GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 456 AIRFOIL (goe456-il) Reynolds number: 200,000 Max Cl/Cd: 87.49 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe456-il-200000.txt Download as CSV file: xf-goe456-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 456 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3342 0.09970 0.09660 -0.0288 1.0000 0.0304
-7.500 -0.3503 0.09928 0.09627 -0.0257 1.0000 0.0306
-7.250 -0.3639 0.09821 0.09526 -0.0225 1.0000 0.0305
-7.000 -0.3642 0.09642 0.09352 -0.0255 0.9980 0.0309
-6.500 -0.3077 0.08565 0.08273 -0.0441 0.9868 0.0314
-6.250 -0.2985 0.07959 0.07667 -0.0437 0.9841 0.0330
-6.000 -0.2773 0.07592 0.07298 -0.0466 0.9792 0.0345
-5.750 -0.2507 0.07173 0.06876 -0.0527 0.9735 0.0366
-5.500 -0.2138 0.06670 0.06363 -0.0623 0.9697 0.0396
-5.250 -0.1613 0.06084 0.05758 -0.0788 0.9607 0.0439
-5.000 -0.1315 0.05385 0.05052 -0.0860 0.9572 0.0455
-4.750 -0.1124 0.05140 0.04807 -0.0864 0.9507 0.0478
-4.500 -0.0738 0.04722 0.04374 -0.0928 0.9461 0.0536
-4.250 -0.0281 0.04160 0.03790 -0.1014 0.9433 0.0611
-4.000 0.0054 0.03740 0.03339 -0.1060 0.9357 0.0725
-3.750 0.0409 0.03526 0.03119 -0.1090 0.9322 0.0874
-3.500 0.0859 0.03228 0.02785 -0.1143 0.9300 0.1114
-3.250 0.1270 0.02093 0.01488 -0.1160 0.9242 0.0403
-3.000 0.1641 0.01829 0.01159 -0.1172 0.9199 0.0365
-2.750 0.2038 0.01652 0.00947 -0.1189 0.9170 0.0365
-2.500 0.2345 0.01546 0.00828 -0.1190 0.9103 0.0401
-2.250 0.2692 0.01441 0.00711 -0.1199 0.9050 0.0453
-2.000 0.3026 0.01340 0.00603 -0.1207 0.8995 0.0549
-1.750 0.3324 0.01255 0.00556 -0.1207 0.8918 0.1744
-1.500 0.3637 0.01251 0.00545 -0.1212 0.8847 0.2203
-1.250 0.3941 0.01235 0.00529 -0.1215 0.8768 0.2505
-1.000 0.4219 0.01217 0.00510 -0.1213 0.8674 0.2737
-0.750 0.4532 0.01181 0.00473 -0.1217 0.8606 0.2925
-0.500 0.4789 0.01154 0.00454 -0.1211 0.8499 0.3200
-0.250 0.5046 0.01113 0.00438 -0.1206 0.8397 0.3862
0.000 0.5493 0.00958 0.00409 -0.1237 0.8336 1.0000
0.250 0.5749 0.00964 0.00400 -0.1230 0.8222 1.0000
0.500 0.6011 0.00971 0.00394 -0.1225 0.8112 1.0000
0.750 0.6277 0.00977 0.00389 -0.1220 0.8008 1.0000
1.000 0.6547 0.00982 0.00382 -0.1216 0.7902 1.0000
1.250 0.6814 0.00986 0.00376 -0.1211 0.7786 1.0000
1.500 0.7070 0.00990 0.00371 -0.1204 0.7657 1.0000
1.750 0.7325 0.00997 0.00371 -0.1197 0.7529 1.0000
2.000 0.7579 0.01005 0.00373 -0.1190 0.7402 1.0000
2.250 0.7834 0.01014 0.00377 -0.1184 0.7275 1.0000
2.500 0.8087 0.01023 0.00384 -0.1177 0.7142 1.0000
2.750 0.8341 0.01034 0.00392 -0.1170 0.7014 1.0000
3.000 0.8597 0.01048 0.00404 -0.1165 0.6903 1.0000
3.250 0.8856 0.01063 0.00419 -0.1160 0.6797 1.0000
3.500 0.9116 0.01080 0.00438 -0.1155 0.6694 1.0000
3.750 0.9359 0.01095 0.00453 -0.1147 0.6542 1.0000
4.000 0.9578 0.01106 0.00456 -0.1131 0.6275 1.0000
4.250 0.9808 0.01123 0.00475 -0.1120 0.6073 1.0000
4.500 1.0000 0.01143 0.00482 -0.1099 0.5677 1.0000
4.750 1.0189 0.01170 0.00502 -0.1079 0.5239 1.0000
5.000 1.0309 0.01233 0.00522 -0.1047 0.4242 1.0000
5.250 1.0277 0.01445 0.00614 -0.0996 0.2368 1.0000
5.500 1.0261 0.01694 0.00745 -0.0953 0.0525 1.0000
5.750 1.0416 0.01802 0.00847 -0.0930 0.0336 1.0000
6.000 1.0594 0.01890 0.00955 -0.0910 0.0300 1.0000
6.250 1.0771 0.01974 0.01059 -0.0891 0.0290 1.0000
6.500 1.0924 0.02072 0.01172 -0.0869 0.0264 1.0000
6.750 1.1046 0.02185 0.01301 -0.0843 0.0248 1.0000
7.000 1.1141 0.02315 0.01441 -0.0813 0.0242 1.0000
7.250 1.1231 0.02451 0.01583 -0.0781 0.0241 1.0000
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Polar data table (+)
Polar graphs
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