GOE 433 AIRFOIL (goe433-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 433 AIRFOIL (goe433-il) Reynolds number: 200,000 Max Cl/Cd: 71.93 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe433-il-200000-n5.txt Download as CSV file: xf-goe433-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7282 0.06165 0.05666 -0.0860 1.0000 0.0695
-13.750 -0.7670 0.05321 0.04800 -0.0928 1.0000 0.0702
-13.500 -0.7891 0.04795 0.04259 -0.0966 1.0000 0.0708
-13.250 -0.8109 0.04412 0.03866 -0.0980 0.9993 0.0713
-13.000 -0.8033 0.03949 0.03377 -0.1058 0.9834 0.0724
-12.750 -0.7914 0.03544 0.02940 -0.1135 0.9675 0.0735
-12.500 -0.7679 0.03380 0.02776 -0.1165 0.9576 0.0745
-12.250 -0.7423 0.03217 0.02607 -0.1200 0.9489 0.0756
-12.000 -0.7214 0.03073 0.02455 -0.1222 0.9374 0.0767
-11.750 -0.6991 0.02940 0.02309 -0.1240 0.9280 0.0779
-11.500 -0.6773 0.02816 0.02170 -0.1253 0.9180 0.0792
-11.250 -0.6551 0.02700 0.02036 -0.1264 0.9085 0.0806
-11.000 -0.6319 0.02597 0.01917 -0.1271 0.8994 0.0819
-10.750 -0.6082 0.02516 0.01835 -0.1274 0.8905 0.0831
-10.500 -0.5838 0.02440 0.01754 -0.1278 0.8817 0.0844
-10.250 -0.5590 0.02368 0.01673 -0.1282 0.8733 0.0858
-10.000 -0.5339 0.02297 0.01592 -0.1285 0.8648 0.0875
-9.750 -0.5081 0.02229 0.01507 -0.1288 0.8576 0.0892
-9.500 -0.4826 0.02163 0.01432 -0.1290 0.8492 0.0908
-9.250 -0.4565 0.02103 0.01370 -0.1292 0.8418 0.0924
-9.000 -0.4301 0.02051 0.01312 -0.1295 0.8341 0.0941
-8.750 -0.4033 0.02002 0.01255 -0.1297 0.8258 0.0960
-8.500 -0.3762 0.01954 0.01195 -0.1298 0.8182 0.0982
-8.250 -0.3492 0.01907 0.01139 -0.1300 0.8093 0.1003
-8.000 -0.3219 0.01862 0.01092 -0.1302 0.8017 0.1023
-7.750 -0.2943 0.01824 0.01050 -0.1304 0.7934 0.1046
-7.500 -0.2665 0.01788 0.01006 -0.1305 0.7850 0.1074
-7.000 -0.2106 0.01717 0.00924 -0.1309 0.7674 0.1130
-6.750 -0.1824 0.01687 0.00889 -0.1310 0.7592 0.1162
-6.500 -0.1541 0.01659 0.00853 -0.1312 0.7497 0.1199
-6.250 -0.1257 0.01630 0.00818 -0.1313 0.7414 0.1237
-6.000 -0.0972 0.01603 0.00791 -0.1316 0.7312 0.1279
-5.750 -0.0687 0.01581 0.00758 -0.1316 0.7223 0.1327
-5.500 -0.0402 0.01555 0.00730 -0.1318 0.7116 0.1372
-5.250 -0.0116 0.01535 0.00703 -0.1319 0.7022 0.1427
-5.000 0.0172 0.01519 0.00677 -0.1320 0.6927 0.1483
-4.750 0.0458 0.01495 0.00651 -0.1322 0.6851 0.1539
-4.500 0.0747 0.01480 0.00630 -0.1323 0.6773 0.1599
-4.250 0.1036 0.01464 0.00608 -0.1325 0.6703 0.1658
-4.000 0.1326 0.01448 0.00590 -0.1327 0.6639 0.1724
-3.750 0.1616 0.01438 0.00574 -0.1328 0.6574 0.1790
-3.500 0.1906 0.01424 0.00559 -0.1330 0.6513 0.1857
-3.250 0.2197 0.01415 0.00545 -0.1332 0.6458 0.1934
-3.000 0.2489 0.01404 0.00537 -0.1334 0.6399 0.2017
-2.750 0.2780 0.01397 0.00528 -0.1336 0.6344 0.2114
-2.500 0.3071 0.01392 0.00521 -0.1337 0.6294 0.2219
-2.250 0.3363 0.01387 0.00517 -0.1339 0.6241 0.2339
-2.000 0.3654 0.01382 0.00515 -0.1341 0.6184 0.2484
-1.750 0.3945 0.01379 0.00515 -0.1343 0.6133 0.2654
-1.500 0.4236 0.01379 0.00513 -0.1344 0.6087 0.2827
-1.250 0.4526 0.01376 0.00516 -0.1346 0.6035 0.2990
-1.000 0.4815 0.01373 0.00518 -0.1347 0.5978 0.3142
-0.500 0.5394 0.01378 0.00522 -0.1349 0.5879 0.3444
-0.250 0.5682 0.01378 0.00531 -0.1350 0.5826 0.3609
0.000 0.5968 0.01380 0.00541 -0.1350 0.5767 0.3791
0.250 0.6254 0.01386 0.00550 -0.1350 0.5710 0.3981
0.500 0.6540 0.01396 0.00559 -0.1350 0.5660 0.4162
0.750 0.6824 0.01402 0.00573 -0.1350 0.5601 0.4326
