GOE 481A AIRFOIL (goe481a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 481A AIRFOIL (goe481a-il) Reynolds number: 200,000 Max Cl/Cd: 63.81 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe481a-il-200000.txt Download as CSV file: xf-goe481a-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 481A 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.1628 0.09941 0.09570 -0.0596 0.9529 0.0941
-7.000 -0.1450 0.09639 0.09267 -0.0625 0.9480 0.0958
-6.750 -0.2023 0.09038 0.08663 -0.0766 0.9323 0.1006
-6.500 -0.1825 0.08779 0.08408 -0.0738 0.9271 0.1009
-6.250 -0.1566 0.08545 0.08175 -0.0724 0.9228 0.1016
-6.000 -0.1285 0.08269 0.07900 -0.0739 0.9196 0.1027
-5.750 -0.1089 0.07976 0.07606 -0.0762 0.9144 0.1044
-5.500 -0.1158 0.07107 0.06717 -0.0899 0.9020 0.1106
-5.250 -0.1071 0.06928 0.06543 -0.0867 0.8915 0.1111
-5.000 -0.0777 0.06691 0.06308 -0.0874 0.8885 0.1122
-4.750 -0.0468 0.06375 0.05989 -0.0906 0.8860 0.1142
-4.500 -0.0405 0.06094 0.05703 -0.0904 0.8735 0.1168
-4.250 -0.0168 0.05401 0.04978 -0.0984 0.8694 0.1218
-4.000 -0.0503 0.03689 0.03140 -0.0972 0.8548 0.0925
-3.750 -0.0236 0.03238 0.02645 -0.0980 0.8524 0.0907
-3.500 -0.0155 0.02989 0.02364 -0.0946 0.8400 0.0905
-3.250 0.0117 0.02643 0.01957 -0.0945 0.8369 0.0913
-3.000 0.0493 0.02457 0.01754 -0.0959 0.8348 0.0930
-2.750 0.0670 0.02389 0.01684 -0.0935 0.8221 0.0941
-2.500 0.1070 0.02253 0.01536 -0.0952 0.8184 0.0958
-2.250 0.1307 0.02138 0.01403 -0.0938 0.8069 0.0972
-2.000 0.1709 0.01987 0.01219 -0.0955 0.8006 0.1000
-1.750 0.2025 0.01912 0.01143 -0.0957 0.7884 0.1024
-1.500 0.2533 0.01824 0.01049 -0.0996 0.7803 0.1061
-1.250 0.2879 0.01749 0.00951 -0.1004 0.7653 0.1099
-1.000 0.3295 0.01693 0.00897 -0.1028 0.7504 0.1136
-0.750 0.3721 0.01650 0.00833 -0.1052 0.7348 0.1201
-0.500 0.4133 0.01619 0.00799 -0.1076 0.7189 0.1259
-0.250 0.4519 0.01594 0.00757 -0.1095 0.7033 0.1345
0.000 0.4778 0.01594 0.00746 -0.1088 0.6877 0.1433
0.250 0.5046 0.01582 0.00732 -0.1084 0.6735 0.1529
0.500 0.5361 0.01571 0.00712 -0.1090 0.6605 0.1644
0.750 0.5586 0.01581 0.00709 -0.1076 0.6476 0.1739
1.000 0.5836 0.01566 0.00698 -0.1070 0.6361 0.1830
1.250 0.6113 0.01569 0.00689 -0.1068 0.6254 0.1916
1.500 0.6325 0.01565 0.00690 -0.1053 0.6150 0.1993
1.750 0.6596 0.01574 0.00689 -0.1050 0.6050 0.2073
2.000 0.6790 0.01571 0.00692 -0.1032 0.5949 0.2150
2.250 0.7031 0.01581 0.00696 -0.1022 0.5851 0.2246
2.500 0.7225 0.01583 0.00702 -0.1004 0.5755 0.2329
