GOE 685 AIRFOIL (goe685-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 685 AIRFOIL (goe685-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.21 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe685-il-1000000.txt Download as CSV file: xf-goe685-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 685 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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.7724 0.11251 0.11014 -0.0446 1.0000 0.0226
-17.250 -0.7971 0.10407 0.10157 -0.0496 1.0000 0.0228
-17.000 -0.8157 0.09698 0.09437 -0.0539 1.0000 0.0229
-16.750 -0.8390 0.08982 0.08710 -0.0581 1.0000 0.0232
-16.500 -0.8482 0.08499 0.08222 -0.0608 1.0000 0.0234
-16.250 -0.8525 0.08097 0.07817 -0.0631 1.0000 0.0237
-16.000 -0.8588 0.07663 0.07378 -0.0656 1.0000 0.0238
-15.750 -0.8651 0.07243 0.06954 -0.0680 1.0000 0.0240
-15.500 -0.8713 0.06828 0.06534 -0.0705 1.0000 0.0241
-15.250 -0.8809 0.06390 0.06091 -0.0731 1.0000 0.0243
-15.000 -0.8913 0.05969 0.05665 -0.0756 1.0000 0.0244
-14.750 -0.9023 0.05540 0.05232 -0.0783 1.0000 0.0246
-14.500 -0.9169 0.05089 0.04774 -0.0810 1.0000 0.0248
-14.250 -0.9352 0.04619 0.04299 -0.0836 1.0000 0.0249
-14.000 -0.9656 0.04093 0.03766 -0.0859 1.0000 0.0249
-13.750 -1.0321 0.03357 0.03019 -0.0871 1.0000 0.0245
-13.500 -1.0081 0.02954 0.02598 -0.0939 0.9984 0.0249
-13.250 -0.9807 0.02746 0.02378 -0.0978 0.9959 0.0254
-13.000 -0.9525 0.02579 0.02200 -0.1008 0.9936 0.0258
-12.750 -0.9268 0.02449 0.02059 -0.1026 0.9906 0.0262
-12.500 -0.8987 0.02344 0.01945 -0.1043 0.9879 0.0265
-12.250 -0.8679 0.02267 0.01858 -0.1060 0.9859 0.0268
-12.000 -0.8430 0.02064 0.01644 -0.1082 0.9835 0.0275
-11.750 -0.8128 0.01955 0.01529 -0.1101 0.9822 0.0280
-11.500 -0.7858 0.01873 0.01444 -0.1109 0.9789 0.0285
-11.250 -0.7562 0.01799 0.01364 -0.1120 0.9761 0.0289
-11.000 -0.7258 0.01730 0.01289 -0.1132 0.9735 0.0294
-10.750 -0.6946 0.01670 0.01223 -0.1144 0.9712 0.0301
-10.500 -0.6625 0.01609 0.01155 -0.1158 0.9689 0.0306
-10.250 -0.6369 0.01560 0.01099 -0.1156 0.9636 0.0309
-10.000 -0.6096 0.01513 0.01046 -0.1158 0.9588 0.0312
-9.750 -0.5833 0.01424 0.00948 -0.1161 0.9542 0.0318
-9.500 -0.5609 0.01359 0.00878 -0.1154 0.9479 0.0326
-9.250 -0.5358 0.01312 0.00826 -0.1150 0.9422 0.0332
-9.000 -0.5094 0.01271 0.00779 -0.1148 0.9366 0.0339
-8.750 -0.4854 0.01233 0.00736 -0.1141 0.9294 0.0344
-8.500 -0.4595 0.01198 0.00693 -0.1137 0.9224 0.0351
-8.250 -0.4342 0.01165 0.00655 -0.1131 0.9151 0.0356
-8.000 -0.4083 0.01136 0.00618 -0.1126 0.9075 0.0361
-7.750 -0.3831 0.01094 0.00568 -0.1120 0.8999 0.0370
-7.500 -0.3578 0.01054 0.00524 -0.1115 0.8912 0.0383
-7.250 -0.3315 0.01025 0.00489 -0.1111 0.8835 0.0394
