GOE 368 AIRFOIL (goe368-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 368 AIRFOIL (goe368-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.59 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe368-il-1000000.txt Download as CSV file: xf-goe368-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 368 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4109 0.08179 0.08031 -0.0100 1.0000 0.0094
-7.500 -0.4134 0.07847 0.07703 -0.0108 1.0000 0.0094
-7.250 -0.4109 0.07431 0.07289 -0.0138 1.0000 0.0094
-7.000 -0.4183 0.06611 0.06471 -0.0206 1.0000 0.0098
-6.750 -0.4107 0.06131 0.05989 -0.0247 1.0000 0.0100
-6.500 -0.3989 0.05740 0.05597 -0.0278 1.0000 0.0102
-6.250 -0.3856 0.05295 0.05148 -0.0311 1.0000 0.0104
-6.000 -0.3712 0.04696 0.04541 -0.0351 1.0000 0.0105
-5.250 -0.2750 0.01674 0.01318 -0.0551 0.9865 0.0082
-5.000 -0.2409 0.01416 0.01020 -0.0566 0.9796 0.0084
-4.500 -0.1652 0.01221 0.00784 -0.0605 0.9463 0.0095
-4.250 -0.1333 0.01049 0.00572 -0.0612 0.8747 0.0099
-4.000 -0.1098 0.00988 0.00481 -0.0600 0.8265 0.0104
-3.750 -0.0843 0.00960 0.00438 -0.0593 0.7994 0.0113
-3.250 -0.0323 0.00892 0.00338 -0.0580 0.7386 0.0130
-3.000 -0.0066 0.00876 0.00299 -0.0572 0.6916 0.0139
-2.750 0.0194 0.00850 0.00249 -0.0566 0.6553 0.0149
-2.500 0.0461 0.00818 0.00199 -0.0561 0.6339 0.0173
-2.250 0.0732 0.00802 0.00174 -0.0557 0.6193 0.0204
-2.000 0.1005 0.00782 0.00145 -0.0553 0.6059 0.0282
-1.750 0.1268 0.00740 0.00128 -0.0550 0.5926 0.1116
-1.500 0.1543 0.00743 0.00125 -0.0548 0.5769 0.1213
-1.250 0.1818 0.00744 0.00123 -0.0545 0.5583 0.1287
-1.000 0.2093 0.00750 0.00118 -0.0542 0.5341 0.1322
-0.750 0.2363 0.00753 0.00112 -0.0539 0.5021 0.1386
-0.500 0.2631 0.00767 0.00112 -0.0536 0.4641 0.1442
-0.250 0.2901 0.00777 0.00109 -0.0533 0.4362 0.1470
0.000 0.3172 0.00782 0.00108 -0.0530 0.4164 0.1525
0.250 0.3445 0.00788 0.00109 -0.0528 0.4002 0.1577
0.500 0.3719 0.00793 0.00109 -0.0525 0.3860 0.1644
0.750 0.3993 0.00799 0.00112 -0.0523 0.3728 0.1717
1.000 0.4267 0.00804 0.00114 -0.0521 0.3597 0.1794
1.250 0.4541 0.00812 0.00118 -0.0519 0.3459 0.1866
1.500 0.4814 0.00818 0.00122 -0.0517 0.3324 0.1940
1.750 0.5087 0.00827 0.00126 -0.0515 0.3188 0.2006
2.000 0.5360 0.00835 0.00131 -0.0513 0.3054 0.2079
2.250 0.5632 0.00844 0.00137 -0.0510 0.2915 0.2148
2.500 0.5903 0.00853 0.00144 -0.0508 0.2775 0.2233
2.750 0.6174 0.00864 0.00153 -0.0506 0.2632 0.2326
3.000 0.6443 0.00875 0.00163 -0.0504 0.2489 0.2458
3.250 0.6711 0.00884 0.00174 -0.0502 0.2354 0.2728
3.500 0.7008 0.00745 0.00197 -0.0510 0.2202 1.0000
3.750 0.7270 0.00767 0.00211 -0.0507 0.2044 1.0000
4.000 0.7534 0.00787 0.00224 -0.0503 0.1942 1.0000
4.250 0.7800 0.00805 0.00237 -0.0500 0.1857 1.0000
4.500 0.8064 0.00824 0.00251 -0.0497 0.1759 1.0000
4.750 0.8326 0.00846 0.00268 -0.0494 0.1650 1.0000
5.000 0.8587 0.00871 0.00284 -0.0490 0.1497 1.0000
5.250 0.8786 0.00992 0.00351 -0.0480 0.0578 1.0000
5.500 0.9017 0.01071 0.00415 -0.0472 0.0149 1.0000
5.750 0.9276 0.01102 0.00455 -0.0467 0.0125 1.0000
6.000 0.9532 0.01136 0.00495 -0.0463 0.0118 1.0000
6.250 0.9785 0.01174 0.00539 -0.0458 0.0109 1.0000
6.500 1.0034 0.01219 0.00588 -0.0452 0.0097 1.0000
6.750 1.0278 0.01271 0.00647 -0.0446 0.0090 1.0000
7.000 1.0512 0.01339 0.00724 -0.0439 0.0084 1.0000
7.250 1.0711 0.01462 0.00863 -0.0427 0.0077 1.0000
7.500 1.0917 0.01561 0.00974 -0.0416 0.0074 1.0000
7.750 1.1154 0.01613 0.01031 -0.0409 0.0070 1.0000
8.000 1.1361 0.01703 0.01129 -0.0399 0.0068 1.0000
8.250 1.1563 0.01794 0.01228 -0.0388 0.0065 1.0000
8.500 1.1769 0.01873 0.01314 -0.0378 0.0060 1.0000
8.750 1.1956 0.01973 0.01421 -0.0366 0.0058 1.0000
9.000 1.2120 0.02095 0.01551 -0.0351 0.0057 1.0000
9.250 1.2279 0.02220 0.01683 -0.0336 0.0056 1.0000
9.500 1.2436 0.02340 0.01808 -0.0322 0.0054 1.0000
9.750 1.2582 0.02467 0.01942 -0.0307 0.0052 1.0000
10.000 1.2712 0.02608 0.02087 -0.0291 0.0050 1.0000
10.250 1.2816 0.02792 0.02276 -0.0272 0.0049 1.0000
10.500 1.2919 0.03185 0.02673 -0.0256 0.0046 1.0000
10.750 1.3066 0.03451 0.02951 -0.0244 0.0046 1.0000
11.000 1.3189 0.03645 0.03157 -0.0229 0.0047 1.0000
11.250 1.3257 0.03740 0.03267 -0.0206 0.0048 1.0000
13.000 1.2582 0.06102 0.05772 -0.0126 0.0056 1.0000
13.250 1.2479 0.06548 0.06231 -0.0147 0.0055 1.0000
13.500 1.2364 0.07045 0.06741 -0.0173 0.0055 1.0000
13.750 1.2201 0.07662 0.07374 -0.0208 0.0055 1.0000
14.000 1.2086 0.08224 0.07947 -0.0243 0.0055 1.0000
14.250 1.1920 0.08919 0.08656 -0.0286 0.0055 1.0000
14.500 1.1748 0.09669 0.09421 -0.0335 0.0055 1.0000
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Polar data table (+)
Polar graphs
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