GOE 363 AIRFOIL (goe363-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 363 AIRFOIL (goe363-il) Reynolds number: 200,000 Max Cl/Cd: 65.31 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe363-il-200000-n5.txt Download as CSV file: xf-goe363-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 363 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1810 0.08986 0.08652 -0.0581 0.9692 0.0196
-8.500 -0.1693 0.08520 0.08186 -0.0628 0.9621 0.0197
-8.250 -0.1642 0.07976 0.07643 -0.0677 0.9505 0.0201
-8.000 -0.1564 0.07608 0.07276 -0.0708 0.9392 0.0208
-7.750 -0.1409 0.07442 0.07109 -0.0723 0.9310 0.0217
-7.500 -0.1314 0.07095 0.06762 -0.0757 0.9203 0.0222
-7.250 -0.1210 0.06631 0.06295 -0.0810 0.9100 0.0224
-7.000 -0.1072 0.06096 0.05755 -0.0875 0.9013 0.0227
-6.750 -0.0921 0.05488 0.05138 -0.0948 0.8912 0.0231
-6.500 -0.0792 0.03028 0.02557 -0.1174 0.8800 0.0258
-6.250 -0.0576 0.02608 0.02074 -0.1191 0.8736 0.0269
-6.000 -0.0334 0.02464 0.01913 -0.1194 0.8670 0.0279
-5.750 -0.0077 0.02355 0.01784 -0.1195 0.8616 0.0296
-5.500 0.0191 0.02197 0.01588 -0.1198 0.8574 0.0314
-5.250 0.0447 0.02054 0.01407 -0.1197 0.8513 0.0327
-5.000 0.0720 0.01961 0.01278 -0.1196 0.8460 0.0341
-4.750 0.0984 0.01818 0.01118 -0.1197 0.8411 0.0359
-4.500 0.1248 0.01740 0.01028 -0.1194 0.8344 0.0371
-4.250 0.1524 0.01671 0.00943 -0.1192 0.8284 0.0386
-4.000 0.1792 0.01616 0.00874 -0.1188 0.8205 0.0405
-3.750 0.2068 0.01557 0.00798 -0.1184 0.8123 0.0418
-3.500 0.2331 0.01506 0.00736 -0.1179 0.8014 0.0427
-3.250 0.2601 0.01462 0.00679 -0.1174 0.7907 0.0436
-3.000 0.2870 0.01409 0.00617 -0.1169 0.7799 0.0454
-2.750 0.3134 0.01371 0.00576 -0.1165 0.7675 0.0477
-2.500 0.3402 0.01342 0.00538 -0.1160 0.7551 0.0496
-2.250 0.3671 0.01316 0.00503 -0.1156 0.7418 0.0517
-2.000 0.3941 0.01294 0.00472 -0.1151 0.7275 0.0541
-1.750 0.4210 0.01269 0.00444 -0.1147 0.7132 0.0590
-1.500 0.4479 0.01245 0.00423 -0.1143 0.6977 0.0733
-1.250 0.4745 0.01230 0.00418 -0.1139 0.6793 0.1196
-1.000 0.5011 0.01229 0.00407 -0.1134 0.6577 0.1404
-0.750 0.5272 0.01231 0.00397 -0.1128 0.6326 0.1552
-0.500 0.5528 0.01237 0.00385 -0.1122 0.6063 0.1658
0.000 0.6028 0.01258 0.00377 -0.1108 0.5564 0.1862
0.250 0.6276 0.01269 0.00381 -0.1102 0.5354 0.2058
0.500 0.6525 0.01279 0.00388 -0.1096 0.5161 0.2339
0.750 0.6776 0.01287 0.00397 -0.1091 0.4972 0.2719
1.000 0.7027 0.01291 0.00405 -0.1086 0.4780 0.3252
1.250 0.7243 0.01233 0.00420 -0.1077 0.4585 0.6090
1.750 0.7763 0.01219 0.00437 -0.1064 0.4088 1.0000
2.000 0.7996 0.01256 0.00449 -0.1056 0.3791 1.0000
2.250 0.8226 0.01296 0.00466 -0.1047 0.3531 1.0000
2.500 0.8457 0.01335 0.00486 -0.1040 0.3332 1.0000
2.750 0.8694 0.01372 0.00508 -0.1033 0.3182 1.0000
3.000 0.8935 0.01406 0.00530 -0.1027 0.3068 1.0000
