GOE 723 AIRFOIL (goe723-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 723 AIRFOIL (goe723-il) Reynolds number: 100,000 Max Cl/Cd: 58.42 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe723-il-100000.txt Download as CSV file: xf-goe723-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 723 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2885 0.10459 0.09947 -0.0383 1.0000 0.1226
-8.750 -0.2957 0.10291 0.09788 -0.0387 1.0000 0.1272
-8.500 -0.3367 0.10391 0.09910 -0.0402 1.0000 0.1294
-8.250 -0.3277 0.09956 0.09480 -0.0382 1.0000 0.1309
-8.000 -0.3082 0.09634 0.09160 -0.0352 1.0000 0.1337
-7.750 -0.3141 0.09511 0.09047 -0.0321 1.0000 0.1362
-7.500 -0.3337 0.09486 0.09036 -0.0279 1.0000 0.1382
-7.250 -0.3610 0.09518 0.09081 -0.0232 1.0000 0.1399
-7.000 -0.3939 0.09353 0.08927 -0.0383 0.9878 0.1452
-6.750 -0.3632 0.08996 0.08569 -0.0300 0.9879 0.1480
-6.500 -0.3346 0.08650 0.08220 -0.0351 0.9803 0.1572
-6.250 -0.3100 0.08143 0.07711 -0.0439 0.9712 0.1639
-6.000 -0.2854 0.07836 0.07402 -0.0464 0.9621 0.1707
-5.750 -0.2649 0.07370 0.06933 -0.0552 0.9510 0.1799
-5.500 -0.2356 0.06903 0.06455 -0.0667 0.9421 0.1942
-5.250 -0.2136 0.06653 0.06208 -0.0645 0.9342 0.1975
-5.000 -0.1779 0.06201 0.05745 -0.0737 0.9285 0.2121
-4.750 -0.1577 0.05981 0.05522 -0.0750 0.9178 0.2227
-4.500 -0.1269 0.03455 0.02739 -0.1003 0.9062 0.0995
-4.250 -0.0919 0.03157 0.02406 -0.1024 0.9004 0.0962
-4.000 -0.0487 0.02878 0.02069 -0.1054 0.8970 0.0928
-3.750 -0.0265 0.02750 0.01901 -0.1044 0.8870 0.0914
-3.500 0.0163 0.02590 0.01711 -0.1069 0.8827 0.0912
-3.250 0.0617 0.02452 0.01558 -0.1098 0.8796 0.0933
-3.000 0.0809 0.02409 0.01508 -0.1081 0.8688 0.0958
-2.750 0.1225 0.02308 0.01395 -0.1102 0.8645 0.0987
-2.500 0.1461 0.02268 0.01351 -0.1092 0.8554 0.1006
-2.250 0.1800 0.02181 0.01273 -0.1100 0.8495 0.1050
-2.000 0.2128 0.02129 0.01220 -0.1105 0.8436 0.1122
-1.750 0.2353 0.02102 0.01200 -0.1094 0.8346 0.1229
-1.500 0.2719 0.01983 0.01143 -0.1108 0.8301 0.2287
-1.250 0.2881 0.01990 0.01198 -0.1086 0.8201 0.3924
-1.000 0.3197 0.01983 0.01202 -0.1086 0.8145 0.4664
-0.750 0.3390 0.02010 0.01237 -0.1068 0.8056 0.5135
-0.500 0.3674 0.02000 0.01235 -0.1063 0.7991 0.5619
-0.250 0.3956 0.01991 0.01236 -0.1059 0.7926 0.6111
0.000 0.4200 0.01978 0.01244 -0.1048 0.7841 0.6694
0.250 0.4603 0.01897 0.01196 -0.1062 0.7795 0.7660
0.500 0.5343 0.01860 0.01172 -0.1159 0.7707 1.0000
0.750 0.5683 0.01859 0.01147 -0.1167 0.7640 1.0000
1.000 0.5903 0.01900 0.01175 -0.1157 0.7545 1.0000
1.250 0.6215 0.01905 0.01164 -0.1159 0.7476 1.0000
1.500 0.6435 0.01947 0.01198 -0.1148 0.7387 1.0000
1.750 0.6728 0.01958 0.01197 -0.1147 0.7314 1.0000
2.000 0.6960 0.01998 0.01232 -0.1138 0.7231 1.0000
2.250 0.7232 0.02016 0.01243 -0.1133 0.7153 1.0000
2.500 0.7481 0.02049 0.01270 -0.1126 0.7074 1.0000
2.750 0.7734 0.02075 0.01293 -0.1119 0.6991 1.0000
3.000 0.7998 0.02101 0.01316 -0.1113 0.6915 1.0000
