GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 614 AIRFOIL (goe614-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.83 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe614-il-1000000-n5.txt Download as CSV file: xf-goe614-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 614 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.4924 0.10060 0.09800 -0.0943 0.9908 0.0202
-17.000 -0.5191 0.09150 0.08875 -0.1005 0.9894 0.0203
-16.750 -0.5327 0.08468 0.08181 -0.1056 0.9879 0.0203
-16.500 -0.5426 0.07851 0.07552 -0.1106 0.9862 0.0204
-16.250 -0.5468 0.07320 0.07013 -0.1153 0.9846 0.0204
-16.000 -0.5492 0.06813 0.06496 -0.1200 0.9830 0.0204
-15.750 -0.5483 0.06345 0.06019 -0.1249 0.9816 0.0205
-15.500 -0.5576 0.05915 0.05581 -0.1274 0.9759 0.0205
-15.250 -0.5577 0.05510 0.05168 -0.1313 0.9720 0.0205
-15.000 -0.5559 0.05092 0.04740 -0.1358 0.9682 0.0206
-14.750 -0.5554 0.04733 0.04373 -0.1390 0.9606 0.0206
-14.500 -0.5446 0.04346 0.03975 -0.1445 0.9555 0.0206
-14.250 -0.5366 0.03982 0.03601 -0.1493 0.9463 0.0207
-14.000 -0.5177 0.03643 0.03252 -0.1554 0.9377 0.0208
-13.750 -0.4927 0.03313 0.02910 -0.1626 0.9260 0.0209
-13.500 -0.4592 0.03015 0.02599 -0.1707 0.9135 0.0210
-13.250 -0.4294 0.02745 0.02314 -0.1778 0.8942 0.0212
-13.000 -0.4127 0.02517 0.02068 -0.1817 0.8717 0.0213
-12.750 -0.4072 0.02329 0.01863 -0.1830 0.8512 0.0213
-12.500 -0.4087 0.02183 0.01702 -0.1820 0.8322 0.0213
-12.250 -0.4088 0.02093 0.01599 -0.1794 0.8176 0.0214
-12.000 -0.4082 0.02018 0.01516 -0.1761 0.8052 0.0215
-11.750 -0.4066 0.01965 0.01453 -0.1725 0.7941 0.0215
-11.500 -0.3992 0.01913 0.01393 -0.1697 0.7828 0.0216
-11.250 -0.3874 0.01862 0.01334 -0.1676 0.7736 0.0217
-11.000 -0.3743 0.01816 0.01280 -0.1655 0.7636 0.0219
-10.750 -0.3590 0.01770 0.01228 -0.1638 0.7550 0.0220
-10.500 -0.3436 0.01727 0.01177 -0.1620 0.7454 0.0221
-10.250 -0.3268 0.01683 0.01126 -0.1603 0.7363 0.0223
-10.000 -0.3100 0.01643 0.01078 -0.1586 0.7257 0.0224
-9.750 -0.2921 0.01600 0.01028 -0.1571 0.7164 0.0224
-9.500 -0.2735 0.01566 0.00986 -0.1556 0.7066 0.0226
-9.250 -0.2542 0.01527 0.00941 -0.1543 0.6971 0.0227
-9.000 -0.2351 0.01495 0.00900 -0.1528 0.6861 0.0228
-8.750 -0.2154 0.01460 0.00858 -0.1514 0.6749 0.0229
-8.500 -0.1952 0.01431 0.00821 -0.1501 0.6639 0.0230
-8.250 -0.1747 0.01402 0.00784 -0.1488 0.6532 0.0232
-8.000 -0.1533 0.01374 0.00750 -0.1476 0.6436 0.0233
-7.500 -0.1104 0.01324 0.00686 -0.1452 0.6227 0.0235
-7.250 -0.0892 0.01302 0.00656 -0.1440 0.6115 0.0236
-7.000 -0.0668 0.01280 0.00628 -0.1429 0.6012 0.0237
