GOE 497 AIRFOIL (goe497-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 497 AIRFOIL (goe497-il) Reynolds number: 50,000 Max Cl/Cd: 34.83 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe497-il-50000-n5.txt Download as CSV file: xf-goe497-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 497 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3579 0.10754 0.10063 -0.0379 1.0000 0.0897
-8.750 -0.3681 0.10526 0.09843 -0.0365 1.0000 0.0893
-8.500 -0.3795 0.10302 0.09626 -0.0351 1.0000 0.0889
-8.250 -0.3873 0.10003 0.09333 -0.0355 0.9982 0.0890
-8.000 -0.3850 0.09536 0.08866 -0.0403 0.9909 0.0898
-7.750 -0.3862 0.09015 0.08346 -0.0460 0.9827 0.0907
-7.500 -0.3857 0.08338 0.07667 -0.0539 0.9735 0.0914
-7.250 -0.3845 0.07501 0.06825 -0.0637 0.9640 0.0917
-7.000 -0.3803 0.06322 0.05621 -0.0783 0.9552 0.0925
-6.750 -0.3576 0.06354 0.05657 -0.0769 0.9491 0.0947
-6.500 -0.3338 0.05842 0.05124 -0.0843 0.9436 0.0982
-6.250 -0.3189 0.05009 0.04233 -0.0942 0.9352 0.1014
-6.000 -0.2854 0.04264 0.03384 -0.1042 0.9305 0.1061
-5.750 -0.2585 0.04191 0.03314 -0.1049 0.9252 0.1100
-5.500 -0.2320 0.03996 0.03088 -0.1069 0.9190 0.1154
-5.250 -0.1972 0.03734 0.02769 -0.1105 0.9147 0.1218
-5.000 -0.1663 0.03665 0.02696 -0.1118 0.9100 0.1283
-4.750 -0.1396 0.03509 0.02494 -0.1130 0.9035 0.1364
-4.500 -0.1086 0.03457 0.02447 -0.1141 0.8985 0.1443
-4.250 -0.0734 0.03371 0.02340 -0.1162 0.8946 0.1553
-4.000 -0.0509 0.03313 0.02259 -0.1159 0.8871 0.1662
-3.750 -0.0188 0.03276 0.02222 -0.1171 0.8821 0.1791
-3.500 0.0140 0.03240 0.02180 -0.1184 0.8774 0.1937
-3.250 0.0361 0.03226 0.02162 -0.1179 0.8697 0.2071
-3.000 0.0712 0.03198 0.02128 -0.1193 0.8647 0.2256
-2.750 0.0972 0.03184 0.02108 -0.1192 0.8563 0.2425
-2.500 0.1327 0.03149 0.02063 -0.1205 0.8492 0.2628
-2.250 0.1618 0.03127 0.02033 -0.1207 0.8404 0.2824
-2.000 0.1957 0.03098 0.02001 -0.1216 0.8331 0.3023
-1.750 0.2256 0.03086 0.01987 -0.1218 0.8256 0.3221
-1.500 0.2542 0.03080 0.01978 -0.1219 0.8179 0.3422
-1.250 0.2934 0.03056 0.01947 -0.1236 0.8136 0.3669
-1.000 0.3113 0.03079 0.01969 -0.1221 0.8034 0.3853
-0.750 0.3474 0.03061 0.01951 -0.1232 0.7984 0.4096
-0.500 0.3682 0.03081 0.01972 -0.1221 0.7891 0.4299
-0.250 0.4020 0.03067 0.01953 -0.1229 0.7831 0.4559
0.000 0.4281 0.03069 0.01959 -0.1225 0.7753 0.4774
0.250 0.4568 0.03062 0.01955 -0.1224 0.7677 0.5008
0.500 0.4967 0.03022 0.01917 -0.1239 0.7637 0.5286
0.750 0.5119 0.03053 0.01955 -0.1221 0.7522 0.5502
1.000 0.5503 0.03008 0.01919 -0.1232 0.7478 0.5831
1.250 0.5658 0.03036 0.01961 -0.1213 0.7364 0.6120
1.500 0.6018 0.02979 0.01926 -0.1219 0.7317 0.6616
1.750 0.6141 0.02988 0.01967 -0.1191 0.7203 0.7295
2.000 0.6503 0.02915 0.01912 -0.1195 0.7152 1.0000
2.250 0.6684 0.02980 0.01964 -0.1184 0.7034 1.0000
2.500 0.7095 0.02959 0.01927 -0.1201 0.6987 1.0000
2.750 0.7262 0.03027 0.01987 -0.1187 0.6866 1.0000
3.000 0.7670 0.03000 0.01950 -0.1202 0.6821 1.0000