1.000 0.7108 0.01411 0.00583 -0.1349 0.5540 0.4482
1.250 0.7390 0.01423 0.00592 -0.1348 0.5485 0.4630
1.500 0.7671 0.01432 0.00607 -0.1347 0.5421 0.4758
1.750 0.7951 0.01442 0.00618 -0.1346 0.5354 0.4886
2.000 0.8229 0.01453 0.00629 -0.1344 0.5297 0.5017
2.250 0.8506 0.01464 0.00645 -0.1343 0.5234 0.5143
2.500 0.8782 0.01476 0.00657 -0.1341 0.5162 0.5268
2.750 0.9053 0.01486 0.00668 -0.1338 0.5097 0.5373
3.000 0.9325 0.01498 0.00683 -0.1336 0.5014 0.5473
3.250 0.9591 0.01508 0.00693 -0.1333 0.4932 0.5550
3.500 0.9856 0.01521 0.00706 -0.1330 0.4838 0.5630
3.750 1.0112 0.01535 0.00716 -0.1325 0.4738 0.5704
4.000 1.0368 0.01549 0.00733 -0.1320 0.4629 0.5787
4.250 1.0619 0.01569 0.00747 -0.1314 0.4531 0.5868
4.500 1.0869 0.01587 0.00768 -0.1309 0.4428 0.5943
4.750 1.1115 0.01611 0.00788 -0.1303 0.4332 0.6031
5.000 1.1355 0.01633 0.00812 -0.1297 0.4227 0.6118
5.250 1.1594 0.01659 0.00837 -0.1290 0.4128 0.6217
5.500 1.1828 0.01685 0.00866 -0.1282 0.4033 0.6332
5.750 1.2062 0.01710 0.00896 -0.1275 0.3949 0.6490
6.000 1.2285 0.01737 0.00929 -0.1266 0.3853 0.6682
6.250 1.2507 0.01764 0.00963 -0.1256 0.3761 0.6914
6.500 1.2720 0.01791 0.00999 -0.1245 0.3669 0.7226
6.750 1.2923 0.01815 0.01035 -0.1232 0.3588 0.7710
7.000 1.3084 0.01819 0.01063 -0.1209 0.3503 0.9070
7.250 1.3274 0.01859 0.01100 -0.1196 0.3413 1.0000
7.500 1.3452 0.01907 0.01144 -0.1181 0.3299 1.0000
7.750 1.3622 0.01958 0.01192 -0.1166 0.3189 1.0000
8.000 1.3773 0.02020 0.01250 -0.1148 0.3076 1.0000
8.250 1.3921 0.02086 0.01313 -0.1132 0.2950 1.0000
8.500 1.4059 0.02161 0.01383 -0.1114 0.2817 1.0000
8.750 1.4177 0.02249 0.01467 -0.1096 0.2678 1.0000
9.000 1.4278 0.02351 0.01564 -0.1076 0.2528 1.0000
9.250 1.4358 0.02472 0.01678 -0.1057 0.2368 1.0000
9.500 1.4419 0.02612 0.01811 -0.1037 0.2201 1.0000
9.750 1.4469 0.02770 0.01962 -0.1018 0.2046 1.0000
10.000 1.4511 0.02941 0.02128 -0.1000 0.1912 1.0000
10.250 1.4536 0.03133 0.02315 -0.0983 0.1788 1.0000
10.500 1.4576 0.03321 0.02500 -0.0968 0.1691 1.0000
10.750 1.4626 0.03506 0.02686 -0.0954 0.1621 1.0000
11.000 1.4677 0.03696 0.02878 -0.0942 0.1558 1.0000
11.250 1.4717 0.03900 0.03085 -0.0930 0.1507 1.0000
11.500 1.4778 0.04089 0.03279 -0.0920 0.1456 1.0000
11.750 1.4815 0.04307 0.03500 -0.0911 0.1406 1.0000
12.000 1.4854 0.04527 0.03725 -0.0902 0.1363 1.0000
12.250 1.4903 0.04743 0.03946 -0.0894 0.1313 1.0000
12.500 1.4906 0.05013 0.04219 -0.0887 0.1251 1.0000
12.750 1.4944 0.05252 0.04463 -0.0881 0.1191 1.0000
13.000 1.4945 0.05536 0.04750 -0.0876 0.1128 1.0000
13.250 1.4947 0.05823 0.05039 -0.0871 0.1044 1.0000
13.500 1.4927 0.06141 0.05358 -0.0867 0.0948 1.0000
13.750 1.4886 0.06488 0.05705 -0.0864 0.0840 1.0000
14.000 1.4829 0.06861 0.06076 -0.0862 0.0757 1.0000
14.250 1.4783 0.07225 0.06441 -0.0860 0.0718 1.0000
14.500 1.4752 0.07578 0.06796 -0.0860 0.0692 1.0000
14.750 1.4725 0.07931 0.07155 -0.0860 0.0677 1.0000
15.000 1.4706 0.08277 0.07507 -0.0861 0.0666 1.0000
15.250 1.4688 0.08627 0.07864 -0.0863 0.0657 1.0000
15.500 1.4665 0.08989 0.08234 -0.0866 0.0650 1.0000
15.750 1.4643 0.09353 0.08606 -0.0869 0.0643 1.0000
16.000 1.4618 0.09724 0.08984 -0.0874 0.0637 1.0000
16.250 1.4588 0.10104 0.09373 -0.0879 0.0632 1.0000
16.500 1.4563 0.10482 0.09758 -0.0886 0.0627 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 433 AIRFOIL (goe433-il)