GOE 527 AIRFOIL (goe527-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 527 AIRFOIL (goe527-il) Reynolds number: 200,000 Max Cl/Cd: 69.46 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe527-il-200000.txt Download as CSV file: xf-goe527-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 527 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.2121 0.14787 0.14408 -0.0462 1.0000 0.0571
-13.750 -0.2109 0.14529 0.14154 -0.0468 1.0000 0.0590
-13.500 -0.2374 0.14297 0.13930 -0.0506 1.0000 0.0604
-13.250 -0.2177 0.13971 0.13606 -0.0482 1.0000 0.0610
-13.000 -0.2108 0.13768 0.13408 -0.0467 1.0000 0.0617
-12.750 -0.2116 0.13617 0.13264 -0.0450 1.0000 0.0626
-12.500 -0.2224 0.13572 0.13228 -0.0417 0.9999 0.0634
-12.250 -0.2054 0.13116 0.12771 -0.0472 0.9968 0.0660
-12.000 -0.2123 0.12527 0.12183 -0.0570 0.9912 0.0678
-11.750 -0.1791 0.12139 0.11793 -0.0579 0.9873 0.0686
-11.500 -0.1541 0.11774 0.11427 -0.0611 0.9832 0.0701
-11.250 -0.1362 0.11389 0.11041 -0.0652 0.9771 0.0727
-11.000 -0.1539 0.10725 0.10379 -0.0785 0.9692 0.0758
-10.750 -0.1213 0.10377 0.10028 -0.0777 0.9633 0.0766
-10.500 -0.0942 0.10041 0.09691 -0.0799 0.9571 0.0776
-10.250 -0.0700 0.09684 0.09332 -0.0838 0.9509 0.0796
-9.750 -0.0504 0.08549 0.08192 -0.1009 0.9337 0.0859
-9.500 -0.0158 0.08266 0.07904 -0.1031 0.9257 0.0873
-9.250 0.0118 0.07917 0.07549 -0.1078 0.9151 0.0894
-9.000 -0.0428 0.06837 0.06454 -0.1297 0.8856 0.0954
-8.750 -0.0124 0.06598 0.06217 -0.1269 0.8756 0.0963
-8.500 0.0216 0.06497 0.06108 -0.1248 0.8663 0.0973
-8.250 -0.1638 0.03929 0.03408 -0.1302 0.8380 0.0674
-8.000 -0.1568 0.03622 0.03069 -0.1289 0.8286 0.0673
-7.750 -0.1507 0.03356 0.02774 -0.1268 0.8172 0.0671
-7.500 -0.1407 0.03093 0.02470 -0.1251 0.8083 0.0671
-7.250 -0.1299 0.02872 0.02206 -0.1230 0.7982 0.0674
-7.000 -0.1115 0.02688 0.01999 -0.1220 0.7903 0.0683
-6.750 -0.0891 0.02629 0.01943 -0.1212 0.7805 0.0697
-6.500 -0.0658 0.02540 0.01836 -0.1205 0.7729 0.0712
-6.250 -0.0469 0.02425 0.01698 -0.1190 0.7630 0.0726
-6.000 -0.0238 0.02299 0.01534 -0.1181 0.7558 0.0742
-5.750 -0.0035 0.02208 0.01411 -0.1165 0.7465 0.0758
-5.500 0.0218 0.02114 0.01316 -0.1162 0.7392 0.0778
-5.250 0.0459 0.02075 0.01272 -0.1154 0.7311 0.0806
-5.000 0.0706 0.02023 0.01196 -0.1145 0.7231 0.0840
-4.750 0.0963 0.01946 0.01111 -0.1141 0.7162 0.0872
-4.500 0.1202 0.01905 0.01069 -0.1132 0.7079 0.0910
-4.250 0.1468 0.01859 0.01002 -0.1127 0.7017 0.0963
-4.000 0.1710 0.01816 0.00967 -0.1120 0.6944 0.1020
