GOE 446 AIRFOIL (goe446-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: GOE 446 AIRFOIL (goe446-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.36 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe446-il-1000000-n5.txt Download as CSV file: xf-goe446-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 446 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.1713 0.11958 0.11753 -0.0797 0.9291 0.0156
-12.250 -0.1655 0.11641 0.11434 -0.0810 0.9228 0.0159
-11.250 -0.4767 0.02711 0.02375 -0.1503 0.8384 0.0211
-11.000 -0.4585 0.02503 0.02144 -0.1514 0.8253 0.0212
-10.750 -0.4374 0.02369 0.01994 -0.1520 0.8139 0.0214
-10.250 -0.3919 0.02156 0.01750 -0.1527 0.7950 0.0217
-9.750 -0.3448 0.01956 0.01519 -0.1532 0.7802 0.0219
-9.500 -0.3205 0.01870 0.01418 -0.1533 0.7730 0.0221
-9.250 -0.2956 0.01790 0.01323 -0.1535 0.7668 0.0222
-9.000 -0.2702 0.01716 0.01237 -0.1536 0.7608 0.0223
-8.750 -0.2446 0.01649 0.01156 -0.1537 0.7552 0.0225
-8.500 -0.2186 0.01585 0.01079 -0.1538 0.7506 0.0226
-8.250 -0.1921 0.01525 0.01009 -0.1539 0.7457 0.0228
-8.000 -0.1656 0.01470 0.00942 -0.1540 0.7407 0.0229
-7.500 -0.1117 0.01372 0.00823 -0.1542 0.7319 0.0232
-7.250 -0.0844 0.01328 0.00770 -0.1543 0.7270 0.0234
-7.000 -0.0573 0.01289 0.00721 -0.1543 0.7214 0.0235
-6.750 -0.0298 0.01252 0.00676 -0.1544 0.7164 0.0237
-6.500 -0.0020 0.01217 0.00633 -0.1545 0.7116 0.0239
-6.250 0.0258 0.01186 0.00595 -0.1546 0.7072 0.0240
-6.000 0.0535 0.01159 0.00560 -0.1546 0.7026 0.0242
-5.750 0.0817 0.01132 0.00527 -0.1548 0.6983 0.0243
-5.500 0.1099 0.01109 0.00499 -0.1549 0.6936 0.0244
-5.250 0.1378 0.01079 0.00462 -0.1550 0.6888 0.0247
-5.000 0.1654 0.01046 0.00423 -0.1551 0.6842 0.0251
-4.750 0.1938 0.01020 0.00394 -0.1552 0.6798 0.0254
-4.500 0.2222 0.01000 0.00371 -0.1554 0.6754 0.0257
-4.250 0.2504 0.00983 0.00350 -0.1555 0.6713 0.0260
-4.000 0.2787 0.00968 0.00331 -0.1556 0.6675 0.0263
-3.750 0.3074 0.00951 0.00313 -0.1558 0.6641 0.0266
-3.500 0.3360 0.00937 0.00296 -0.1560 0.6603 0.0270
-3.250 0.3644 0.00924 0.00281 -0.1561 0.6564 0.0273
-3.000 0.3926 0.00914 0.00267 -0.1562 0.6524 0.0277
-2.750 0.4213 0.00903 0.00254 -0.1564 0.6487 0.0280
-2.500 0.4499 0.00893 0.00243 -0.1565 0.6440 0.0284
-2.250 0.4782 0.00886 0.00233 -0.1566 0.6389 0.0287
-2.000 0.5063 0.00878 0.00222 -0.1567 0.6342 0.0293
-1.750 0.5349 0.00868 0.00212 -0.1568 0.6297 0.0302
-1.500 0.5632 0.00862 0.00204 -0.1569 0.6244 0.0312
-1.000 0.6196 0.00854 0.00194 -0.1571 0.6139 0.0337
-0.750 0.6477 0.00850 0.00189 -0.1572 0.6076 0.0365
-0.500 0.6754 0.00842 0.00185 -0.1572 0.6013 0.0525
-0.250 0.7033 0.00837 0.00187 -0.1573 0.5937 0.0743
0.000 0.7306 0.00840 0.00189 -0.1572 0.5855 0.0820
0.250 0.7583 0.00843 0.00192 -0.1572 0.5763 0.0875
0.500 0.7854 0.00849 0.00195 -0.1571 0.5674 0.0908
0.750 0.8125 0.00854 0.00199 -0.1571 0.5573 0.0976
1.000 0.8395 0.00860 0.00204 -0.1569 0.5474 0.1030
1.250 0.8659 0.00870 0.00209 -0.1567 0.5364 0.1077
1.500 0.8923 0.00879 0.00217 -0.1565 0.5245 0.1142
2.000 0.9444 0.00900 0.00234 -0.1560 0.5007 0.1333
2.250 0.9699 0.00913 0.00245 -0.1556 0.4885 0.1512
2.500 0.9956 0.00922 0.00258 -0.1554 0.4773 0.1814
2.750 1.0215 0.00926 0.00271 -0.1552 0.4685 0.2369
3.000 1.0468 0.00928 0.00289 -0.1549 0.4583 0.3391