-6.750 -0.0445 0.01260 0.00601 -0.1418 0.5923 0.0238
-6.500 -0.0215 0.01240 0.00575 -0.1409 0.5833 0.0239
-6.250 0.0011 0.01223 0.00551 -0.1398 0.5751 0.0240
-6.000 0.0246 0.01206 0.00529 -0.1389 0.5666 0.0241
-5.750 0.0473 0.01192 0.00509 -0.1378 0.5577 0.0242
-5.500 0.0698 0.01164 0.00475 -0.1368 0.5500 0.0245
-5.250 0.0923 0.01149 0.00453 -0.1357 0.5414 0.0247
-5.000 0.1160 0.01130 0.00431 -0.1348 0.5351 0.0249
-4.750 0.1397 0.01116 0.00413 -0.1339 0.5284 0.0253
-4.250 0.1873 0.01093 0.00382 -0.1322 0.5165 0.0259
-4.000 0.2113 0.01083 0.00369 -0.1313 0.5103 0.0262
-3.500 0.2587 0.01067 0.00345 -0.1294 0.4985 0.0268
-3.250 0.2826 0.01060 0.00335 -0.1286 0.4929 0.0270
-3.000 0.3048 0.01055 0.00325 -0.1273 0.4865 0.0274
-2.750 0.3278 0.01049 0.00316 -0.1262 0.4815 0.0277
-2.500 0.3501 0.01044 0.00308 -0.1250 0.4746 0.0279
-2.250 0.3715 0.01041 0.00301 -0.1236 0.4683 0.0284
-2.000 0.3945 0.01035 0.00293 -0.1225 0.4635 0.0291
-1.750 0.4177 0.01031 0.00287 -0.1215 0.4583 0.0298
-1.500 0.4401 0.01031 0.00283 -0.1203 0.4524 0.0308
-1.250 0.4622 0.01032 0.00281 -0.1191 0.4454 0.0320
-1.000 0.4851 0.01030 0.00277 -0.1180 0.4397 0.0348
-0.750 0.5045 0.01013 0.00272 -0.1164 0.4324 0.0832
-0.500 0.5273 0.01010 0.00273 -0.1153 0.4278 0.1003
-0.250 0.5505 0.01011 0.00274 -0.1144 0.4225 0.1085
0.000 0.5731 0.01014 0.00278 -0.1133 0.4178 0.1185
0.250 0.5940 0.01007 0.00282 -0.1120 0.4132 0.1593
0.500 0.6168 0.01005 0.00289 -0.1110 0.4095 0.1896
0.750 0.6395 0.01010 0.00296 -0.1100 0.4041 0.2035
1.000 0.6613 0.01019 0.00305 -0.1088 0.3986 0.2127
1.250 0.6835 0.01028 0.00313 -0.1077 0.3939 0.2209
1.500 0.7065 0.01034 0.00321 -0.1067 0.3892 0.2312
1.750 0.7278 0.01045 0.00332 -0.1055 0.3823 0.2422
2.000 0.7486 0.01056 0.00343 -0.1041 0.3770 0.2554
2.250 0.7710 0.01064 0.00353 -0.1031 0.3724 0.2660
2.500 0.7929 0.01072 0.00364 -0.1020 0.3680 0.2817
2.750 0.8128 0.01083 0.00379 -0.1006 0.3620 0.3071
3.000 0.8342 0.01093 0.00392 -0.0994 0.3571 0.3258
3.250 0.8550 0.01102 0.00407 -0.0982 0.3521 0.3496
3.500 0.8734 0.01120 0.00426 -0.0965 0.3443 0.3728
3.750 0.8939 0.01134 0.00442 -0.0953 0.3375 0.3909
4.000 0.9128 0.01152 0.00462 -0.0937 0.3306 0.4120
4.250 0.9314 0.01170 0.00484 -0.0922 0.3233 0.4363
4.500 0.9500 0.01190 0.00505 -0.0906 0.3162 0.4584
4.750 0.9670 0.01216 0.00532 -0.0888 0.3059 0.4794
5.000 0.9839 0.01243 0.00559 -0.0870 0.2980 0.4987
5.250 0.9981 0.01278 0.00593 -0.0848 0.2848 0.5250
5.500 1.0117 0.01316 0.00631 -0.0826 0.2716 0.5510
5.750 1.0247 0.01346 0.00671 -0.0803 0.2625 0.6032
6.000 1.0349 0.01382 0.00718 -0.0775 0.2503 0.6660