3.250 0.9174 0.01440 0.00554 -0.1021 0.2975 1.0000
3.500 0.9417 0.01472 0.00578 -0.1015 0.2895 1.0000
3.750 0.9656 0.01505 0.00604 -0.1009 0.2833 1.0000
4.000 0.9901 0.01535 0.00629 -0.1003 0.2775 1.0000
4.250 1.0139 0.01568 0.00658 -0.0997 0.2723 1.0000
4.500 1.0375 0.01603 0.00688 -0.0991 0.2679 1.0000
4.750 1.0619 0.01632 0.00716 -0.0986 0.2634 1.0000
5.000 1.0855 0.01666 0.00747 -0.0979 0.2584 1.0000
5.250 1.1082 0.01704 0.00782 -0.0972 0.2540 1.0000
5.500 1.1318 0.01738 0.00815 -0.0966 0.2505 1.0000
5.750 1.1553 0.01769 0.00849 -0.0960 0.2463 1.0000
6.000 1.1780 0.01806 0.00886 -0.0953 0.2419 1.0000
6.250 1.1997 0.01848 0.00925 -0.0944 0.2380 1.0000
6.500 1.2224 0.01883 0.00963 -0.0937 0.2343 1.0000
6.750 1.2450 0.01917 0.01004 -0.0930 0.2305 1.0000
7.000 1.2666 0.01956 0.01045 -0.0921 0.2267 1.0000
7.250 1.2872 0.02000 0.01090 -0.0912 0.2232 1.0000
7.500 1.3071 0.02044 0.01136 -0.0901 0.2200 1.0000
7.750 1.3279 0.02080 0.01182 -0.0891 0.2156 1.0000
8.000 1.3465 0.02123 0.01228 -0.0878 0.2092 1.0000
8.250 1.3643 0.02170 0.01277 -0.0865 0.2011 1.0000
8.500 1.3815 0.02221 0.01328 -0.0851 0.1917 1.0000
8.750 1.3999 0.02269 0.01382 -0.0840 0.1822 1.0000
9.000 1.4167 0.02326 0.01440 -0.0827 0.1712 1.0000
9.250 1.4317 0.02396 0.01506 -0.0812 0.1560 1.0000
9.500 1.4435 0.02489 0.01589 -0.0795 0.1411 1.0000
9.750 1.4535 0.02599 0.01691 -0.0776 0.1294 1.0000
10.000 1.4624 0.02722 0.01810 -0.0757 0.1189 1.0000
10.250 1.4704 0.02854 0.01940 -0.0738 0.1110 1.0000
10.500 1.4816 0.02965 0.02055 -0.0723 0.1022 1.0000
10.750 1.4906 0.03096 0.02187 -0.0707 0.0896 1.0000
11.250 1.4675 0.03726 0.02781 -0.0652 0.0198 1.0000
11.500 1.4706 0.03928 0.02994 -0.0637 0.0177 1.0000
11.750 1.4750 0.04124 0.03204 -0.0624 0.0167 1.0000
12.000 1.4776 0.04343 0.03441 -0.0613 0.0157 1.0000
12.250 1.4778 0.04592 0.03707 -0.0602 0.0149 1.0000
12.500 1.4754 0.04879 0.04011 -0.0593 0.0142 1.0000
12.750 1.4702 0.05210 0.04361 -0.0585 0.0136 1.0000
13.000 1.4674 0.05527 0.04695 -0.0581 0.0133 1.0000
13.250 1.4638 0.05870 0.05056 -0.0580 0.0130 1.0000
13.500 1.4582 0.06256 0.05461 -0.0582 0.0128 1.0000
13.750 1.4506 0.06689 0.05913 -0.0587 0.0125 1.0000
14.000 1.4410 0.07169 0.06411 -0.0596 0.0124 1.0000
14.250 1.4293 0.07701 0.06962 -0.0609 0.0122 1.0000
14.500 1.4154 0.08283 0.07563 -0.0625 0.0121 1.0000
14.750 1.3994 0.08914 0.08213 -0.0644 0.0120 1.0000
15.000 1.3815 0.09594 0.08912 -0.0666 0.0119 1.0000
15.250 1.3623 0.10318 0.09654 -0.0692 0.0119 1.0000
15.500 1.3422 0.11074 0.10429 -0.0720 0.0119 1.0000
15.750 1.3222 0.11849 0.11221 -0.0751 0.0119 1.0000
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Polar data table (+)
Polar graphs
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