3.250 0.8235 0.02135 0.01348 -0.1104 0.6826 1.0000
3.500 0.8505 0.02157 0.01368 -0.1099 0.6751 1.0000
3.750 0.8738 0.02190 0.01403 -0.1089 0.6657 1.0000
4.000 0.8997 0.02218 0.01430 -0.1083 0.6579 1.0000
4.250 0.9239 0.02248 0.01463 -0.1074 0.6487 1.0000
4.500 0.9479 0.02281 0.01499 -0.1064 0.6399 1.0000
4.750 0.9763 0.02281 0.01498 -0.1059 0.6308 1.0000
5.000 0.9974 0.02315 0.01537 -0.1045 0.6197 1.0000
5.250 1.0290 0.02276 0.01494 -0.1041 0.6091 1.0000
5.500 1.0580 0.02237 0.01451 -0.1033 0.5964 1.0000
5.750 1.0801 0.02232 0.01450 -0.1017 0.5825 1.0000
6.000 1.1034 0.02227 0.01449 -0.1003 0.5693 1.0000
6.250 1.1284 0.02211 0.01434 -0.0991 0.5561 1.0000
6.500 1.1541 0.02190 0.01412 -0.0980 0.5427 1.0000
6.750 1.1800 0.02171 0.01393 -0.0969 0.5293 1.0000
7.000 1.2014 0.02168 0.01395 -0.0952 0.5146 1.0000
7.250 1.2211 0.02167 0.01400 -0.0933 0.4989 1.0000
7.500 1.2402 0.02166 0.01405 -0.0912 0.4823 1.0000
7.750 1.2541 0.02170 0.01421 -0.0883 0.4612 1.0000
8.000 1.2666 0.02168 0.01420 -0.0850 0.4346 1.0000
8.250 1.2731 0.02192 0.01443 -0.0809 0.3995 1.0000
8.500 1.2701 0.02258 0.01486 -0.0753 0.3441 1.0000
8.750 1.2539 0.02403 0.01582 -0.0682 0.2689 1.0000
9.000 1.2338 0.02618 0.01738 -0.0617 0.1970 1.0000
9.250 1.2205 0.02847 0.01928 -0.0569 0.1655 1.0000
9.500 1.2141 0.03058 0.02124 -0.0533 0.1508 1.0000
9.750 1.2109 0.03265 0.02320 -0.0503 0.1420 1.0000
10.000 1.2127 0.03450 0.02503 -0.0479 0.1347 1.0000
10.250 1.2178 0.03629 0.02672 -0.0457 0.1285 1.0000
10.500 1.2289 0.03774 0.02817 -0.0440 0.1223 1.0000
10.750 1.2519 0.03903 0.02921 -0.0428 0.1159 1.0000
11.000 1.2696 0.04032 0.03064 -0.0415 0.1108 1.0000
11.250 1.3038 0.04160 0.03173 -0.0416 0.1043 1.0000
11.500 1.3308 0.04324 0.03348 -0.0412 0.0994 1.0000
11.750 1.3503 0.04485 0.03524 -0.0403 0.0949 1.0000
12.000 1.3994 0.04744 0.03769 -0.0427 0.0887 1.0000
12.250 1.4044 0.04920 0.03975 -0.0403 0.0862 1.0000
12.500 1.4155 0.05121 0.04198 -0.0388 0.0831 1.0000
12.750 1.4318 0.05333 0.04418 -0.0380 0.0798 1.0000
13.000 1.4577 0.05709 0.04806 -0.0385 0.0767 1.0000
13.250 1.4486 0.05939 0.05071 -0.0352 0.0757 1.0000
13.500 1.4392 0.06205 0.05370 -0.0325 0.0745 1.0000
13.750 1.4298 0.06504 0.05699 -0.0302 0.0733 1.0000
14.000 1.4196 0.06828 0.06050 -0.0284 0.0723 1.0000
14.250 1.4089 0.07165 0.06412 -0.0269 0.0712 1.0000
14.500 1.3955 0.07551 0.06824 -0.0258 0.0707 1.0000
14.750 1.3777 0.07990 0.07289 -0.0250 0.0704 1.0000
15.000 1.3552 0.08484 0.07811 -0.0248 0.0703 1.0000
15.250 1.3247 0.09084 0.08441 -0.0256 0.0709 1.0000
15.500 1.2900 0.09777 0.09162 -0.0275 0.0716 1.0000
15.750 1.2514 0.10588 0.10000 -0.0307 0.0725 1.0000
16.000 1.2114 0.11527 0.10962 -0.0354 0.0736 1.0000
16.250 1.1716 0.12604 0.12057 -0.0414 0.0749 1.0000
16.500 1.1389 0.13702 0.13164 -0.0476 0.0762 1.0000
16.750 1.1214 0.14621 0.14088 -0.0521 0.0771 1.0000
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