GOE 433 AIRFOIL (goe433-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 433 AIRFOIL (goe433-il) Reynolds number: 500,000 Max Cl/Cd: 89.02 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe433-il-500000-n5.txt Download as CSV file: xf-goe433-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 433 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
------ -------- --------- --------- -------- -------- --------
-18.250 -0.8184 0.11127 0.10792 -0.0496 1.0000 0.0466
-18.000 -0.8557 0.10132 0.09780 -0.0557 1.0000 0.0476
-17.750 -0.8799 0.09372 0.09006 -0.0604 1.0000 0.0482
-17.500 -0.8883 0.08887 0.08519 -0.0633 1.0000 0.0489
-17.250 -0.8995 0.08355 0.07983 -0.0667 1.0000 0.0495
-17.000 -0.9118 0.07815 0.07437 -0.0701 1.0000 0.0502
-16.750 -0.9246 0.07271 0.06884 -0.0737 1.0000 0.0508
-16.500 -0.9367 0.06748 0.06352 -0.0772 1.0000 0.0515
-16.250 -0.9472 0.06254 0.05848 -0.0806 1.0000 0.0521
-16.000 -0.9563 0.05790 0.05374 -0.0838 1.0000 0.0527
-15.750 -0.9644 0.05357 0.04931 -0.0868 1.0000 0.0532
-15.500 -0.9705 0.04956 0.04518 -0.0896 1.0000 0.0537
-15.250 -0.9764 0.04571 0.04130 -0.0923 1.0000 0.0542
-15.000 -0.9806 0.04212 0.03767 -0.0949 1.0000 0.0547
-14.750 -0.9832 0.03882 0.03432 -0.0974 0.9988 0.0552
-14.500 -0.9712 0.03562 0.03105 -0.1021 0.9794 0.0559
-14.250 -0.9586 0.03284 0.02818 -0.1059 0.9635 0.0567
-14.000 -0.9486 0.03035 0.02558 -0.1086 0.9460 0.0574
-13.750 -0.9364 0.02805 0.02315 -0.1114 0.9294 0.0580
-13.500 -0.9182 0.02595 0.02091 -0.1147 0.9135 0.0588
-13.250 -0.8956 0.02414 0.01894 -0.1182 0.8985 0.0596
-13.000 -0.8731 0.02269 0.01739 -0.1206 0.8860 0.0605
-12.750 -0.8498 0.02170 0.01631 -0.1219 0.8753 0.0613
-12.500 -0.8254 0.02090 0.01542 -0.1228 0.8649 0.0622
-12.250 -0.8003 0.02021 0.01463 -0.1235 0.8559 0.0631
-12.000 -0.7745 0.01959 0.01391 -0.1242 0.8472 0.0641
-11.500 -0.7215 0.01855 0.01266 -0.1252 0.8330 0.0660
-11.250 -0.6950 0.01796 0.01200 -0.1257 0.8262 0.0671
-10.750 -0.6406 0.01697 0.01091 -0.1267 0.8142 0.0692
-10.500 -0.6128 0.01656 0.01043 -0.1271 0.8078 0.0703
-10.250 -0.5850 0.01619 0.00998 -0.1274 0.8018 0.0715
-10.000 -0.5568 0.01584 0.00956 -0.1278 0.7958 0.0727
-9.750 -0.5284 0.01552 0.00916 -0.1281 0.7888 0.0737
-9.500 -0.5007 0.01507 0.00867 -0.1285 0.7816 0.0751
-9.250 -0.4722 0.01470 0.00827 -0.1289 0.7747 0.0763
-9.000 -0.4436 0.01437 0.00789 -0.1292 0.7669 0.0777
-8.750 -0.4150 0.01410 0.00755 -0.1295 0.7596 0.0791
-8.500 -0.3860 0.01383 0.00722 -0.1297 0.7509 0.0806
-8.250 -0.3574 0.01359 0.00689 -0.1299 0.7414 0.0819
-8.000 -0.3286 0.01325 0.00653 -0.1303 0.7300 0.0835