-7.000 -0.3050 0.00998 0.00458 -0.1107 0.8748 0.0406
-6.750 -0.2781 0.00977 0.00429 -0.1103 0.8670 0.0417
-6.500 -0.2517 0.00945 0.00393 -0.1099 0.8578 0.0439
-6.250 -0.2251 0.00919 0.00364 -0.1095 0.8484 0.0466
-6.000 -0.1986 0.00892 0.00334 -0.1091 0.8369 0.0515
-5.750 -0.1724 0.00858 0.00301 -0.1086 0.8242 0.0640
-5.500 -0.1471 0.00811 0.00265 -0.1082 0.8109 0.0944
-5.250 -0.1210 0.00785 0.00245 -0.1077 0.7968 0.1200
-5.000 -0.0942 0.00776 0.00233 -0.1073 0.7819 0.1326
-4.750 -0.0674 0.00769 0.00222 -0.1069 0.7669 0.1421
-4.500 -0.0401 0.00765 0.00213 -0.1066 0.7530 0.1482
-4.250 -0.0128 0.00759 0.00205 -0.1063 0.7410 0.1549
-4.000 0.0147 0.00759 0.00198 -0.1059 0.7302 0.1595
-3.750 0.0420 0.00753 0.00189 -0.1056 0.7195 0.1658
-3.500 0.0696 0.00750 0.00183 -0.1054 0.7094 0.1714
-3.000 0.1244 0.00745 0.00172 -0.1048 0.6869 0.1832
-2.750 0.1518 0.00744 0.00167 -0.1045 0.6759 0.1889
-2.500 0.1791 0.00743 0.00162 -0.1041 0.6645 0.1960
-2.250 0.2068 0.00740 0.00160 -0.1039 0.6533 0.2037
-2.000 0.2341 0.00739 0.00157 -0.1036 0.6424 0.2123
-1.750 0.2615 0.00740 0.00155 -0.1033 0.6303 0.2198
-1.500 0.2891 0.00739 0.00153 -0.1031 0.6187 0.2267
-1.250 0.3165 0.00741 0.00152 -0.1027 0.6063 0.2342
-1.000 0.3437 0.00746 0.00151 -0.1024 0.5928 0.2405
-0.750 0.3706 0.00749 0.00152 -0.1020 0.5777 0.2478
-0.500 0.3975 0.00757 0.00154 -0.1016 0.5602 0.2536
-0.250 0.4241 0.00764 0.00155 -0.1012 0.5410 0.2595
0.000 0.4508 0.00773 0.00158 -0.1008 0.5236 0.2656
0.250 0.4775 0.00783 0.00162 -0.1004 0.5071 0.2706
0.500 0.5041 0.00793 0.00166 -0.1000 0.4914 0.2756
1.000 0.5576 0.00811 0.00177 -0.0993 0.4647 0.2868
1.250 0.5845 0.00821 0.00182 -0.0989 0.4541 0.2910
1.750 0.6381 0.00835 0.00195 -0.0982 0.4359 0.3019
2.000 0.6648 0.00846 0.00202 -0.0978 0.4277 0.3061
2.250 0.6917 0.00852 0.00208 -0.0975 0.4200 0.3114
2.500 0.7182 0.00861 0.00216 -0.0971 0.4115 0.3174
2.750 0.7451 0.00869 0.00224 -0.0968 0.4047 0.3229
3.000 0.7719 0.00876 0.00231 -0.0964 0.3981 0.3290
3.250 0.7981 0.00887 0.00241 -0.0960 0.3914 0.3355
3.500 0.8253 0.00892 0.00249 -0.0957 0.3858 0.3413
3.750 0.8515 0.00900 0.00259 -0.0953 0.3791 0.3501
4.250 0.9046 0.00914 0.00279 -0.0946 0.3681 0.3722
4.500 0.9298 0.00926 0.00291 -0.0940 0.3584 0.3875
4.750 0.9559 0.00932 0.00302 -0.0936 0.3486 0.4089
5.000 0.9808 0.00938 0.00316 -0.0930 0.3376 0.4495
5.250 1.0192 0.00855 0.00349 -0.0956 0.3244 1.0000
5.500 1.0432 0.00878 0.00363 -0.0948 0.3089 1.0000
5.750 1.0665 0.00905 0.00381 -0.0939 0.2889 1.0000
6.000 1.0879 0.00944 0.00405 -0.0927 0.2631 1.0000
6.250 1.1060 0.01004 0.00441 -0.0909 0.2206 1.0000
6.500 1.1233 0.01068 0.00484 -0.0891 0.1862 1.0000
