GOE 679 AIRFOIL (goe679-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 679 AIRFOIL (goe679-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.83 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe679-il-1000000-n5.txt Download as CSV file: xf-goe679-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 679 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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.7687 0.08510 0.08160 -0.0936 0.9927 0.0267
-17.500 -0.7780 0.08029 0.07673 -0.0964 0.9919 0.0268
-17.250 -0.7877 0.07560 0.07197 -0.0990 0.9907 0.0268
-17.000 -0.8042 0.07010 0.06639 -0.1025 0.9895 0.0268
-16.750 -0.8225 0.06418 0.06038 -0.1064 0.9882 0.0269
-16.500 -0.8474 0.05745 0.05354 -0.1110 0.9868 0.0269
-16.250 -0.8714 0.05049 0.04645 -0.1161 0.9854 0.0269
-16.000 -0.8907 0.04336 0.03916 -0.1222 0.9840 0.0269
-15.750 -0.8992 0.03697 0.03261 -0.1289 0.9828 0.0269
-15.500 -0.8986 0.03242 0.02791 -0.1341 0.9818 0.0270
-15.250 -0.8960 0.02859 0.02395 -0.1387 0.9808 0.0272
-15.000 -0.9088 0.02660 0.02187 -0.1362 0.9758 0.0272
-14.750 -0.9033 0.02477 0.01996 -0.1364 0.9730 0.0274
-14.500 -0.8907 0.02343 0.01855 -0.1367 0.9712 0.0276
-14.250 -0.8737 0.02235 0.01743 -0.1369 0.9698 0.0279
-14.000 -0.8532 0.02140 0.01642 -0.1374 0.9688 0.0280
-13.750 -0.8559 0.02079 0.01576 -0.1328 0.9632 0.0281
-13.500 -0.8422 0.02011 0.01503 -0.1312 0.9600 0.0283
-13.250 -0.8237 0.01945 0.01433 -0.1303 0.9579 0.0285
-13.000 -0.8029 0.01882 0.01366 -0.1297 0.9564 0.0286
-12.750 -0.7792 0.01822 0.01302 -0.1295 0.9553 0.0289
-12.500 -0.7795 0.01784 0.01261 -0.1243 0.9479 0.0290
-12.250 -0.7588 0.01727 0.01199 -0.1234 0.9448 0.0292
-12.000 -0.7329 0.01671 0.01140 -0.1234 0.9426 0.0294
-11.750 -0.7041 0.01617 0.01082 -0.1239 0.9410 0.0296
-11.500 -0.7004 0.01587 0.01048 -0.1192 0.9321 0.0298
-11.250 -0.6743 0.01540 0.00998 -0.1191 0.9283 0.0300
-11.000 -0.6407 0.01492 0.00945 -0.1204 0.9258 0.0303
-10.750 -0.6261 0.01459 0.00909 -0.1178 0.9155 0.0304
-10.500 -0.5864 0.01411 0.00856 -0.1203 0.9085 0.0306
-10.250 -0.5382 0.01350 0.00788 -0.1247 0.8897 0.0312
-10.000 -0.4707 0.01299 0.00720 -0.1332 0.8547 0.0318
-9.750 -0.4451 0.01282 0.00685 -0.1328 0.8227 0.0322
-9.250 -0.4076 0.01248 0.00634 -0.1290 0.7909 0.0329
-9.000 -0.3885 0.01231 0.00611 -0.1271 0.7797 0.0334
-8.750 -0.3690 0.01215 0.00588 -0.1254 0.7683 0.0337
-8.500 -0.3491 0.01199 0.00567 -0.1236 0.7589 0.0342
-8.250 -0.3283 0.01182 0.00545 -0.1221 0.7505 0.0347
-7.750 -0.2878 0.01145 0.00501 -0.1188 0.7339 0.0363
-7.500 -0.2676 0.01129 0.00481 -0.1170 0.7249 0.0372
-7.250 -0.2465 0.01114 0.00462 -0.1155 0.7173 0.0381