3.250 1.0663 0.00833 0.00325 -0.1536 0.4498 0.9043
3.500 1.0909 0.00843 0.00337 -0.1529 0.4402 1.0000
3.750 1.1165 0.00859 0.00349 -0.1526 0.4325 1.0000
4.000 1.1409 0.00881 0.00366 -0.1521 0.4248 1.0000
4.250 1.1667 0.00896 0.00378 -0.1518 0.4194 1.0000
4.500 1.1915 0.00914 0.00394 -0.1513 0.4129 1.0000
4.750 1.2155 0.00936 0.00411 -0.1507 0.4057 1.0000
5.000 1.2395 0.00957 0.00428 -0.1501 0.3966 1.0000
5.250 1.2624 0.00981 0.00448 -0.1493 0.3869 1.0000
5.500 1.2853 0.01004 0.00467 -0.1485 0.3780 1.0000
5.750 1.3076 0.01024 0.00486 -0.1476 0.3722 1.0000
6.000 1.3303 0.01043 0.00504 -0.1468 0.3663 1.0000
6.250 1.3518 0.01067 0.00527 -0.1457 0.3602 1.0000
6.500 1.3730 0.01094 0.00550 -0.1446 0.3497 1.0000
6.750 1.3899 0.01139 0.00585 -0.1428 0.3294 1.0000
7.000 1.4039 0.01200 0.00630 -0.1405 0.3007 1.0000
7.250 1.4146 0.01278 0.00690 -0.1378 0.2688 1.0000
7.500 1.4222 0.01373 0.00766 -0.1345 0.2347 1.0000
7.750 1.4299 0.01472 0.00847 -0.1315 0.2040 1.0000
8.000 1.4394 0.01564 0.00925 -0.1288 0.1786 1.0000
8.250 1.4500 0.01652 0.01003 -0.1263 0.1585 1.0000
8.500 1.4611 0.01740 0.01083 -0.1240 0.1408 1.0000
8.750 1.4730 0.01826 0.01162 -0.1219 0.1269 1.0000
9.000 1.4853 0.01912 0.01242 -0.1200 0.1164 1.0000
9.250 1.4976 0.02000 0.01326 -0.1181 0.1071 1.0000
9.500 1.5120 0.02076 0.01403 -0.1166 0.1012 1.0000
9.750 1.5236 0.02173 0.01497 -0.1147 0.0936 1.0000
10.000 1.5360 0.02268 0.01590 -0.1130 0.0860 1.0000
10.250 1.5453 0.02385 0.01702 -0.1111 0.0758 1.0000
10.500 1.5364 0.02636 0.01933 -0.1072 0.0419 1.0000
10.750 1.5367 0.02833 0.02127 -0.1046 0.0286 1.0000
11.000 1.5454 0.02971 0.02267 -0.1030 0.0254 1.0000
11.250 1.5553 0.03103 0.02402 -0.1015 0.0233 1.0000
11.500 1.5644 0.03246 0.02548 -0.1001 0.0214 1.0000
11.750 1.5734 0.03393 0.02699 -0.0988 0.0198 1.0000
12.000 1.5831 0.03536 0.02846 -0.0975 0.0186 1.0000
12.250 1.5912 0.03696 0.03009 -0.0962 0.0175 1.0000
12.500 1.5987 0.03864 0.03181 -0.0950 0.0166 1.0000
12.750 1.6075 0.04023 0.03344 -0.0938 0.0160 1.0000
13.000 1.6152 0.04197 0.03522 -0.0927 0.0153 1.0000
13.250 1.6223 0.04376 0.03706 -0.0916 0.0147 1.0000
13.500 1.6282 0.04569 0.03903 -0.0905 0.0141 1.0000
13.750 1.6328 0.04778 0.04117 -0.0894 0.0135 1.0000
14.000 1.6391 0.04974 0.04318 -0.0884 0.0131 1.0000
14.250 1.6447 0.05181 0.04531 -0.0875 0.0127 1.0000
14.500 1.6497 0.05395 0.04751 -0.0867 0.0123 1.0000
14.750 1.6540 0.05618 0.04980 -0.0858 0.0119 1.0000
15.000 1.6571 0.05860 0.05227 -0.0850 0.0116 1.0000
15.250 1.6600 0.06107 0.05479 -0.0842 0.0113 1.0000
15.500 1.6618 0.06370 0.05748 -0.0835 0.0109 1.0000
15.750 1.6620 0.06655 0.06040 -0.0828 0.0106 1.0000
16.000 1.6644 0.06916 0.06308 -0.0823 0.0105 1.0000
16.250 1.6659 0.07190 0.06589 -0.0818 0.0103 1.0000
16.500 1.6667 0.07479 0.06885 -0.0814 0.0101 1.0000
16.750 1.6676 0.07768 0.07181 -0.0811 0.0099 1.0000
17.000 1.6677 0.08071 0.07491 -0.0808 0.0097 1.0000
17.250 1.6669 0.08388 0.07816 -0.0806 0.0095 1.0000
17.500 1.6660 0.08705 0.08140 -0.0805 0.0092 1.0000
17.750 1.6646 0.09034 0.08475 -0.0804 0.0090 1.0000
18.000 1.6621 0.09382 0.08830 -0.0805 0.0088 1.0000
18.250 1.6590 0.09739 0.09195 -0.0807 0.0086 1.0000
18.500 1.6555 0.10105 0.09568 -0.0809 0.0085 1.0000
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