GOE 508 AIRFOIL (goe508-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 508 AIRFOIL (goe508-il) Reynolds number: 200,000 Max Cl/Cd: 71.34 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe508-il-200000.txt Download as CSV file: xf-goe508-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 508 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
------ -------- --------- --------- -------- -------- --------
-10.750 0.0096 0.09943 0.09557 -0.1063 0.9366 0.0769
-10.500 0.0274 0.09614 0.09225 -0.1100 0.9272 0.0790
-10.250 0.0077 0.09052 0.08659 -0.1219 0.9150 0.0829
-10.000 0.0386 0.08765 0.08367 -0.1212 0.9078 0.0836
-9.750 0.0656 0.08508 0.08103 -0.1225 0.9007 0.0849
-9.500 0.0778 0.08285 0.07877 -0.1231 0.8898 0.0864
-9.250 0.0847 0.08023 0.07610 -0.1252 0.8804 0.0898
-9.000 0.0391 0.07492 0.07077 -0.1319 0.8660 0.0928
-8.750 0.0666 0.07342 0.06925 -0.1292 0.8591 0.0936
-8.500 0.0851 0.07187 0.06766 -0.1280 0.8515 0.0950
-8.250 0.0945 0.06989 0.06563 -0.1280 0.8442 0.0968
-8.000 0.0923 0.06759 0.06334 -0.1280 0.8350 0.0991
-7.750 -0.0308 0.06161 0.05708 -0.1328 0.8185 0.1033
-7.500 0.0019 0.05798 0.05360 -0.1325 0.8137 0.1042
-7.250 -0.0837 0.04086 0.03551 -0.1307 0.8058 0.0746
-7.000 -0.0648 0.03993 0.03468 -0.1298 0.7986 0.0754
-6.750 -0.0606 0.03622 0.03064 -0.1279 0.7927 0.0715
-6.500 -0.0607 0.03235 0.02627 -0.1252 0.7867 0.0700
-6.250 -0.0535 0.02972 0.02326 -0.1227 0.7795 0.0698
-6.000 -0.0385 0.02750 0.02063 -0.1209 0.7742 0.0698
-5.750 -0.0192 0.02580 0.01856 -0.1197 0.7695 0.0702
-5.500 -0.0022 0.02459 0.01714 -0.1179 0.7624 0.0709
-5.250 0.0200 0.02341 0.01568 -0.1168 0.7569 0.0720
-5.000 0.0456 0.02241 0.01433 -0.1161 0.7526 0.0736
-4.750 0.0663 0.02163 0.01350 -0.1149 0.7456 0.0752
-4.500 0.0908 0.02113 0.01299 -0.1142 0.7397 0.0773
-4.250 0.1185 0.02052 0.01226 -0.1139 0.7352 0.0797
-4.000 0.1427 0.02004 0.01161 -0.1131 0.7298 0.0821
-3.750 0.1659 0.01946 0.01106 -0.1122 0.7236 0.0846
-3.500 0.1928 0.01910 0.01069 -0.1118 0.7188 0.0883
-3.250 0.2220 0.01868 0.01010 -0.1118 0.7150 0.0931
-3.000 0.2423 0.01841 0.00997 -0.1104 0.7081 0.0974
-2.750 0.2679 0.01814 0.00961 -0.1097 0.7028 0.1034
-2.500 0.2952 0.01770 0.00922 -0.1095 0.6988 0.1116
-2.250 0.3197 0.01740 0.00896 -0.1088 0.6943 0.1216
-2.000 0.3408 0.01717 0.00881 -0.1075 0.6885 0.1347
-1.750 0.3658 0.01687 0.00857 -0.1069 0.6839 0.1524
-1.500 0.3938 0.01661 0.00830 -0.1068 0.6801 0.1722
-1.250 0.4165 0.01652 0.00829 -0.1058 0.6753 0.1899
-1.000 0.4382 0.01643 0.00830 -0.1047 0.6701 0.2093
-0.750 0.4631 0.01624 0.00819 -0.1041 0.6659 0.2361
-0.500 0.4893 0.01588 0.00802 -0.1037 0.6624 0.2879
-0.250 0.5051 0.01535 0.00809 -0.1016 0.6576 0.4303
0.000 0.5162 0.01434 0.00840 -0.0976 0.6520 0.7867
0.250 0.6369 0.01431 0.00836 -0.1147 0.6464 0.9638
0.500 0.7076 0.01437 0.00820 -0.1229 0.6418 0.9858
0.750 0.7665 0.01443 0.00821 -0.1295 0.6357 1.0000
1.000 0.7864 0.01449 0.00818 -0.1281 0.6309 1.0000
1.250 0.8104 0.01450 0.00805 -0.1273 0.6268 1.0000
1.500 0.8277 0.01467 0.00818 -0.1255 0.6217 1.0000
1.750 0.8449 0.01479 0.00828 -0.1235 0.6161 1.0000
2.000 0.8681 0.01480 0.00818 -0.1226 0.6111 1.0000
2.250 0.8919 0.01488 0.00815 -0.1217 0.6065 1.0000
2.500 0.9059 0.01506 0.00835 -0.1192 0.6002 1.0000
2.750 0.9278 0.01513 0.00835 -0.1180 0.5951 1.0000
3.000 0.9542 0.01520 0.00831 -0.1176 0.5911 1.0000
3.250 0.9705 0.01545 0.00858 -0.1155 0.5862 1.0000
