GOE 405 AIRFOIL (goe405-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 405 AIRFOIL (goe405-il) Reynolds number: 500,000 Max Cl/Cd: 104.56 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe405-il-500000-n5.txt Download as CSV file: xf-goe405-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 405 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0972 0.09688 0.09444 -0.0927 0.9568 0.0090
-10.500 -0.0861 0.09240 0.08996 -0.0969 0.9521 0.0095
-9.500 -0.2767 0.02394 0.02030 -0.1513 0.8770 0.0113
-9.250 -0.2618 0.02098 0.01698 -0.1514 0.8687 0.0118
-9.000 -0.2421 0.01923 0.01490 -0.1513 0.8613 0.0123
-8.750 -0.2220 0.01791 0.01336 -0.1507 0.8533 0.0129
-8.500 -0.1977 0.01720 0.01252 -0.1505 0.8462 0.0136
-8.250 -0.1739 0.01660 0.01179 -0.1501 0.8380 0.0143
-7.750 -0.1252 0.01542 0.01027 -0.1493 0.8220 0.0163
-7.500 -0.1003 0.01495 0.00967 -0.1490 0.8143 0.0173
-7.250 -0.0744 0.01476 0.00943 -0.1487 0.8057 0.0183
-7.000 -0.0487 0.01448 0.00904 -0.1484 0.7980 0.0195
-6.750 -0.0235 0.01409 0.00848 -0.1480 0.7899 0.0207
-6.500 0.0024 0.01382 0.00804 -0.1476 0.7825 0.0218
-6.250 0.0270 0.01334 0.00746 -0.1472 0.7747 0.0231
-6.000 0.0528 0.01312 0.00716 -0.1468 0.7674 0.0242
-5.750 0.0783 0.01288 0.00681 -0.1464 0.7587 0.0254
-5.500 0.1038 0.01264 0.00643 -0.1460 0.7495 0.0268
-5.250 0.1292 0.01244 0.00609 -0.1454 0.7400 0.0280
-5.000 0.1550 0.01224 0.00578 -0.1450 0.7312 0.0287
-4.750 0.1797 0.01178 0.00518 -0.1445 0.7244 0.0301
-4.500 0.2052 0.01140 0.00473 -0.1441 0.7183 0.0314
-4.250 0.2311 0.01117 0.00442 -0.1437 0.7123 0.0326
-4.000 0.2572 0.01097 0.00415 -0.1434 0.7071 0.0338
-3.750 0.2834 0.01075 0.00386 -0.1430 0.7014 0.0348
-3.500 0.3094 0.01057 0.00359 -0.1426 0.6959 0.0357
-3.250 0.3357 0.01040 0.00336 -0.1423 0.6904 0.0366
-3.000 0.3620 0.01026 0.00316 -0.1419 0.6848 0.0375
-2.750 0.3880 0.01013 0.00295 -0.1415 0.6795 0.0391
-2.500 0.4142 0.00996 0.00275 -0.1412 0.6737 0.0416
-2.250 0.4403 0.00984 0.00260 -0.1408 0.6679 0.0444
-2.000 0.4664 0.00977 0.00248 -0.1404 0.6626 0.0481
-1.750 0.4925 0.00963 0.00237 -0.1401 0.6566 0.0593
-1.500 0.5178 0.00950 0.00230 -0.1396 0.6503 0.0853
-1.250 0.5437 0.00944 0.00226 -0.1392 0.6443 0.1045
-1.000 0.5697 0.00941 0.00224 -0.1389 0.6377 0.1180
-0.750 0.5952 0.00941 0.00223 -0.1384 0.6312 0.1308
-0.500 0.6211 0.00940 0.00224 -0.1380 0.6237 0.1450
-0.250 0.6463 0.00942 0.00225 -0.1375 0.6165 0.1557
0.000 0.6721 0.00944 0.00225 -0.1371 0.6085 0.1642
0.250 0.6970 0.00947 0.00227 -0.1365 0.6005 0.1725
0.500 0.7220 0.00951 0.00230 -0.1360 0.5911 0.1831
0.750 0.7467 0.00956 0.00233 -0.1354 0.5819 0.1924
1.000 0.7706 0.00963 0.00236 -0.1346 0.5717 0.1997
1.250 0.7951 0.00969 0.00240 -0.1340 0.5608 0.2071
1.500 0.8188 0.00976 0.00246 -0.1332 0.5498 0.2155
1.750 0.8419 0.00987 0.00253 -0.1323 0.5373 0.2240
2.000 0.8644 0.00998 0.00261 -0.1313 0.5239 0.2327