-3.750 0.1962 0.01775 0.00914 -0.1113 0.6873 0.1089
-3.500 0.2234 0.01733 0.00871 -0.1111 0.6817 0.1163
-3.250 0.2464 0.01696 0.00835 -0.1101 0.6744 0.1238
-3.000 0.2719 0.01668 0.00808 -0.1096 0.6683 0.1319
-2.750 0.2991 0.01636 0.00770 -0.1093 0.6633 0.1403
-2.500 0.3221 0.01622 0.00760 -0.1084 0.6565 0.1489
-2.250 0.3470 0.01594 0.00737 -0.1077 0.6505 0.1586
-2.000 0.3745 0.01580 0.00716 -0.1075 0.6459 0.1699
-1.750 0.3979 0.01566 0.00711 -0.1066 0.6402 0.1827
-1.500 0.4219 0.01546 0.00700 -0.1058 0.6344 0.2008
-1.250 0.4470 0.01514 0.00685 -0.1052 0.6296 0.2434
-1.000 0.4678 0.01458 0.00687 -0.1041 0.6252 0.3925
-0.750 0.4850 0.01421 0.00704 -0.1020 0.6197 0.5363
-0.500 0.5044 0.01385 0.00712 -0.1000 0.6148 0.6606
-0.250 0.5401 0.01353 0.00724 -0.1005 0.6104 0.8349
0.000 0.6107 0.01374 0.00747 -0.1084 0.6048 0.9526
0.250 0.6775 0.01389 0.00750 -0.1161 0.5987 0.9839
0.500 0.7397 0.01394 0.00736 -0.1231 0.5935 1.0000
0.750 0.7611 0.01412 0.00742 -0.1220 0.5891 1.0000
1.000 0.7784 0.01426 0.00755 -0.1201 0.5830 1.0000
1.250 0.8004 0.01433 0.00750 -0.1189 0.5771 1.0000
1.500 0.8236 0.01446 0.00749 -0.1180 0.5714 1.0000
1.750 0.8407 0.01458 0.00761 -0.1159 0.5646 1.0000
2.000 0.8633 0.01469 0.00762 -0.1148 0.5592 1.0000
2.250 0.8895 0.01489 0.00768 -0.1145 0.5552 1.0000
2.500 0.9065 0.01511 0.00795 -0.1125 0.5501 1.0000
2.750 0.9272 0.01529 0.00810 -0.1111 0.5449 1.0000
3.000 0.9516 0.01544 0.00815 -0.1104 0.5403 1.0000
3.250 0.9755 0.01567 0.00830 -0.1097 0.5358 1.0000
3.500 0.9927 0.01587 0.00855 -0.1077 0.5301 1.0000
3.750 1.0150 0.01604 0.00867 -0.1066 0.5250 1.0000
4.000 1.0415 0.01621 0.00874 -0.1063 0.5206 1.0000
4.250 1.0596 0.01648 0.00904 -0.1046 0.5154 1.0000
4.500 1.0790 0.01668 0.00926 -0.1030 0.5098 1.0000
4.750 1.1035 0.01683 0.00935 -0.1023 0.5050 1.0000
5.000 1.1272 0.01708 0.00954 -0.1016 0.5001 1.0000
5.250 1.1430 0.01731 0.00984 -0.0994 0.4941 1.0000
5.500 1.1656 0.01746 0.00996 -0.0985 0.4886 1.0000
5.750 1.1917 0.01766 0.01007 -0.0982 0.4835 1.0000
6.000 1.2043 0.01787 0.01038 -0.0954 0.4764 1.0000
6.250 1.2261 0.01799 0.01045 -0.0943 0.4702 1.0000
6.500 1.2456 0.01819 0.01063 -0.0928 0.4638 1.0000
6.750 1.2604 0.01837 0.01087 -0.0905 0.4565 1.0000
7.000 1.2844 0.01849 0.01088 -0.0898 0.4502 1.0000
7.250 1.2938 0.01875 0.01124 -0.0866 0.4424 1.0000
7.500 1.3113 0.01891 0.01137 -0.0848 0.4355 1.0000
7.750 1.3260 0.01918 0.01166 -0.0826 0.4285 1.0000
