GOE 514 AIRFOIL (goe514-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 514 AIRFOIL (goe514-il) Reynolds number: 100,000 Max Cl/Cd: 45.3 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe514-il-100000.txt Download as CSV file: xf-goe514-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 514 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3012 0.11193 0.10796 -0.0466 0.9607 0.1425
-8.000 -0.3306 0.10903 0.10510 -0.0505 0.9496 0.1430
-7.750 -0.4379 0.08106 0.07695 -0.0572 0.9428 0.0806
-7.500 -0.4560 0.07423 0.06998 -0.0569 0.9326 0.0791
-7.250 -0.4798 0.06219 0.05748 -0.0587 0.9262 0.0780
-7.000 -0.5105 0.05349 0.04807 -0.0546 0.9151 0.0774
-6.750 -0.5151 0.04643 0.03970 -0.0520 0.9076 0.0799
-6.500 -0.4923 0.04469 0.03806 -0.0515 0.8967 0.0836
-6.250 -0.4724 0.04268 0.03566 -0.0504 0.8875 0.0889
-6.000 -0.4446 0.04158 0.03450 -0.0504 0.8797 0.0961
-5.750 -0.4252 0.03990 0.03238 -0.0489 0.8719 0.1042
-5.500 -0.3970 0.03981 0.03227 -0.0488 0.8637 0.1145
-5.250 -0.3674 0.04021 0.03287 -0.0489 0.8556 0.1238
-5.000 -0.3394 0.04012 0.03275 -0.0487 0.8472 0.1349
-4.750 -0.3129 0.03973 0.03220 -0.0482 0.8396 0.1466
-4.500 -0.2871 0.03927 0.03146 -0.0475 0.8310 0.1587
-4.250 -0.2562 0.03957 0.03205 -0.0478 0.8231 0.1676
-4.000 -0.2291 0.03854 0.03077 -0.0473 0.8148 0.1786
-3.750 -0.2010 0.03809 0.03020 -0.0468 0.8066 0.1894
-3.500 -0.1688 0.03769 0.02984 -0.0471 0.7985 0.1993
-3.250 -0.1431 0.03685 0.02878 -0.0462 0.7896 0.2111
-3.000 -0.1090 0.03616 0.02793 -0.0465 0.7823 0.2260
-2.750 -0.0814 0.03599 0.02785 -0.0459 0.7728 0.2361
-2.500 -0.0445 0.03518 0.02695 -0.0466 0.7660 0.2500
-2.250 -0.0168 0.03451 0.02610 -0.0459 0.7569 0.2626
-2.000 0.0213 0.03360 0.02509 -0.0467 0.7501 0.2744
-1.750 0.0704 0.03211 0.02352 -0.0492 0.7472 0.2860
-1.500 0.0909 0.03167 0.02283 -0.0473 0.7350 0.2947
-1.250 0.1411 0.03008 0.02127 -0.0501 0.7318 0.3061
-1.000 0.1710 0.02929 0.02037 -0.0497 0.7215 0.3162
-0.750 0.2234 0.02780 0.01871 -0.0530 0.7162 0.3274
-0.500 0.2954 0.02580 0.01660 -0.0600 0.7127 0.3367
-0.250 0.3276 0.02516 0.01579 -0.0602 0.6986 0.3443
0.000 0.3731 0.02423 0.01477 -0.0629 0.6855 0.3520
0.250 0.4282 0.02340 0.01372 -0.0675 0.6720 0.3630
0.500 0.4812 0.02266 0.01289 -0.0721 0.6569 0.3754
0.750 0.5250 0.02218 0.01230 -0.0749 0.6411 0.3891
1.000 0.5649 0.02184 0.01188 -0.0771 0.6254 0.4051
1.250 0.5965 0.02168 0.01170 -0.0779 0.6096 0.4216
1.500 0.6302 0.02159 0.01160 -0.0791 0.5946 0.4397
1.750 0.6613 0.02153 0.01152 -0.0799 0.5812 0.4587
2.000 0.6942 0.02135 0.01134 -0.0810 0.5703 0.4831
2.250 0.7118 0.02109 0.01131 -0.0791 0.5599 0.5243
2.500 0.9828 0.02214 0.01298 -0.1279 0.5335 1.0000
2.750 1.0042 0.02247 0.01315 -0.1268 0.5253 1.0000
3.000 1.0232 0.02288 0.01346 -0.1253 0.5180 1.0000
3.250 1.0403 0.02329 0.01380 -0.1235 0.5108 1.0000
3.500 1.0708 0.02364 0.01393 -0.1242 0.5047 1.0000
3.750 1.0770 0.02417 0.01453 -0.1203 0.4980 1.0000
4.000 1.0983 0.02456 0.01482 -0.1193 0.4919 1.0000
4.250 1.1229 0.02501 0.01515 -0.1189 0.4863 1.0000
4.500 1.1299 0.02559 0.01579 -0.1153 0.4807 1.0000
4.750 1.1495 0.02607 0.01623 -0.1140 0.4757 1.0000
5.000 1.1840 0.02653 0.01653 -0.1155 0.4712 1.0000
5.250 1.1852 0.02724 0.01737 -0.1109 0.4665 1.0000
5.500 1.1948 0.02786 0.01805 -0.1078 0.4616 1.0000
5.750 1.2175 0.02837 0.01849 -0.1071 0.4571 1.0000
6.000 1.2476 0.02899 0.01901 -0.1079 0.4530 1.0000
6.250 1.2438 0.02985 0.02003 -0.1024 0.4491 1.0000
6.500 1.2494 0.03064 0.02092 -0.0988 0.4452 1.0000
6.750 1.2658 0.03133 0.02162 -0.0970 0.4413 1.0000
7.000 1.2973 0.03195 0.02215 -0.0981 0.4377 1.0000
7.250 1.3004 0.03294 0.02324 -0.0941 0.4341 1.0000
7.500 1.2904 0.03403 0.02450 -0.0878 0.4304 1.0000
7.750 1.2935 0.03498 0.02553 -0.0839 0.4266 1.0000
8.000 1.3097 0.03580 0.02637 -0.0823 0.4232 1.0000
8.250 1.3443 0.03649 0.02702 -0.0840 0.4200 1.0000
8.500 1.3337 0.03791 0.02858 -0.0779 0.4170 1.0000
8.750 1.2918 0.03964 0.03049 -0.0666 0.4139 1.0000
9.000 1.2602 0.04147 0.03247 -0.0577 0.4106 1.0000
9.250 1.2608 0.04279 0.03386 -0.0541 0.4071 1.0000
9.500 1.2943 0.04333 0.03439 -0.0554 0.4040 1.0000
9.750 1.3220 0.04433 0.03538 -0.0560 0.4007 1.0000
10.000 0.7202 0.10319 0.09506 -0.0261 0.3835 1.0000
10.250 0.7036 0.10934 0.10127 -0.0267 0.3835 1.0000
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Polar data table (+)
Polar graphs
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