3.250 0.7819 0.03079 0.02025 -0.1185 0.6698 1.0000
3.500 0.8106 0.03102 0.02043 -0.1184 0.6619 1.0000
3.750 0.8372 0.03128 0.02067 -0.1181 0.6527 1.0000
4.000 0.8600 0.03166 0.02103 -0.1172 0.6423 1.0000
4.250 0.8977 0.03123 0.02056 -0.1177 0.6343 1.0000
4.500 0.9175 0.03155 0.02087 -0.1162 0.6211 1.0000
4.750 0.9439 0.03156 0.02086 -0.1155 0.6096 1.0000
5.000 0.9795 0.03116 0.02045 -0.1157 0.6004 1.0000
5.250 0.9941 0.03190 0.02123 -0.1139 0.5881 1.0000
5.500 1.0218 0.03208 0.02143 -0.1135 0.5791 1.0000
5.750 1.0449 0.03245 0.02184 -0.1125 0.5690 1.0000
6.000 1.0602 0.03318 0.02263 -0.1108 0.5579 1.0000
6.250 1.0976 0.03289 0.02236 -0.1114 0.5502 1.0000
6.500 1.1063 0.03388 0.02346 -0.1089 0.5379 1.0000
6.750 1.1247 0.03448 0.02412 -0.1074 0.5274 1.0000
7.000 1.1579 0.03437 0.02405 -0.1076 0.5187 1.0000
7.250 1.1679 0.03538 0.02516 -0.1053 0.5070 1.0000
7.500 1.1892 0.03584 0.02571 -0.1041 0.4965 1.0000
7.750 1.2225 0.03568 0.02560 -0.1042 0.4867 1.0000
8.000 1.2333 0.03670 0.02673 -0.1020 0.4747 1.0000
8.250 1.2539 0.03727 0.02739 -0.1008 0.4636 1.0000
8.500 1.2825 0.03729 0.02743 -0.1002 0.4513 1.0000
8.750 1.3049 0.03746 0.02760 -0.0989 0.4363 1.0000
9.000 1.3192 0.03796 0.02809 -0.0967 0.4198 1.0000
9.250 1.3265 0.03884 0.02903 -0.0939 0.4035 1.0000
9.500 1.3296 0.04007 0.03033 -0.0911 0.3878 1.0000
9.750 1.3317 0.04154 0.03191 -0.0884 0.3735 1.0000
10.000 1.3349 0.04304 0.03351 -0.0860 0.3596 1.0000
10.250 1.3385 0.04455 0.03512 -0.0838 0.3459 1.0000
10.500 1.3420 0.04611 0.03677 -0.0817 0.3322 1.0000
10.750 1.3458 0.04771 0.03847 -0.0798 0.3186 1.0000
11.000 1.3500 0.04933 0.04014 -0.0780 0.3050 1.0000
11.250 1.3544 0.05097 0.04180 -0.0763 0.2913 1.0000
11.500 1.3567 0.05291 0.04380 -0.0748 0.2775 1.0000
11.750 1.3581 0.05508 0.04601 -0.0733 0.2637 1.0000
12.000 1.3595 0.05734 0.04831 -0.0720 0.2501 1.0000
12.250 1.3611 0.05968 0.05067 -0.0708 0.2368 1.0000
12.500 1.3633 0.06203 0.05302 -0.0697 0.2240 1.0000
12.750 1.3677 0.06417 0.05510 -0.0686 0.2119 1.0000
13.000 1.3635 0.06761 0.05873 -0.0680 0.2004 1.0000
13.250 1.3627 0.07068 0.06188 -0.0674 0.1901 1.0000
13.500 1.3663 0.07313 0.06431 -0.0667 0.1807 1.0000
13.750 1.3599 0.07725 0.06866 -0.0668 0.1721 1.0000
14.000 1.3632 0.07994 0.07135 -0.0664 0.1648 1.0000
14.250 1.3587 0.08401 0.07565 -0.0667 0.1580 1.0000
14.500 1.3643 0.08638 0.07800 -0.0664 0.1519 1.0000
14.750 1.3562 0.09124 0.08312 -0.0672 0.1463 1.0000
15.000 1.3613 0.09378 0.08568 -0.0671 0.1408 1.0000
15.250 1.3572 0.09810 0.09017 -0.0679 0.1362 1.0000
15.500 1.3482 0.10336 0.09565 -0.0694 0.1318 1.0000
15.750 1.3658 0.10363 0.09575 -0.0683 0.1258 1.0000
16.000 1.3424 0.11169 0.10417 -0.0716 0.1225 1.0000
16.250 1.3223 0.11943 0.11216 -0.0750 0.1189 1.0000
16.500 1.3418 0.11875 0.11131 -0.0737 0.1115 1.0000
16.750 1.3091 0.12951 0.12240 -0.0794 0.1093 1.0000
17.000 1.2548 0.14651 0.13971 -0.0894 0.1086 1.0000
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