6.750 1.1443 0.01107 0.00515 -0.0879 0.1733 1.0000
7.000 1.1665 0.01137 0.00542 -0.0868 0.1664 1.0000
7.250 1.1880 0.01170 0.00571 -0.0856 0.1588 1.0000
7.500 1.2110 0.01192 0.00594 -0.0847 0.1547 1.0000
7.750 1.2322 0.01224 0.00624 -0.0835 0.1482 1.0000
8.000 1.2537 0.01253 0.00651 -0.0824 0.1410 1.0000
8.250 1.2732 0.01291 0.00682 -0.0809 0.1284 1.0000
8.500 1.2779 0.01393 0.00753 -0.0770 0.0793 1.0000
8.750 1.2905 0.01447 0.00805 -0.0744 0.0700 1.0000
9.000 1.3032 0.01501 0.00857 -0.0718 0.0630 1.0000
9.250 1.3175 0.01550 0.00904 -0.0695 0.0564 1.0000
9.500 1.3315 0.01602 0.00954 -0.0673 0.0499 1.0000
9.750 1.3451 0.01657 0.01007 -0.0650 0.0451 1.0000
10.000 1.3580 0.01717 0.01065 -0.0628 0.0412 1.0000
10.250 1.3721 0.01773 0.01122 -0.0608 0.0390 1.0000
10.500 1.3857 0.01833 0.01184 -0.0589 0.0372 1.0000
10.750 1.3976 0.01904 0.01256 -0.0567 0.0355 1.0000
11.000 1.4087 0.01982 0.01337 -0.0546 0.0341 1.0000
11.250 1.4222 0.02049 0.01409 -0.0529 0.0333 1.0000
11.500 1.4346 0.02125 0.01488 -0.0511 0.0323 1.0000
11.750 1.4454 0.02214 0.01579 -0.0493 0.0312 1.0000
12.000 1.4539 0.02321 0.01690 -0.0473 0.0303 1.0000
12.250 1.4591 0.02454 0.01829 -0.0452 0.0292 1.0000
12.500 1.4703 0.02554 0.01934 -0.0438 0.0288 1.0000
12.750 1.4807 0.02662 0.02048 -0.0424 0.0282 1.0000
13.000 1.4899 0.02784 0.02174 -0.0410 0.0274 1.0000
13.250 1.4979 0.02921 0.02316 -0.0397 0.0268 1.0000
13.500 1.5031 0.03087 0.02487 -0.0384 0.0262 1.0000
13.750 1.5055 0.03285 0.02690 -0.0372 0.0255 1.0000
14.000 1.5021 0.03548 0.02961 -0.0359 0.0249 1.0000
14.250 1.5101 0.03711 0.03132 -0.0352 0.0246 1.0000
14.500 1.5152 0.03909 0.03336 -0.0346 0.0242 1.0000
14.750 1.5198 0.04118 0.03553 -0.0340 0.0238 1.0000
15.000 1.5234 0.04343 0.03784 -0.0335 0.0233 1.0000
15.250 1.5269 0.04573 0.04020 -0.0332 0.0228 1.0000
15.500 1.5272 0.04847 0.04301 -0.0330 0.0224 1.0000
15.750 1.5256 0.05150 0.04610 -0.0329 0.0220 1.0000
16.000 1.5213 0.05492 0.04960 -0.0329 0.0216 1.0000
16.250 1.5100 0.05933 0.05410 -0.0333 0.0211 1.0000
16.500 1.5061 0.06294 0.05779 -0.0337 0.0209 1.0000
16.750 1.5066 0.06604 0.06098 -0.0341 0.0207 1.0000
17.000 1.5046 0.06951 0.06454 -0.0347 0.0204 1.0000
17.250 1.5029 0.07300 0.06811 -0.0353 0.0201 1.0000
17.500 1.5002 0.07671 0.07189 -0.0361 0.0197 1.0000
17.750 1.4974 0.08045 0.07571 -0.0369 0.0194 1.0000
18.000 1.4940 0.08431 0.07964 -0.0379 0.0191 1.0000
18.250 1.4904 0.08828 0.08369 -0.0390 0.0188 1.0000
18.500 1.4853 0.09255 0.08801 -0.0403 0.0185 1.0000
18.750 1.4786 0.09710 0.09263 -0.0417 0.0182 1.0000
19.000 1.4699 0.10199 0.09759 -0.0434 0.0179 1.0000
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