GOE 601 AIRFOIL (goe601-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 601 AIRFOIL (goe601-il) Reynolds number: 50,000 Max Cl/Cd: 28.02 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe601-il-50000-n5.txt Download as CSV file: xf-goe601-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 601 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4671 0.10864 0.10061 -0.0597 1.0000 0.0844
-12.500 -0.5346 0.09166 0.08366 -0.0689 1.0000 0.0834
-12.250 -0.5808 0.08184 0.07380 -0.0736 1.0000 0.0831
-12.000 -0.6229 0.07450 0.06640 -0.0764 1.0000 0.0827
-11.750 -0.6604 0.06916 0.06098 -0.0769 1.0000 0.0825
-11.500 -0.6945 0.06527 0.05699 -0.0755 1.0000 0.0824
-11.250 -0.7274 0.06237 0.05400 -0.0723 1.0000 0.0824
-11.000 -0.7594 0.06029 0.05183 -0.0673 1.0000 0.0824
-10.750 -0.7891 0.05847 0.04990 -0.0617 1.0000 0.0826
-10.500 -0.8129 0.05642 0.04766 -0.0567 1.0000 0.0830
-10.250 -0.8302 0.05444 0.04549 -0.0521 1.0000 0.0836
-10.000 -0.8328 0.05293 0.04395 -0.0488 1.0000 0.0846
-9.750 -0.8358 0.05142 0.04235 -0.0455 1.0000 0.0857
-9.500 -0.8378 0.04994 0.04075 -0.0422 1.0000 0.0871
-9.250 -0.8391 0.04843 0.03908 -0.0390 1.0000 0.0890
-9.000 -0.8396 0.04686 0.03727 -0.0358 1.0000 0.0913
-8.750 -0.8217 0.04472 0.03465 -0.0361 0.9947 0.0951
-8.500 -0.7970 0.04328 0.03322 -0.0368 0.9900 0.0984
-8.250 -0.7729 0.04176 0.03150 -0.0374 0.9850 0.1027
-8.000 -0.7497 0.04025 0.02964 -0.0376 0.9800 0.1084
-7.750 -0.7262 0.03904 0.02852 -0.0379 0.9749 0.1145
-7.500 -0.6999 0.03777 0.02699 -0.0386 0.9705 0.1229
-7.250 -0.6802 0.03665 0.02595 -0.0380 0.9649 0.1307
-7.000 -0.6571 0.03557 0.02483 -0.0381 0.9598 0.1411
-6.750 -0.6345 0.03465 0.02387 -0.0381 0.9548 0.1537
-6.250 -0.5922 0.03313 0.02241 -0.0376 0.9437 0.1832
-6.000 -0.5744 0.03252 0.02190 -0.0367 0.9378 0.2021
-5.750 -0.5544 0.03200 0.02144 -0.0361 0.9319 0.2268
-5.500 -0.5286 0.03148 0.02103 -0.0365 0.9274 0.2562
-5.250 -0.5128 0.03097 0.02057 -0.0349 0.9209 0.2827
-5.000 -0.4905 0.03051 0.02017 -0.0344 0.9155 0.3158
-4.750 -0.4628 0.03018 0.01997 -0.0347 0.9114 0.3518
-4.500 -0.4491 0.03001 0.01990 -0.0324 0.9043 0.3797
-4.250 -0.4247 0.02997 0.01989 -0.0319 0.8991 0.4126
-4.000 -0.3987 0.02999 0.01984 -0.0317 0.8945 0.4431
-3.750 -0.3817 0.02998 0.01974 -0.0301 0.8877 0.4679
-3.500 -0.3540 0.02999 0.01968 -0.0302 0.8829 0.4921
-3.250 -0.3303 0.03002 0.01966 -0.0295 0.8778 0.5172
-3.000 -0.3117 0.03006 0.01968 -0.0280 0.8714 0.5420
-2.750 -0.2840 0.03011 0.01976 -0.0278 0.8669 0.5675
-2.500 -0.2625 0.03019 0.01982 -0.0266 0.8614 0.5907
-2.250 -0.2430 0.03028 0.01992 -0.0252 0.8551 0.6136
-2.000 -0.2142 0.03036 0.02003 -0.0251 0.8507 0.6381
-1.750 -0.1937 0.03048 0.02015 -0.0238 0.8450 0.6613
-1.500 -0.1738 0.03060 0.02026 -0.0224 0.8386 0.6842
-1.250 -0.1432 0.03067 0.02037 -0.0227 0.8343 0.7071
-1.000 -0.1202 0.03082 0.02053 -0.0219 0.8287 0.7282
-0.750 -0.0985 0.03099 0.02072 -0.0209 0.8222 0.7498
-0.500 -0.0656 0.03109 0.02083 -0.0217 0.8177 0.7743
-0.250 -0.0347 0.03131 0.02110 -0.0223 0.8127 0.7985
0.000 -0.0080 0.03165 0.02148 -0.0224 0.8058 0.8254
0.250 0.0377 0.03194 0.02179 -0.0258 0.8014 0.8541
0.500 0.0952 0.03220 0.02205 -0.0311 0.7982 0.8845
0.750 0.1397 0.03271 0.02257 -0.0349 0.7887 0.9142
1.000 0.2115 0.03260 0.02240 -0.0424 0.7826 0.9393
1.250 0.2675 0.03251 0.02227 -0.0477 0.7709 0.9610
1.500 0.3402 0.03173 0.02141 -0.0550 0.7641 0.9763