6.500 1.1575 0.01464 0.00850 -0.0936 0.2225 1.0000
6.750 1.1737 0.01516 0.00898 -0.0921 0.2153 1.0000
7.000 1.1905 0.01566 0.00946 -0.0908 0.2091 1.0000
7.250 1.2070 0.01620 0.00996 -0.0894 0.2038 1.0000
7.500 1.2238 0.01673 0.01047 -0.0881 0.1987 1.0000
7.750 1.2396 0.01733 0.01104 -0.0868 0.1924 1.0000
8.000 1.2541 0.01802 0.01169 -0.0853 0.1865 1.0000
8.250 1.2680 0.01875 0.01239 -0.0839 0.1774 1.0000
8.500 1.2626 0.02060 0.01404 -0.0803 0.1410 1.0000
8.750 1.2580 0.02255 0.01587 -0.0770 0.1158 1.0000
9.000 1.2719 0.02341 0.01674 -0.0759 0.1139 1.0000
9.250 1.2841 0.02441 0.01774 -0.0747 0.1111 1.0000
9.500 1.2980 0.02532 0.01867 -0.0736 0.1099 1.0000
9.750 1.3108 0.02634 0.01970 -0.0726 0.1084 1.0000
10.000 1.3238 0.02737 0.02074 -0.0716 0.1070 1.0000
10.250 1.3364 0.02845 0.02184 -0.0706 0.1058 1.0000
10.500 1.3490 0.02953 0.02295 -0.0697 0.1046 1.0000
10.750 1.3616 0.03065 0.02411 -0.0688 0.1043 1.0000
11.000 1.3735 0.03184 0.02533 -0.0680 0.1034 1.0000
11.250 1.3839 0.03319 0.02671 -0.0671 0.1024 1.0000
11.500 1.3952 0.03449 0.02804 -0.0663 0.1020 1.0000
11.750 1.4048 0.03594 0.02953 -0.0655 0.1014 1.0000
12.000 1.4131 0.03753 0.03115 -0.0646 0.1004 1.0000
12.250 1.4233 0.03899 0.03266 -0.0639 0.1003 1.0000
12.500 1.4285 0.04093 0.03463 -0.0631 0.0988 1.0000
12.750 1.4368 0.04261 0.03636 -0.0624 0.0984 1.0000
13.000 1.4432 0.04449 0.03827 -0.0617 0.0977 1.0000
13.250 1.4477 0.04659 0.04042 -0.0610 0.0965 1.0000
13.500 1.4523 0.04871 0.04258 -0.0604 0.0954 1.0000
13.750 1.4567 0.05088 0.04481 -0.0598 0.0948 1.0000
14.000 1.4614 0.05307 0.04706 -0.0593 0.0946 1.0000
14.250 1.4666 0.05518 0.04923 -0.0589 0.0941 1.0000
14.500 1.4722 0.05730 0.05140 -0.0585 0.0938 1.0000
14.750 1.4782 0.05937 0.05353 -0.0582 0.0935 1.0000
15.000 1.4831 0.06159 0.05581 -0.0579 0.0931 1.0000
15.250 1.4872 0.06391 0.05819 -0.0576 0.0926 1.0000
15.500 1.4914 0.06623 0.06056 -0.0574 0.0922 1.0000
15.750 1.4944 0.06868 0.06307 -0.0571 0.0914 1.0000
16.000 1.4970 0.07119 0.06563 -0.0570 0.0899 1.0000
16.250 1.4969 0.07404 0.06854 -0.0568 0.0887 1.0000
16.500 1.4989 0.07664 0.07119 -0.0567 0.0879 1.0000
16.750 1.4959 0.07989 0.07448 -0.0566 0.0862 1.0000
17.000 1.4950 0.08284 0.07748 -0.0565 0.0847 1.0000
17.250 1.4947 0.08579 0.08049 -0.0566 0.0839 1.0000
17.500 1.4984 0.08822 0.08298 -0.0566 0.0828 1.0000
17.750 1.4983 0.09117 0.08597 -0.0568 0.0794 1.0000
18.000 1.4861 0.09560 0.09033 -0.0570 0.0653 1.0000
18.250 1.4516 0.10296 0.09762 -0.0575 0.0485 1.0000
18.500 1.4226 0.10981 0.10449 -0.0583 0.0368 1.0000
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