GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 484 AIRFOIL (goe484-il) Reynolds number: 500,000 Max Cl/Cd: 128 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe484-il-500000.txt Download as CSV file: xf-goe484-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 484 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3719 0.11143 0.10909 -0.0296 1.0000 0.0211
-9.250 -0.3772 0.10941 0.10711 -0.0289 1.0000 0.0212
-9.000 -0.3839 0.10744 0.10518 -0.0278 1.0000 0.0212
-8.750 -0.3825 0.10457 0.10232 -0.0290 0.9992 0.0212
-8.500 -0.3684 0.09950 0.09724 -0.0296 0.9982 0.0216
-8.250 -0.3502 0.09602 0.09375 -0.0323 0.9964 0.0219
-8.000 -0.3308 0.09268 0.09041 -0.0359 0.9945 0.0224
-7.750 -0.3143 0.08934 0.08706 -0.0397 0.9913 0.0229
-7.500 -0.2967 0.08588 0.08360 -0.0442 0.9878 0.0240
-7.250 -0.2683 0.08085 0.07855 -0.0562 0.9837 0.0261
-7.000 -0.2437 0.07586 0.07353 -0.0663 0.9765 0.0264
-6.750 -0.2125 0.07058 0.06822 -0.0759 0.9735 0.0265
-6.500 -0.1948 0.06527 0.06289 -0.0797 0.9720 0.0272
-6.250 -0.1751 0.06266 0.06027 -0.0819 0.9676 0.0276
-6.000 -0.1514 0.05993 0.05752 -0.0853 0.9637 0.0284
-5.750 -0.1190 0.05617 0.05372 -0.0922 0.9612 0.0300
-5.500 -0.0583 0.04909 0.04646 -0.1098 0.9593 0.0331
-5.250 -0.0165 0.04061 0.03779 -0.1217 0.9579 0.0340
-5.000 0.0038 0.03876 0.03590 -0.1225 0.9523 0.0347
-4.750 0.0334 0.03677 0.03387 -0.1252 0.9493 0.0357
-4.500 0.0684 0.03394 0.03093 -0.1294 0.9469 0.0378
-4.250 0.1150 0.02638 0.02280 -0.1377 0.9444 0.0433
-4.000 0.1407 0.02529 0.02170 -0.1383 0.9401 0.0443
-3.750 0.1667 0.02412 0.02046 -0.1389 0.9354 0.0460
-3.500 0.2011 0.02079 0.01660 -0.1413 0.9321 0.0538
-3.250 0.2310 0.01968 0.01553 -0.1425 0.9296 0.0555
-3.000 0.2560 0.01905 0.01487 -0.1422 0.9244 0.0584
-2.750 0.2846 0.01750 0.01303 -0.1428 0.9196 0.0670
-2.500 0.3177 0.01263 0.00722 -0.1428 0.9161 0.0437
-2.250 0.3463 0.01251 0.00700 -0.1426 0.9114 0.0423
-2.000 0.3729 0.01127 0.00564 -0.1422 0.9059 0.0409
-1.750 0.4021 0.01050 0.00476 -0.1424 0.9017 0.0404
-1.500 0.4297 0.01005 0.00426 -0.1421 0.8966 0.0408
-1.250 0.4567 0.00961 0.00378 -0.1417 0.8906 0.0410
-1.000 0.4858 0.00914 0.00326 -0.1418 0.8857 0.0409
-0.750 0.5117 0.00883 0.00294 -0.1412 0.8787 0.0410
-0.500 0.5398 0.00855 0.00263 -0.1410 0.8724 0.0415
-0.250 0.5667 0.00835 0.00243 -0.1406 0.8655 0.0421
0.000 0.5941 0.00810 0.00215 -0.1403 0.8583 0.0437
0.250 0.6209 0.00797 0.00201 -0.1398 0.8494 0.0458
0.500 0.6482 0.00787 0.00188 -0.1394 0.8390 0.0491
0.750 0.6742 0.00777 0.00178 -0.1387 0.8247 0.0599
1.000 0.6991 0.00756 0.00179 -0.1379 0.8071 0.1520
1.250 0.7238 0.00746 0.00177 -0.1370 0.7864 0.2045
1.500 0.7456 0.00680 0.00192 -0.1359 0.7622 0.5676
1.750 0.7757 0.00606 0.00193 -0.1362 0.7316 1.0000
2.000 0.7982 0.00627 0.00192 -0.1348 0.6906 1.0000
