GOE 626 AIRFOIL (goe626-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 626 AIRFOIL (goe626-il) Reynolds number: 200,000 Max Cl/Cd: 71.23 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe626-il-200000.txt Download as CSV file: xf-goe626-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 626 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6644 0.07045 0.06576 -0.0806 1.0000 0.0553
-13.250 -0.7150 0.06285 0.05795 -0.0841 1.0000 0.0548
-13.000 -0.7448 0.05845 0.05345 -0.0847 1.0000 0.0546
-12.750 -0.7704 0.05506 0.04998 -0.0843 1.0000 0.0546
-12.500 -0.7960 0.05218 0.04703 -0.0830 1.0000 0.0545
-12.250 -0.8246 0.04959 0.04439 -0.0811 1.0000 0.0544
-12.000 -0.8602 0.04709 0.04183 -0.0784 1.0000 0.0542
-11.750 -0.8749 0.04425 0.03890 -0.0787 1.0000 0.0544
-11.500 -0.8785 0.04155 0.03610 -0.0798 1.0000 0.0547
-11.250 -0.8734 0.03920 0.03362 -0.0810 0.9997 0.0550
-11.000 -0.8435 0.03705 0.03134 -0.0853 0.9957 0.0558
-10.750 -0.8119 0.03514 0.02927 -0.0894 0.9918 0.0569
-10.500 -0.7843 0.03342 0.02739 -0.0922 0.9871 0.0579
-10.250 -0.7533 0.03202 0.02589 -0.0947 0.9831 0.0589
-10.000 -0.7189 0.03096 0.02490 -0.0974 0.9800 0.0601
-9.750 -0.6935 0.02982 0.02375 -0.0985 0.9740 0.0613
-9.500 -0.6589 0.02869 0.02257 -0.1013 0.9697 0.0629
-9.250 -0.6196 0.02761 0.02139 -0.1048 0.9668 0.0648
-9.000 -0.5967 0.02655 0.02034 -0.1052 0.9599 0.0665
-8.750 -0.5605 0.02548 0.01925 -0.1082 0.9555 0.0696
-8.500 -0.5192 0.02441 0.01813 -0.1119 0.9526 0.0740
-8.250 -0.4941 0.02339 0.01711 -0.1125 0.9451 0.0787
-8.000 -0.4577 0.02210 0.01581 -0.1154 0.9405 0.0885
-7.750 -0.4165 0.02036 0.01417 -0.1197 0.9375 0.1144
-7.500 -0.3893 0.01932 0.01324 -0.1206 0.9300 0.1435
-7.250 -0.3513 0.01877 0.01277 -0.1228 0.9248 0.1719
-7.000 -0.3061 0.01865 0.01270 -0.1258 0.9215 0.1945
-6.750 -0.2709 0.01879 0.01282 -0.1267 0.9148 0.2093
-6.500 -0.2322 0.01886 0.01279 -0.1282 0.9085 0.2217
-6.250 -0.1852 0.01912 0.01305 -0.1309 0.9053 0.2306
-6.000 -0.1358 0.01924 0.01313 -0.1342 0.9033 0.2393
-5.750 -0.1068 0.01959 0.01350 -0.1336 0.8941 0.2451
-5.500 -0.0641 0.01948 0.01326 -0.1359 0.8895 0.2536
-5.250 -0.0184 0.01990 0.01381 -0.1381 0.8861 0.2588
-5.000 0.0130 0.01990 0.01373 -0.1382 0.8770 0.2655
-4.750 0.0509 0.01963 0.01337 -0.1396 0.8701 0.2713
-4.500 0.0902 0.01988 0.01372 -0.1407 0.8634 0.2760
-4.250 0.1203 0.01991 0.01370 -0.1405 0.8518 0.2826
-4.000 0.1524 0.01956 0.01322 -0.1410 0.8411 0.2889
-3.750 0.1862 0.01960 0.01332 -0.1413 0.8302 0.2928
-3.500 0.2139 0.01959 0.01329 -0.1407 0.8157 0.2978
-3.250 0.2443 0.01928 0.01268 -0.1411 0.8020 0.3053
-3.000 0.2743 0.01900 0.01244 -0.1410 0.7886 0.3092
-2.750 0.3020 0.01895 0.01238 -0.1405 0.7733 0.3129
-2.500 0.3287 0.01873 0.01205 -0.1400 0.7574 0.3173
-2.250 0.3565 0.01840 0.01148 -0.1400 0.7419 0.3221
-2.000 0.3840 0.01792 0.01081 -0.1399 0.7269 0.3249
-1.750 0.4113 0.01761 0.01042 -0.1396 0.7127 0.3274
-1.500 0.4385 0.01749 0.01022 -0.1392 0.6988 0.3303
-1.250 0.4648 0.01736 0.01000 -0.1387 0.6848 0.3333
-1.000 0.4919 0.01720 0.00969 -0.1385 0.6718 0.3361
-0.750 0.5203 0.01709 0.00936 -0.1384 0.6597 0.3390
-0.500 0.5466 0.01708 0.00918 -0.1380 0.6469 0.3421
-0.250 0.5735 0.01686 0.00886 -0.1378 0.6358 0.3445
0.000 0.6003 0.01679 0.00871 -0.1374 0.6248 0.3467
0.250 0.6264 0.01677 0.00865 -0.1370 0.6138 0.3490
0.500 0.6540 0.01682 0.00859 -0.1368 0.6036 0.3517
0.750 0.6791 0.01683 0.00858 -0.1361 0.5927 0.3548