1.750 0.3898 0.03166 0.02133 -0.0597 0.7524 0.9985
2.000 0.4284 0.03107 0.02068 -0.0615 0.7461 1.0000
2.250 0.4146 0.03138 0.02090 -0.0551 0.7324 1.0000
2.500 0.4231 0.03143 0.02089 -0.0521 0.7214 1.0000
2.750 0.4507 0.03111 0.02053 -0.0517 0.7130 1.0000
3.000 0.4543 0.03136 0.02072 -0.0478 0.6998 1.0000
3.250 0.4760 0.03119 0.02053 -0.0464 0.6896 1.0000
3.500 0.5004 0.03093 0.02025 -0.0453 0.6792 1.0000
4.000 0.5258 0.03103 0.02032 -0.0398 0.6522 1.0000
4.250 0.5554 0.03055 0.01985 -0.0393 0.6416 1.0000
4.500 0.5772 0.03029 0.01960 -0.0376 0.6283 1.0000
4.750 0.5923 0.03027 0.01959 -0.0351 0.6128 1.0000
5.250 0.6297 0.03007 0.01940 -0.0312 0.5804 1.0000
5.500 0.6517 0.02988 0.01921 -0.0296 0.5632 1.0000
5.750 0.6757 0.02967 0.01899 -0.0283 0.5455 1.0000
6.000 0.7014 0.02947 0.01876 -0.0272 0.5275 1.0000
6.250 0.7271 0.02936 0.01858 -0.0263 0.5091 1.0000
6.500 0.7489 0.02950 0.01868 -0.0249 0.4906 1.0000
6.750 0.7716 0.02970 0.01881 -0.0238 0.4731 1.0000
7.000 0.7951 0.02994 0.01898 -0.0228 0.4573 1.0000
7.250 0.8177 0.03030 0.01929 -0.0219 0.4429 1.0000
7.500 0.8363 0.03087 0.01984 -0.0205 0.4293 1.0000
7.750 0.8568 0.03145 0.02040 -0.0195 0.4174 1.0000
8.000 0.8826 0.03189 0.02080 -0.0191 0.4070 1.0000
8.250 0.9017 0.03259 0.02155 -0.0180 0.3967 1.0000
8.500 0.9248 0.03325 0.02223 -0.0174 0.3877 1.0000
8.750 0.9483 0.03392 0.02296 -0.0169 0.3791 1.0000
9.000 0.9716 0.03467 0.02379 -0.0165 0.3713 1.0000
9.250 0.9926 0.03547 0.02468 -0.0157 0.3632 1.0000
9.500 1.0143 0.03624 0.02551 -0.0151 0.3548 1.0000
9.750 1.0303 0.03703 0.02637 -0.0136 0.3447 1.0000
10.000 1.0394 0.03802 0.02745 -0.0114 0.3349 1.0000
10.250 1.0574 0.03858 0.02794 -0.0101 0.3230 1.0000
10.500 1.0563 0.03986 0.02939 -0.0069 0.3133 1.0000
10.750 1.0665 0.04073 0.03030 -0.0049 0.3029 1.0000
11.000 1.0705 0.04171 0.03133 -0.0024 0.2917 1.0000
11.250 1.0649 0.04323 0.03299 0.0006 0.2812 1.0000
11.500 1.0642 0.04439 0.03415 0.0032 0.2691 1.0000
11.750 1.0572 0.04603 0.03588 0.0058 0.2573 1.0000
12.000 1.0486 0.04812 0.03813 0.0081 0.2466 1.0000
12.250 1.0464 0.04983 0.03991 0.0099 0.2358 1.0000
12.500 1.0408 0.05209 0.04235 0.0114 0.2254 1.0000
12.750 1.0343 0.05464 0.04510 0.0126 0.2146 1.0000
13.000 1.0285 0.05719 0.04779 0.0135 0.2026 1.0000
13.250 1.0215 0.06006 0.05079 0.0142 0.1894 1.0000
13.500 1.0118 0.06348 0.05436 0.0145 0.1740 1.0000
13.750 1.0019 0.06719 0.05817 0.0145 0.1575 1.0000
14.000 0.9919 0.07105 0.06201 0.0142 0.1400 1.0000
14.250 0.9822 0.07504 0.06591 0.0138 0.1251 1.0000
14.500 0.9720 0.07935 0.07012 0.0131 0.1136 1.0000
14.750 0.9631 0.08367 0.07436 0.0123 0.1057 1.0000
15.000 0.9545 0.08806 0.07867 0.0113 0.0994 1.0000
15.250 0.9487 0.09223 0.08284 0.0103 0.0944 1.0000
15.500 0.9447 0.09615 0.08676 0.0094 0.0903 1.0000
15.750 0.9443 0.09938 0.08987 0.0088 0.0870 1.0000
16.000 0.9429 0.10321 0.09386 0.0079 0.0842 1.0000
16.250 0.9418 0.10694 0.09769 0.0069 0.0814 1.0000
16.500 0.9433 0.11016 0.10092 0.0061 0.0789 1.0000
16.750 0.9499 0.11231 0.10299 0.0059 0.0765 1.0000
17.000 0.9446 0.11721 0.10811 0.0041 0.0747 1.0000
17.250 0.9374 0.12260 0.11371 0.0018 0.0730 1.0000
17.500 0.9291 0.12833 0.11963 -0.0008 0.0716 1.0000
17.750 0.9168 0.13512 0.12660 -0.0040 0.0706 1.0000
18.000 0.8925 0.14512 0.13679 -0.0092 0.0699 1.0000
18.250 0.8526 0.16025 0.15201 -0.0171 0.0694 1.0000
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