8.000 1.3364 0.01942 0.01193 -0.0796 0.4210 1.0000
8.250 1.3532 0.01967 0.01212 -0.0778 0.4142 1.0000
8.500 1.3566 0.02003 0.01255 -0.0737 0.4060 1.0000
8.750 1.3727 0.02030 0.01273 -0.0718 0.3985 1.0000
9.000 1.3749 0.02078 0.01330 -0.0679 0.3896 1.0000
9.250 1.3901 0.02116 0.01358 -0.0660 0.3820 1.0000
9.500 1.3939 0.02179 0.01430 -0.0627 0.3735 1.0000
9.750 1.4095 0.02226 0.01465 -0.0611 0.3661 1.0000
10.000 1.4123 0.02303 0.01553 -0.0579 0.3577 1.0000
10.500 1.4298 0.02451 0.01701 -0.0536 0.3424 1.0000
10.750 1.4424 0.02521 0.01764 -0.0520 0.3359 1.0000
11.000 1.4512 0.02611 0.01859 -0.0500 0.3294 1.0000
11.250 1.4599 0.02702 0.01954 -0.0482 0.3233 1.0000
11.500 1.4780 0.02765 0.02006 -0.0474 0.3178 1.0000
11.750 1.4813 0.02885 0.02140 -0.0452 0.3121 1.0000
12.000 1.4908 0.02984 0.02242 -0.0437 0.3068 1.0000
12.250 1.5107 0.03044 0.02291 -0.0432 0.3018 1.0000
12.500 1.5124 0.03185 0.02448 -0.0412 0.2969 1.0000
12.750 1.5194 0.03304 0.02573 -0.0397 0.2919 1.0000
13.000 1.5376 0.03371 0.02632 -0.0391 0.2872 1.0000
13.250 1.5423 0.03513 0.02786 -0.0376 0.2827 1.0000
13.500 1.5461 0.03660 0.02943 -0.0361 0.2779 1.0000
13.750 1.5571 0.03767 0.03050 -0.0352 0.2734 1.0000
14.000 1.5716 0.03863 0.03144 -0.0344 0.2688 1.0000
14.250 1.5687 0.04063 0.03361 -0.0329 0.2642 1.0000
14.500 1.5744 0.04212 0.03515 -0.0318 0.2595 1.0000
14.750 1.5983 0.04245 0.03536 -0.0316 0.2545 1.0000
15.000 1.5866 0.04523 0.03836 -0.0300 0.2501 1.0000
15.250 1.5873 0.04720 0.04042 -0.0290 0.2451 1.0000
15.500 1.6063 0.04777 0.04089 -0.0286 0.2399 1.0000
15.750 1.5954 0.05080 0.04411 -0.0275 0.2351 1.0000
16.000 1.5927 0.05323 0.04663 -0.0267 0.2298 1.0000
16.250 1.6112 0.05377 0.04704 -0.0263 0.2244 1.0000
16.500 1.5955 0.05754 0.05103 -0.0256 0.2196 1.0000
16.750 1.5910 0.06033 0.05391 -0.0252 0.2144 1.0000
17.000 1.6100 0.06076 0.05420 -0.0249 0.2091 1.0000
17.250 1.5915 0.06520 0.05888 -0.0247 0.2048 1.0000
17.500 1.5857 0.06838 0.06217 -0.0247 0.2003 1.0000
17.750 1.5942 0.06991 0.06365 -0.0246 0.1958 1.0000
18.000 1.5899 0.07306 0.06691 -0.0246 0.1918 1.0000
18.250 1.5766 0.07738 0.07140 -0.0251 0.1875 1.0000
18.500 1.5768 0.08008 0.07415 -0.0254 0.1836 1.0000
18.750 1.5902 0.08103 0.07502 -0.0253 0.1796 1.0000
19.000 1.5707 0.08643 0.08066 -0.0264 0.1764 1.0000
19.250 1.5602 0.09071 0.08509 -0.0273 0.1726 1.0000
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Polar data table (+)
Polar graphs
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