1.000 0.7073 0.01691 0.00848 -0.1360 0.5831 0.3576
1.250 0.7317 0.01689 0.00844 -0.1352 0.5723 0.3598
1.750 0.7832 0.01682 0.00827 -0.1341 0.5529 0.3642
2.000 0.8102 0.01687 0.00824 -0.1338 0.5444 0.3671
2.250 0.8339 0.01688 0.00830 -0.1329 0.5347 0.3702
2.500 0.8604 0.01694 0.00829 -0.1324 0.5267 0.3733
2.750 0.8854 0.01700 0.00835 -0.1317 0.5183 0.3761
3.000 0.9110 0.01707 0.00836 -0.1312 0.5104 0.3788
3.250 0.9373 0.01718 0.00841 -0.1307 0.5031 0.3814
3.500 0.9613 0.01715 0.00845 -0.1299 0.4948 0.3844
3.750 0.9879 0.01727 0.00851 -0.1295 0.4879 0.3879
4.000 1.0115 0.01737 0.00869 -0.1286 0.4804 0.3920
4.250 1.0367 0.01750 0.00880 -0.1280 0.4737 0.3964
4.500 1.0640 0.01772 0.00894 -0.1278 0.4678 0.4003
4.750 1.0866 0.01776 0.00912 -0.1267 0.4605 0.4042
5.000 1.1111 0.01788 0.00923 -0.1259 0.4533 0.4088
5.250 1.1349 0.01805 0.00943 -0.1251 0.4460 0.4140
5.500 1.1573 0.01818 0.00958 -0.1240 0.4382 0.4193
5.750 1.1821 0.01834 0.00974 -0.1233 0.4310 0.4254
6.000 1.2022 0.01845 0.00998 -0.1218 0.4232 0.4327
6.250 1.2253 0.01862 0.01014 -0.1208 0.4159 0.4413
6.500 1.2470 0.01880 0.01042 -0.1197 0.4090 0.4513
6.750 1.2675 0.01894 0.01067 -0.1183 0.4018 0.4630
7.250 1.3089 0.01927 0.01124 -0.1156 0.3882 0.5033
7.500 1.3287 0.01931 0.01151 -0.1142 0.3809 0.5643
7.750 1.3499 0.01895 0.01178 -0.1128 0.3738 1.0000
8.000 1.3665 0.01922 0.01207 -0.1107 0.3660 1.0000
8.250 1.3852 0.01958 0.01231 -0.1091 0.3589 1.0000
8.500 1.3973 0.01986 0.01269 -0.1063 0.3509 1.0000
8.750 1.4113 0.02022 0.01299 -0.1038 0.3428 1.0000
9.000 1.4229 0.02059 0.01342 -0.1011 0.3336 1.0000
9.250 1.4351 0.02104 0.01382 -0.0985 0.3250 1.0000
9.500 1.4468 0.02149 0.01435 -0.0960 0.3152 1.0000
9.750 1.4570 0.02207 0.01486 -0.0933 0.3061 1.0000
10.000 1.4668 0.02265 0.01551 -0.0907 0.2949 1.0000
10.250 1.4755 0.02335 0.01621 -0.0881 0.2839 1.0000
10.500 1.4818 0.02420 0.01701 -0.0853 0.2729 1.0000
10.750 1.4901 0.02506 0.01790 -0.0829 0.2611 1.0000
11.000 1.4974 0.02604 0.01888 -0.0805 0.2508 1.0000
11.250 1.5022 0.02720 0.01999 -0.0780 0.2413 1.0000
11.500 1.5094 0.02832 0.02115 -0.0760 0.2313 1.0000
11.750 1.5135 0.02968 0.02248 -0.0737 0.2227 1.0000
12.000 1.5190 0.03104 0.02386 -0.0718 0.2144 1.0000
12.250 1.5225 0.03259 0.02539 -0.0698 0.2075 1.0000
12.500 1.5273 0.03413 0.02698 -0.0681 0.2003 1.0000
12.750 1.5276 0.03605 0.02887 -0.0662 0.1939 1.0000
13.000 1.5320 0.03778 0.03068 -0.0648 0.1871 1.0000
13.250 1.5305 0.04004 0.03291 -0.0633 0.1806 1.0000
13.500 1.5323 0.04215 0.03510 -0.0621 0.1740 1.0000
13.750 1.5299 0.04473 0.03768 -0.0610 0.1673 1.0000
14.000 1.5284 0.04737 0.04039 -0.0601 0.1605 1.0000
14.250 1.5241 0.05040 0.04345 -0.0595 0.1532 1.0000
14.500 1.5201 0.05356 0.04668 -0.0590 0.1455 1.0000
14.750 1.5133 0.05715 0.05027 -0.0588 0.1381 1.0000
15.000 1.5094 0.06059 0.05381 -0.0588 0.1300 1.0000
15.250 1.5013 0.06455 0.05774 -0.0590 0.1238 1.0000
15.500 1.4999 0.06785 0.06114 -0.0591 0.1177 1.0000
15.750 1.4951 0.07160 0.06491 -0.0595 0.1133 1.0000
16.000 1.4933 0.07501 0.06833 -0.0598 0.1099 1.0000
16.250 1.4935 0.07821 0.07162 -0.0602 0.1065 1.0000
16.500 1.4928 0.08158 0.07502 -0.0606 0.1038 1.0000
16.750 1.4920 0.08496 0.07838 -0.0612 0.1015 1.0000
17.000 1.4942 0.08792 0.08137 -0.0615 0.0996 1.0000
17.250 1.4973 0.09082 0.08437 -0.0620 0.0977 1.0000
17.500 1.4996 0.09388 0.08750 -0.0626 0.0958 1.0000
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