-7.750 -0.2999 0.01298 0.00621 -0.1305 0.7181 0.0852
-7.500 -0.2711 0.01276 0.00592 -0.1307 0.7053 0.0871
-7.250 -0.2422 0.01258 0.00565 -0.1309 0.6920 0.0890
-7.000 -0.2135 0.01241 0.00539 -0.1310 0.6791 0.0908
-6.750 -0.1849 0.01221 0.00512 -0.1312 0.6659 0.0931
-6.500 -0.1561 0.01206 0.00490 -0.1314 0.6539 0.0957
-6.250 -0.1271 0.01193 0.00471 -0.1315 0.6444 0.0986
-6.000 -0.0979 0.01177 0.00452 -0.1318 0.6372 0.1020
-5.750 -0.0687 0.01164 0.00435 -0.1320 0.6309 0.1060
-5.500 -0.0393 0.01153 0.00420 -0.1322 0.6257 0.1100
-5.250 -0.0097 0.01138 0.00406 -0.1325 0.6209 0.1155
-5.000 0.0199 0.01129 0.00395 -0.1327 0.6161 0.1211
-4.750 0.0493 0.01119 0.00383 -0.1329 0.6113 0.1268
-4.500 0.0787 0.01113 0.00374 -0.1331 0.6070 0.1323
-4.250 0.1085 0.01102 0.00364 -0.1334 0.6036 0.1373
-4.000 0.1383 0.01093 0.00355 -0.1336 0.5996 0.1430
-3.750 0.1679 0.01088 0.00348 -0.1338 0.5953 0.1477
-3.500 0.1974 0.01081 0.00339 -0.1340 0.5911 0.1526
-3.000 0.2567 0.01070 0.00326 -0.1344 0.5841 0.1621
-2.750 0.2865 0.01061 0.00319 -0.1347 0.5802 0.1676
-2.500 0.3162 0.01054 0.00314 -0.1349 0.5759 0.1738
-2.250 0.3457 0.01052 0.00309 -0.1351 0.5715 0.1792
-2.000 0.3751 0.01048 0.00305 -0.1353 0.5676 0.1867
-1.750 0.4049 0.01042 0.00302 -0.1355 0.5641 0.1954
-1.500 0.4347 0.01033 0.00300 -0.1358 0.5598 0.2081
-1.250 0.4642 0.01027 0.00298 -0.1360 0.5549 0.2232
-1.000 0.4935 0.01024 0.00298 -0.1362 0.5500 0.2403
-0.750 0.5229 0.01021 0.00299 -0.1364 0.5458 0.2577
-0.500 0.5526 0.01016 0.00300 -0.1366 0.5411 0.2746
-0.250 0.5820 0.01014 0.00302 -0.1368 0.5355 0.2906
0.000 0.6110 0.01015 0.00303 -0.1369 0.5296 0.3041
0.250 0.6403 0.01015 0.00305 -0.1370 0.5240 0.3152
0.500 0.6695 0.01015 0.00308 -0.1372 0.5177 0.3274
0.750 0.6983 0.01017 0.00312 -0.1372 0.5113 0.3410
1.000 0.7273 0.01018 0.00317 -0.1373 0.5038 0.3572
1.250 0.7556 0.01023 0.00324 -0.1373 0.4927 0.3774
1.500 0.7838 0.01029 0.00332 -0.1373 0.4808 0.3991
1.750 0.8117 0.01040 0.00343 -0.1372 0.4704 0.4180
2.000 0.8398 0.01051 0.00354 -0.1372 0.4612 0.4334
2.250 0.8673 0.01067 0.00366 -0.1370 0.4506 0.4470
2.750 0.9212 0.01104 0.00396 -0.1365 0.4251 0.4720
3.000 0.9480 0.01125 0.00413 -0.1363 0.4145 0.4834
3.250 0.9749 0.01143 0.00429 -0.1360 0.4044 0.4905
3.500 1.0016 0.01163 0.00447 -0.1358 0.3945 0.4984
3.750 1.0279 0.01186 0.00465 -0.1354 0.3842 0.5070
4.000 1.0546 0.01204 0.00484 -0.1352 0.3756 0.5156
4.250 1.0805 0.01228 0.00504 -0.1348 0.3653 0.5224
4.500 1.1067 0.01249 0.00522 -0.1345 0.3556 0.5273
4.750 1.1317 0.01276 0.00546 -0.1340 0.3445 0.5323
