GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 388 AIRFOIL (goe388-il) Reynolds number: 1,000,000 Max Cl/Cd: 53.51 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe388-il-1000000.txt Download as CSV file: xf-goe388-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 388 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3241 0.09459 0.09008 -0.0483 0.1005 0.0218
-9.000 -0.3310 0.08816 0.08367 -0.0514 0.0954 0.0222
-8.750 -0.3205 0.08621 0.08172 -0.0518 0.0997 0.0225
-8.500 -0.3095 0.08426 0.07976 -0.0525 0.0974 0.0228
-8.250 -0.2994 0.08211 0.07760 -0.0538 0.0934 0.0233
-8.000 -0.2910 0.07979 0.07526 -0.0554 0.0791 0.0239
-7.750 -0.2816 0.07708 0.07253 -0.0582 0.0625 0.0249
-7.500 -0.2618 0.07163 0.06706 -0.0690 0.0624 0.0274
-7.250 -0.2446 0.06674 0.06215 -0.0756 0.0612 0.0275
-7.000 -0.2252 0.06122 0.05657 -0.0827 0.0602 0.0276
-6.750 -0.2114 0.04972 0.04494 -0.0951 0.0613 0.0285
-6.500 -0.1903 0.04815 0.04335 -0.0965 0.0575 0.0289
-6.250 -0.1677 0.04625 0.04142 -0.0984 0.0429 0.0294
-6.000 -0.1437 0.04361 0.03871 -0.1010 0.0375 0.0301
-5.750 -0.1183 0.04045 0.03545 -0.1041 0.0347 0.0312
-5.500 -0.0845 0.03669 0.03145 -0.1073 0.0329 0.0348
-4.500 0.0141 0.01899 0.01216 -0.1145 0.0298 0.0325
-4.250 0.0407 0.01715 0.01001 -0.1148 0.0289 0.0321
-4.000 0.0672 0.01639 0.00909 -0.1148 0.0282 0.0326
-3.750 0.0930 0.01587 0.00842 -0.1147 0.0279 0.0330
-3.500 0.1199 0.01528 0.00770 -0.1147 0.0278 0.0334
-3.250 0.1472 0.01485 0.00717 -0.1148 0.0277 0.0340
-3.000 0.1749 0.01443 0.00666 -0.1149 0.0273 0.0344
-2.750 0.2020 0.01417 0.00633 -0.1150 0.0267 0.0346
-2.500 0.2287 0.01401 0.00611 -0.1149 0.0261 0.0349
-2.250 0.2553 0.01394 0.00598 -0.1149 0.0256 0.0351
-2.000 0.2813 0.01357 0.00555 -0.1148 0.0249 0.0353
-1.750 0.3066 0.01328 0.00520 -0.1145 0.0245 0.0359
-1.500 0.3301 0.01343 0.00530 -0.1140 0.0242 0.0369
-1.250 0.3523 0.01398 0.00580 -0.1133 0.0241 0.0382
-1.000 0.3785 0.01403 0.00583 -0.1132 0.0240 0.0395
-0.750 0.4060 0.01388 0.00567 -0.1133 0.0239 0.0407
-0.500 0.4354 0.01348 0.00527 -0.1137 0.0233 0.0419
-0.250 0.4615 0.01358 0.00534 -0.1136 0.0225 0.0430
0.000 0.4866 0.01382 0.00555 -0.1133 0.0220 0.0439
0.250 0.5114 0.01413 0.00583 -0.1130 0.0217 0.0446
0.500 0.5361 0.01442 0.00606 -0.1126 0.0214 0.0476
0.750 0.5606 0.01480 0.00642 -0.1122 0.0212 0.0535
1.000 0.5850 0.01524 0.00686 -0.1119 0.0210 0.0688
1.250 0.6098 0.01558 0.00744 -0.1118 0.0209 0.1832
1.500 0.6349 0.01600 0.00815 -0.1118 0.0208 0.3263
1.750 0.6607 0.01636 0.00903 -0.1122 0.0207 0.5770
6.500 1.1023 0.02060 0.01402 -0.1041 0.0205 1.0000
6.750 1.1247 0.02148 0.01496 -0.1037 0.0205 1.0000
7.000 1.1468 0.02244 0.01598 -0.1034 0.0205 1.0000
7.250 1.1688 0.02338 0.01701 -0.1030 0.0205 1.0000
7.500 1.1908 0.02427 0.01798 -0.1025 0.0204 1.0000
7.750 1.2132 0.02494 0.01877 -0.1021 0.0204 1.0000
8.000 1.2370 0.02450 0.01855 -0.1013 0.0202 1.0000
8.250 1.2618 0.02368 0.01779 -0.1010 0.0178 1.0000
8.500 1.2807 0.02570 0.01980 -0.1009 0.0170 1.0000
8.750 1.3557 0.03613 0.02995 -0.1089 0.0144 1.0000
9.000 1.3783 0.03707 0.03098 -0.1084 0.0103 1.0000
9.250 1.4011 0.03751 0.03140 -0.1084 0.0096 1.0000
9.500 1.4228 0.03827 0.03219 -0.1081 0.0090 1.0000
9.750 1.4437 0.03923 0.03319 -0.1077 0.0084 1.0000
10.000 1.4649 0.03995 0.03392 -0.1074 0.0079 1.0000
10.250 1.4874 0.04021 0.03414 -0.1074 0.0075 1.0000
10.500 1.5060 0.04156 0.03559 -0.1066 0.0072 1.0000
10.750 1.5237 0.04300 0.03715 -0.1057 0.0069 1.0000
11.000 1.5421 0.04411 0.03833 -0.1049 0.0065 1.0000
11.250 1.5610 0.04497 0.03923 -0.1043 0.0063 1.0000
11.500 1.5794 0.04581 0.04011 -0.1037 0.0061 1.0000
11.750 1.5962 0.04680 0.04117 -0.1028 0.0058 1.0000
12.000 1.6080 0.04848 0.04301 -0.1011 0.0056 1.0000
12.250 1.6169 0.05070 0.04545 -0.0990 0.0055 1.0000
12.500 1.6239 0.05303 0.04798 -0.0967 0.0055 1.0000
12.750 1.6277 0.05557 0.05073 -0.0941 0.0054 1.0000
13.000 1.6276 0.05829 0.05369 -0.0910 0.0053 1.0000
13.250 1.6230 0.06122 0.05686 -0.0875 0.0053 1.0000
13.500 1.6139 0.06428 0.06016 -0.0835 0.0052 1.0000
13.750 1.6001 0.06745 0.06356 -0.0792 0.0052 1.0000
14.000 1.5779 0.07053 0.06686 -0.0738 0.0051 1.0000
14.250 1.5478 0.07366 0.07020 -0.0680 0.0051 1.0000
14.500 1.5176 0.07713 0.07386 -0.0635 0.0051 1.0000
14.750 1.4884 0.08091 0.07782 -0.0602 0.0051 1.0000
15.000 1.4574 0.08526 0.08235 -0.0578 0.0051 1.0000
15.250 1.4261 0.09010 0.08737 -0.0565 0.0052 1.0000
15.500 1.3938 0.09555 0.09299 -0.0562 0.0052 1.0000
15.750 1.3628 0.10141 0.09901 -0.0569 0.0052 1.0000
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Polar data table (+)
Polar graphs
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