-7.000 -0.2249 0.01099 0.00444 -0.1141 0.7095 0.0391
-6.750 -0.2051 0.01084 0.00425 -0.1122 0.7014 0.0406
-6.500 -0.1833 0.01068 0.00408 -0.1108 0.6937 0.0426
-6.250 -0.1646 0.01053 0.00390 -0.1088 0.6836 0.0453
-6.000 -0.1448 0.01036 0.00372 -0.1069 0.6756 0.0490
-5.750 -0.1253 0.01019 0.00355 -0.1050 0.6666 0.0542
-5.500 -0.1067 0.01000 0.00336 -0.1030 0.6579 0.0627
-5.250 -0.0875 0.00981 0.00319 -0.1010 0.6468 0.0733
-5.000 -0.0685 0.00965 0.00305 -0.0990 0.6351 0.0846
-4.750 -0.0496 0.00956 0.00293 -0.0970 0.6213 0.0934
-4.500 -0.0294 0.00948 0.00284 -0.0952 0.6060 0.1015
-4.250 -0.0091 0.00942 0.00275 -0.0935 0.5909 0.1079
-4.000 0.0109 0.00941 0.00269 -0.0916 0.5739 0.1143
-3.750 0.0308 0.00940 0.00263 -0.0898 0.5560 0.1198
-3.500 0.0512 0.00944 0.00259 -0.0880 0.5390 0.1238
-3.250 0.0713 0.00945 0.00256 -0.0863 0.5233 0.1289
-3.000 0.0931 0.00945 0.00253 -0.0848 0.5101 0.1336
-2.750 0.1147 0.00946 0.00251 -0.0833 0.4979 0.1392
-2.250 0.1586 0.00949 0.00248 -0.0806 0.4758 0.1518
-1.750 0.2035 0.00954 0.00248 -0.0779 0.4569 0.1624
-1.500 0.2256 0.00957 0.00249 -0.0766 0.4481 0.1679
-1.250 0.2485 0.00958 0.00250 -0.0754 0.4410 0.1734
-0.750 0.2926 0.00967 0.00255 -0.0727 0.4238 0.1859
-0.500 0.3152 0.00970 0.00257 -0.0714 0.4163 0.1928
-0.250 0.3368 0.00976 0.00261 -0.0700 0.4086 0.1991
0.000 0.3592 0.00979 0.00265 -0.0687 0.4030 0.2063
0.250 0.3824 0.00982 0.00268 -0.0676 0.3980 0.2129
0.500 0.4042 0.00986 0.00273 -0.0663 0.3920 0.2234
1.000 0.4493 0.00995 0.00283 -0.0638 0.3820 0.2407
1.500 0.4933 0.01006 0.00296 -0.0612 0.3713 0.2607
1.750 0.5150 0.01013 0.00303 -0.0598 0.3659 0.2706
2.000 0.5372 0.01017 0.00310 -0.0586 0.3617 0.2817
2.250 0.5591 0.01023 0.00317 -0.0573 0.3569 0.2927
2.500 0.5796 0.01033 0.00327 -0.0557 0.3508 0.3046
2.750 0.6016 0.01038 0.00335 -0.0545 0.3468 0.3183
3.000 0.6234 0.01044 0.00344 -0.0532 0.3412 0.3327
3.250 0.6438 0.01051 0.00355 -0.0517 0.3358 0.3538
3.500 0.6634 0.01060 0.00367 -0.0500 0.3308 0.3762
3.750 0.6836 0.01062 0.00379 -0.0485 0.3260 0.4092
4.000 0.7028 0.01065 0.00392 -0.0468 0.3207 0.4510
4.250 0.7200 0.01071 0.00408 -0.0447 0.3139 0.5055
4.500 0.7371 0.01061 0.00424 -0.0426 0.3097 0.5941
4.750 0.7521 0.01055 0.00441 -0.0400 0.3042 0.6824
5.000 0.7615 0.01039 0.00464 -0.0362 0.2988 0.8118
5.500 0.9815 0.01114 0.00556 -0.0721 0.2748 0.9981
5.750 1.0171 0.01145 0.00581 -0.0740 0.2671 1.0000
6.000 1.0331 0.01169 0.00601 -0.0718 0.2603 1.0000
6.250 1.0504 0.01193 0.00621 -0.0698 0.2539 1.0000
6.500 1.0666 0.01223 0.00646 -0.0677 0.2465 1.0000
6.750 1.0851 0.01245 0.00667 -0.0660 0.2426 1.0000