2.250 0.8201 0.00657 0.00199 -0.1333 0.6521 1.0000
2.500 0.8423 0.00690 0.00213 -0.1320 0.6201 1.0000
2.750 0.8645 0.00724 0.00229 -0.1307 0.5887 1.0000
3.000 0.8867 0.00757 0.00246 -0.1294 0.5534 1.0000
3.250 0.9079 0.00796 0.00264 -0.1280 0.5084 1.0000
3.500 0.9189 0.00910 0.00303 -0.1248 0.3509 1.0000
3.750 0.9196 0.01164 0.00414 -0.1204 0.0789 1.0000
4.000 0.9416 0.01218 0.00457 -0.1193 0.0589 1.0000
4.250 0.9645 0.01261 0.00497 -0.1182 0.0533 1.0000
4.500 0.9867 0.01311 0.00549 -0.1171 0.0494 1.0000
4.750 1.0099 0.01348 0.00589 -0.1161 0.0478 1.0000
5.000 1.0325 0.01390 0.00635 -0.1151 0.0460 1.0000
5.250 1.0544 0.01437 0.00684 -0.1139 0.0440 1.0000
5.500 1.0753 0.01492 0.00739 -0.1126 0.0420 1.0000
5.750 1.0929 0.01578 0.00830 -0.1107 0.0400 1.0000
6.000 1.1098 0.01674 0.00932 -0.1087 0.0387 1.0000
6.250 1.1318 0.01715 0.00976 -0.1076 0.0376 1.0000
6.500 1.1526 0.01769 0.01033 -0.1064 0.0362 1.0000
6.750 1.1726 0.01832 0.01101 -0.1049 0.0348 1.0000
7.000 1.1924 0.01895 0.01167 -0.1036 0.0333 1.0000
7.250 1.2111 0.01975 0.01245 -0.1021 0.0317 1.0000
7.500 1.2283 0.02166 0.01440 -0.1005 0.0300 1.0000
7.750 1.2494 0.02209 0.01490 -0.0993 0.0290 1.0000
8.000 1.2702 0.02281 0.01571 -0.0981 0.0278 1.0000
8.250 1.2901 0.02342 0.01637 -0.0968 0.0265 1.0000
8.500 1.3089 0.02399 0.01696 -0.0955 0.0252 1.0000
8.750 1.3280 0.02503 0.01799 -0.0943 0.0241 1.0000
9.000 1.3512 0.02714 0.02025 -0.0939 0.0229 1.0000
9.250 1.3701 0.02798 0.02122 -0.0924 0.0221 1.0000
9.500 1.3888 0.02904 0.02241 -0.0911 0.0210 1.0000
9.750 1.4053 0.02979 0.02323 -0.0894 0.0201 1.0000
10.000 1.4180 0.03034 0.02384 -0.0871 0.0194 1.0000
10.250 1.4294 0.03096 0.02450 -0.0847 0.0188 1.0000
10.500 1.4492 0.03409 0.02782 -0.0844 0.0179 1.0000
10.750 1.4587 0.03532 0.02928 -0.0816 0.0175 1.0000
11.000 1.4682 0.03737 0.03159 -0.0791 0.0169 1.0000
11.250 1.4743 0.03972 0.03421 -0.0762 0.0163 1.0000
11.500 1.4772 0.04193 0.03664 -0.0731 0.0158 1.0000
11.750 1.4784 0.04377 0.03866 -0.0700 0.0155 1.0000
12.000 1.4804 0.04494 0.03993 -0.0672 0.0152 1.0000
12.250 1.4813 0.04626 0.04135 -0.0645 0.0149 1.0000
12.500 1.4850 0.04689 0.04199 -0.0623 0.0146 1.0000
12.750 1.4828 0.04897 0.04420 -0.0600 0.0144 1.0000
13.000 1.4746 0.05212 0.04751 -0.0577 0.0141 1.0000
13.250 1.4471 0.05822 0.05398 -0.0551 0.0139 1.0000
13.500 1.4301 0.06254 0.05855 -0.0536 0.0138 1.0000
13.750 1.4097 0.06769 0.06398 -0.0529 0.0137 1.0000
14.000 1.3863 0.07370 0.07025 -0.0532 0.0137 1.0000
14.250 1.3607 0.08056 0.07735 -0.0547 0.0137 1.0000
14.500 1.3340 0.08825 0.08525 -0.0575 0.0137 1.0000
14.750 1.3076 0.09668 0.09387 -0.0615 0.0138 1.0000
15.000 1.2805 0.10606 0.10343 -0.0668 0.0138 1.0000
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Polar data table (+)
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