3.500 0.9886 0.01564 0.00877 -0.1137 0.5811 1.0000
3.750 1.0124 0.01573 0.00879 -0.1129 0.5765 1.0000
4.000 1.0403 0.01584 0.00878 -0.1129 0.5725 1.0000
4.250 1.0521 0.01610 0.00914 -0.1099 0.5666 1.0000
4.500 1.0727 0.01622 0.00923 -0.1085 0.5610 1.0000
4.750 1.1002 0.01628 0.00918 -0.1083 0.5562 1.0000
5.000 1.1143 0.01652 0.00948 -0.1058 0.5500 1.0000
5.250 1.1331 0.01665 0.00961 -0.1041 0.5439 1.0000
5.500 1.1603 0.01671 0.00957 -0.1039 0.5387 1.0000
5.750 1.1729 0.01696 0.00988 -0.1011 0.5321 1.0000
6.000 1.1911 0.01709 0.01001 -0.0993 0.5255 1.0000
6.250 1.2174 0.01717 0.01000 -0.0989 0.5196 1.0000
6.500 1.2248 0.01741 0.01034 -0.0952 0.5118 1.0000
6.750 1.2459 0.01748 0.01035 -0.0939 0.5046 1.0000
7.000 1.2555 0.01771 0.01063 -0.0905 0.4964 1.0000
7.250 1.2705 0.01781 0.01069 -0.0881 0.4879 1.0000
7.500 1.2751 0.01805 0.01096 -0.0839 0.4782 1.0000
7.750 1.2875 0.01816 0.01100 -0.0810 0.4687 1.0000
8.000 1.2834 0.01851 0.01143 -0.0755 0.4573 1.0000
8.250 1.2878 0.01886 0.01176 -0.0716 0.4450 1.0000
8.500 1.2914 0.01930 0.01216 -0.0678 0.4311 1.0000
8.750 1.2919 0.01993 0.01274 -0.0637 0.4144 1.0000
9.000 1.2920 0.02073 0.01348 -0.0600 0.3969 1.0000
9.250 1.2926 0.02169 0.01433 -0.0565 0.3793 1.0000
9.500 1.2946 0.02275 0.01528 -0.0535 0.3635 1.0000
9.750 1.2979 0.02387 0.01628 -0.0508 0.3495 1.0000
10.000 1.3033 0.02498 0.01729 -0.0485 0.3377 1.0000
10.250 1.3115 0.02603 0.01832 -0.0466 0.3281 1.0000
10.500 1.3217 0.02702 0.01917 -0.0450 0.3200 1.0000
10.750 1.3310 0.02808 0.02027 -0.0434 0.3123 1.0000
11.000 1.3426 0.02903 0.02114 -0.0420 0.3055 1.0000
11.250 1.3546 0.03000 0.02212 -0.0407 0.2995 1.0000
11.500 1.3657 0.03102 0.02316 -0.0394 0.2938 1.0000
11.750 1.3813 0.03181 0.02384 -0.0385 0.2882 1.0000
12.000 1.3930 0.03283 0.02492 -0.0373 0.2836 1.0000
12.250 1.4043 0.03388 0.02604 -0.0362 0.2790 1.0000
12.500 1.4186 0.03477 0.02692 -0.0353 0.2747 1.0000
12.750 1.4414 0.03524 0.02729 -0.0349 0.2705 1.0000
13.000 1.4479 0.03658 0.02877 -0.0336 0.2668 1.0000
13.250 1.4582 0.03774 0.03001 -0.0326 0.2628 1.0000
13.500 1.4705 0.03877 0.03106 -0.0316 0.2587 1.0000
13.750 1.4971 0.03905 0.03121 -0.0316 0.2545 1.0000
14.000 1.4971 0.04083 0.03318 -0.0300 0.2510 1.0000
14.250 1.5032 0.04229 0.03475 -0.0289 0.2469 1.0000
14.500 1.5130 0.04351 0.03599 -0.0281 0.2428 1.0000
14.750 1.5368 0.04388 0.03625 -0.0278 0.2382 1.0000
15.000 1.5330 0.04607 0.03864 -0.0264 0.2348 1.0000
15.250 1.5362 0.04785 0.04054 -0.0254 0.2309 1.0000
15.500 1.5432 0.04931 0.04203 -0.0247 0.2267 1.0000
15.750 1.5621 0.04993 0.04256 -0.0242 0.2221 1.0000
16.000 1.5529 0.05278 0.04563 -0.0231 0.2183 1.0000
16.250 1.5516 0.05507 0.04803 -0.0224 0.2139 1.0000
16.500 1.5576 0.05671 0.04968 -0.0218 0.2097 1.0000
16.750 1.5668 0.05814 0.05112 -0.0213 0.2056 1.0000
17.000 1.5595 0.06123 0.05441 -0.0208 0.2020 1.0000
17.250 1.5583 0.06376 0.05705 -0.0205 0.1978 1.0000
17.500 1.5641 0.06557 0.05886 -0.0202 0.1941 1.0000
17.750 1.5669 0.06774 0.06109 -0.0199 0.1902 1.0000
18.000 1.5582 0.07133 0.06488 -0.0199 0.1863 1.0000
18.250 1.5553 0.07429 0.06794 -0.0200 0.1821 1.0000
18.500 1.5617 0.07609 0.06969 -0.0199 0.1781 1.0000
18.750 1.5515 0.08012 0.07392 -0.0203 0.1741 1.0000
19.000 1.5427 0.08403 0.07798 -0.0208 0.1695 1.0000
19.250 1.5428 0.08679 0.08077 -0.0212 0.1655 1.0000
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