2.250 0.8863 0.01012 0.00270 -0.1302 0.5095 0.2425
2.750 0.9288 0.01043 0.00294 -0.1278 0.4810 0.2717
3.000 0.9509 0.01054 0.00308 -0.1268 0.4698 0.2946
3.250 0.9714 0.01050 0.00325 -0.1255 0.4601 0.3973
3.750 1.0379 0.00993 0.00379 -0.1287 0.4402 1.0000
4.000 1.0588 0.01015 0.00395 -0.1274 0.4324 1.0000
4.250 1.0801 0.01033 0.00411 -0.1262 0.4253 1.0000
4.500 1.0995 0.01055 0.00429 -0.1247 0.4185 1.0000
4.750 1.1199 0.01074 0.00446 -0.1233 0.4113 1.0000
5.000 1.1387 0.01098 0.00467 -0.1217 0.4048 1.0000
5.250 1.1595 0.01116 0.00486 -0.1204 0.3987 1.0000
5.500 1.1794 0.01138 0.00508 -0.1191 0.3928 1.0000
5.750 1.1989 0.01163 0.00532 -0.1176 0.3872 1.0000
6.000 1.2195 0.01184 0.00554 -0.1164 0.3810 1.0000
6.250 1.2371 0.01215 0.00583 -0.1147 0.3718 1.0000
6.500 1.2551 0.01245 0.00611 -0.1131 0.3610 1.0000
6.750 1.2719 0.01280 0.00643 -0.1113 0.3477 1.0000
7.000 1.2892 0.01315 0.00676 -0.1096 0.3369 1.0000
7.250 1.3043 0.01360 0.00715 -0.1076 0.3213 1.0000
7.500 1.3195 0.01405 0.00757 -0.1057 0.3076 1.0000
7.750 1.3312 0.01468 0.00810 -0.1033 0.2862 1.0000
8.000 1.3415 0.01540 0.00870 -0.1007 0.2636 1.0000
8.250 1.3495 0.01627 0.00944 -0.0979 0.2397 1.0000
8.500 1.3573 0.01720 0.01024 -0.0952 0.2146 1.0000
8.750 1.3642 0.01822 0.01115 -0.0924 0.1902 1.0000
9.000 1.3614 0.01984 0.01250 -0.0886 0.1464 1.0000
9.250 1.3384 0.02283 0.01502 -0.0826 0.0659 1.0000
9.500 1.3300 0.02512 0.01711 -0.0787 0.0233 1.0000
9.750 1.3380 0.02635 0.01835 -0.0768 0.0176 1.0000
10.000 1.3472 0.02755 0.01959 -0.0751 0.0147 1.0000
10.250 1.3579 0.02866 0.02078 -0.0736 0.0136 1.0000
10.500 1.3674 0.02990 0.02209 -0.0722 0.0127 1.0000
10.750 1.3752 0.03129 0.02355 -0.0706 0.0118 1.0000
11.000 1.3803 0.03297 0.02531 -0.0690 0.0107 1.0000
11.250 1.3869 0.03457 0.02700 -0.0676 0.0103 1.0000
11.500 1.3944 0.03613 0.02864 -0.0664 0.0099 1.0000
11.750 1.4005 0.03786 0.03045 -0.0651 0.0092 1.0000
12.000 1.4061 0.03970 0.03236 -0.0640 0.0088 1.0000
12.250 1.4096 0.04178 0.03452 -0.0628 0.0084 1.0000
12.500 1.4123 0.04400 0.03682 -0.0618 0.0081 1.0000
12.750 1.4131 0.04649 0.03939 -0.0608 0.0078 1.0000
13.000 1.4090 0.04959 0.04259 -0.0597 0.0076 1.0000
13.250 1.4087 0.05236 0.04548 -0.0590 0.0073 1.0000
13.500 1.4093 0.05511 0.04833 -0.0584 0.0072 1.0000
13.750 1.4107 0.05782 0.05113 -0.0580 0.0069 1.0000
14.000 1.4067 0.06128 0.05471 -0.0576 0.0068 1.0000
14.250 1.4082 0.06413 0.05764 -0.0574 0.0064 1.0000
14.500 1.4047 0.06767 0.06128 -0.0573 0.0062 1.0000
14.750 1.4006 0.07140 0.06511 -0.0573 0.0061 1.0000
15.000 1.3969 0.07515 0.06895 -0.0575 0.0059 1.0000
15.250 1.3937 0.07890 0.07280 -0.0578 0.0058 1.0000
15.500 1.3877 0.08313 0.07713 -0.0583 0.0057 1.0000
15.750 1.3824 0.08730 0.08138 -0.0589 0.0056 1.0000
16.000 1.3752 0.09184 0.08602 -0.0597 0.0054 1.0000
16.250 1.3671 0.09658 0.09085 -0.0606 0.0053 1.0000
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