5.000 1.1573 0.01300 0.00568 -0.1336 0.3330 0.5383
5.250 1.1817 0.01330 0.00593 -0.1330 0.3200 0.5442
5.500 1.2052 0.01365 0.00622 -0.1323 0.3050 0.5496
5.750 1.2277 0.01404 0.00655 -0.1315 0.2876 0.5552
6.000 1.2487 0.01452 0.00693 -0.1305 0.2667 0.5612
6.250 1.2671 0.01514 0.00742 -0.1291 0.2417 0.5685
6.500 1.2820 0.01592 0.00805 -0.1272 0.2100 0.5770
6.750 1.2911 0.01689 0.00882 -0.1244 0.1761 0.5849
7.000 1.3034 0.01762 0.00950 -0.1221 0.1587 0.5944
7.500 1.3341 0.01896 0.01082 -0.1188 0.1379 0.6187
7.750 1.3503 0.01960 0.01148 -0.1173 0.1294 0.6330
8.000 1.3652 0.02032 0.01223 -0.1158 0.1210 0.6507
8.250 1.3787 0.02113 0.01309 -0.1141 0.1115 0.6806
8.500 1.3904 0.02201 0.01409 -0.1124 0.0998 0.7486
8.750 1.3865 0.02330 0.01557 -0.1085 0.0687 1.0000
9.000 1.3914 0.02492 0.01712 -0.1065 0.0593 1.0000
9.250 1.4021 0.02619 0.01839 -0.1051 0.0564 1.0000
9.500 1.4144 0.02737 0.01960 -0.1040 0.0550 1.0000
9.750 1.4264 0.02860 0.02086 -0.1029 0.0540 1.0000
10.000 1.4377 0.02992 0.02221 -0.1017 0.0532 1.0000
10.250 1.4483 0.03133 0.02365 -0.1007 0.0525 1.0000
10.500 1.4581 0.03282 0.02518 -0.0996 0.0520 1.0000
10.750 1.4667 0.03444 0.02685 -0.0985 0.0514 1.0000
11.000 1.4746 0.03617 0.02862 -0.0975 0.0509 1.0000
11.250 1.4816 0.03803 0.03053 -0.0965 0.0505 1.0000
11.500 1.4876 0.04000 0.03255 -0.0956 0.0501 1.0000
11.750 1.4948 0.04191 0.03452 -0.0948 0.0499 1.0000
12.000 1.5012 0.04395 0.03662 -0.0941 0.0497 1.0000
12.250 1.5071 0.04610 0.03883 -0.0934 0.0495 1.0000
12.500 1.5123 0.04836 0.04115 -0.0928 0.0492 1.0000
12.750 1.5168 0.05072 0.04357 -0.0922 0.0490 1.0000
13.000 1.5208 0.05319 0.04611 -0.0917 0.0488 1.0000
13.250 1.5238 0.05580 0.04879 -0.0912 0.0486 1.0000
13.500 1.5266 0.05843 0.05149 -0.0908 0.0484 1.0000
13.750 1.5285 0.06121 0.05434 -0.0904 0.0482 1.0000
14.000 1.5296 0.06412 0.05732 -0.0901 0.0481 1.0000
14.250 1.5307 0.06705 0.06032 -0.0899 0.0479 1.0000
14.500 1.5306 0.07016 0.06351 -0.0897 0.0477 1.0000
14.750 1.5305 0.07329 0.06670 -0.0895 0.0476 1.0000
15.000 1.5299 0.07653 0.07002 -0.0894 0.0474 1.0000
15.250 1.5288 0.07988 0.07345 -0.0894 0.0473 1.0000
15.500 1.5280 0.08321 0.07684 -0.0895 0.0471 1.0000
15.750 1.5260 0.08673 0.08044 -0.0896 0.0470 1.0000
16.000 1.5245 0.09021 0.08400 -0.0898 0.0469 1.0000
16.250 1.5231 0.09372 0.08757 -0.0901 0.0467 1.0000
16.500 1.5209 0.09736 0.09128 -0.0905 0.0464 1.0000
16.750 1.5193 0.10090 0.09488 -0.0909 0.0461 1.0000
17.000 1.5164 0.10465 0.09870 -0.0914 0.0459 1.0000
17.250 1.5142 0.10830 0.10240 -0.0920 0.0455 1.0000
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