 1.5276 0.04198 0.03529 -0.0587 0.1252 1.0000
14.000 1.5374 0.04351 0.03688 -0.0579 0.1226 1.0000
14.250 1.5453 0.04526 0.03867 -0.0571 0.1198 1.0000
14.500 1.5516 0.04715 0.04061 -0.0562 0.1169 1.0000
14.750 1.5557 0.04930 0.04278 -0.0553 0.1138 1.0000
15.000 1.5626 0.05122 0.04476 -0.0547 0.1113 1.0000
15.250 1.5709 0.05301 0.04662 -0.0541 0.1089 1.0000
15.500 1.5766 0.05509 0.04874 -0.0535 0.1061 1.0000
15.750 1.5799 0.05742 0.05110 -0.0528 0.1028 1.0000
16.000 1.5835 0.05975 0.05349 -0.0523 0.0999 1.0000
16.250 1.5907 0.06172 0.05553 -0.0518 0.0970 1.0000
16.500 1.5949 0.06403 0.05789 -0.0514 0.0933 1.0000
16.750 1.5963 0.06669 0.06058 -0.0510 0.0895 1.0000
17.000 1.6003 0.06906 0.06301 -0.0507 0.0840 1.0000
17.250 1.5980 0.07218 0.06612 -0.0503 0.0756 1.0000
17.500 1.5895 0.07605 0.06994 -0.0500 0.0648 1.0000
18.000 1.5716 0.08416 0.07805 -0.0498 0.0507 1.0000
18.250 1.5637 0.08816 0.08210 -0.0498 0.0455 1.0000
18.500 1.5550 0.09236 0.08633 -0.0501 0.0406 1.0000
18.750 1.5461 0.09664 0.09065 -0.0505 0.0357 1.0000
19.000 1.5370 0.10103 0.09509 -0.0510 0.0313 1.0000
19.250 1.5276 0.10550 0.09960 -0.0517 0.0273 1.0000
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