7.000 1.1019 0.01276 0.00694 -0.0641 0.2358 1.0000
7.250 1.1192 0.01307 0.00722 -0.0623 0.2306 1.0000
7.500 1.1382 0.01334 0.00747 -0.0609 0.2264 1.0000
7.750 1.1561 0.01365 0.00777 -0.0593 0.2219 1.0000
8.000 1.1725 0.01404 0.00812 -0.0575 0.2165 1.0000
8.250 1.1913 0.01434 0.00842 -0.0561 0.2132 1.0000
8.500 1.2103 0.01465 0.00873 -0.0547 0.2104 1.0000
8.750 1.2273 0.01505 0.00910 -0.0532 0.2060 1.0000
9.000 1.2439 0.01548 0.00952 -0.0516 0.2020 1.0000
9.250 1.2623 0.01585 0.00989 -0.0502 0.1994 1.0000
9.500 1.2803 0.01623 0.01028 -0.0489 0.1970 1.0000
9.750 1.2981 0.01664 0.01069 -0.0476 0.1945 1.0000
10.000 1.3151 0.01710 0.01115 -0.0462 0.1915 1.0000
10.250 1.3309 0.01763 0.01167 -0.0448 0.1887 1.0000
10.500 1.3471 0.01815 0.01220 -0.0434 0.1858 1.0000
10.750 1.3645 0.01863 0.01270 -0.0422 0.1837 1.0000
11.000 1.3812 0.01915 0.01324 -0.0410 0.1817 1.0000
11.250 1.3975 0.01971 0.01381 -0.0397 0.1795 1.0000
11.500 1.4127 0.02034 0.01446 -0.0384 0.1773 1.0000
11.750 1.4273 0.02103 0.01515 -0.0371 0.1748 1.0000
12.000 1.4408 0.02180 0.01593 -0.0358 0.1721 1.0000
12.250 1.4570 0.02243 0.01659 -0.0348 0.1706 1.0000
12.500 1.4719 0.02315 0.01734 -0.0336 0.1686 1.0000
12.750 1.4862 0.02392 0.01813 -0.0325 0.1663 1.0000
13.000 1.4986 0.02484 0.01906 -0.0313 0.1635 1.0000
13.250 1.5106 0.02581 0.02004 -0.0301 0.1609 1.0000
13.500 1.5223 0.02682 0.02107 -0.0290 0.1586 1.0000
13.750 1.5362 0.02770 0.02199 -0.0281 0.1571 1.0000
14.000 1.5485 0.02870 0.02303 -0.0271 0.1552 1.0000
14.250 1.5602 0.02976 0.02412 -0.0261 0.1530 1.0000
14.500 1.5704 0.03096 0.02535 -0.0251 0.1510 1.0000
14.750 1.5792 0.03229 0.02669 -0.0241 0.1485 1.0000
15.000 1.5877 0.03368 0.02812 -0.0231 0.1464 1.0000
15.250 1.5986 0.03488 0.02936 -0.0223 0.1448 1.0000
15.500 1.6074 0.03628 0.03081 -0.0215 0.1427 1.0000
15.750 1.6142 0.03786 0.03242 -0.0206 0.1394 1.0000
16.000 1.6157 0.03995 0.03450 -0.0196 0.1349 1.0000
16.250 1.6226 0.04161 0.03622 -0.0189 0.1325 1.0000
16.500 1.6279 0.04343 0.03807 -0.0183 0.1291 1.0000
16.750 1.6278 0.04579 0.04045 -0.0175 0.1252 1.0000
17.000 1.6281 0.04817 0.04286 -0.0169 0.1208 1.0000
17.250 1.6264 0.05080 0.04552 -0.0163 0.1161 1.0000
17.500 1.6240 0.05357 0.04831 -0.0159 0.1123 1.0000
17.750 1.6173 0.05682 0.05159 -0.0155 0.1063 1.0000
18.000 1.6088 0.06035 0.05515 -0.0153 0.1013 1.0000
18.250 1.5976 0.06427 0.05910 -0.0152 0.0962 1.0000
18.500 1.5872 0.06817 0.06304 -0.0153 0.0922 1.0000
18.750 1.5786 0.07193 0.06686 -0.0155 0.0896 1.0000
19.000 1.5684 0.07595 0.07093 -0.0159 0.0873 1.0000
19.250 1.5577 0.08010 0.07514 -0.0163 0.0849 1.0000
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