2.750 0.7430 0.01589 0.00707 -0.0987 0.5660 0.2406
3.000 0.7646 0.01600 0.00714 -0.0973 0.5567 0.2481
3.250 0.7807 0.01602 0.00723 -0.0947 0.5475 0.2570
3.500 0.8064 0.01613 0.00730 -0.0942 0.5390 0.2699
3.750 0.9750 0.01558 0.00834 -0.1249 0.5207 1.0000
4.000 0.9837 0.01574 0.00850 -0.1208 0.5121 1.0000
4.250 1.0034 0.01597 0.00859 -0.1190 0.5038 1.0000
4.500 1.0211 0.01621 0.00877 -0.1168 0.4957 1.0000
4.750 1.0362 0.01642 0.00893 -0.1141 0.4876 1.0000
5.000 1.0604 0.01671 0.00907 -0.1133 0.4798 1.0000
5.250 1.0715 0.01691 0.00930 -0.1098 0.4718 1.0000
5.500 1.0904 0.01715 0.00945 -0.1080 0.4644 1.0000
5.750 1.1096 0.01743 0.00969 -0.1062 0.4573 1.0000
6.000 1.1245 0.01768 0.00994 -0.1036 0.4500 1.0000
6.250 1.1461 0.01796 0.01012 -0.1024 0.4433 1.0000
6.500 1.1628 0.01825 0.01042 -0.1002 0.4366 1.0000
6.750 1.1779 0.01852 0.01069 -0.0977 0.4295 1.0000
7.000 1.2003 0.01883 0.01087 -0.0966 0.4230 1.0000
7.250 1.2132 0.01913 0.01124 -0.0938 0.4161 1.0000
7.500 1.2285 0.01943 0.01154 -0.0915 0.4094 1.0000
7.750 1.2522 0.01978 0.01175 -0.0907 0.4030 1.0000
8.000 1.2628 0.02011 0.01219 -0.0876 0.3964 1.0000
8.250 1.2777 0.02045 0.01253 -0.0852 0.3897 1.0000
8.500 1.2969 0.02082 0.01281 -0.0838 0.3829 1.0000
8.750 1.3065 0.02121 0.01328 -0.0806 0.3755 1.0000
9.000 1.3209 0.02159 0.01360 -0.0782 0.3681 1.0000
9.250 1.3330 0.02204 0.01409 -0.0756 0.3605 1.0000
9.500 1.3436 0.02249 0.01456 -0.0728 0.3527 1.0000
9.750 1.3588 0.02299 0.01498 -0.0708 0.3453 1.0000
10.000 1.3665 0.02353 0.01561 -0.0677 0.3370 1.0000
10.250 1.3801 0.02408 0.01605 -0.0655 0.3289 1.0000
10.500 1.3865 0.02473 0.01682 -0.0623 0.3205 1.0000
10.750 1.3962 0.02540 0.01741 -0.0598 0.3119 1.0000
11.000 1.4028 0.02616 0.01826 -0.0568 0.3029 1.0000
11.250 1.4117 0.02694 0.01898 -0.0543 0.2946 1.0000
11.500 1.4183 0.02783 0.01994 -0.0516 0.2857 1.0000
11.750 1.4249 0.02876 0.02081 -0.0490 0.2772 1.0000
12.000 1.4310 0.02976 0.02188 -0.0465 0.2686 1.0000
12.250 1.4374 0.03080 0.02288 -0.0441 0.2610 1.0000
12.500 1.4445 0.03190 0.02401 -0.0419 0.2539 1.0000
12.750 1.4509 0.03304 0.02519 -0.0397 0.2469 1.0000
13.000 1.4583 0.03421 0.02629 -0.0377 0.2412 1.0000
13.250 1.4645 0.03548 0.02767 -0.0358 0.2349 1.0000
13.500 1.4709 0.03677 0.02895 -0.0340 0.2296 1.0000
13.750 1.4784 0.03805 0.03021 -0.0323 0.2247 1.0000
14.000 1.4841 0.03949 0.03177 -0.0306 0.2197 1.0000
14.250 1.4890 0.04100 0.03330 -0.0290 0.2148 1.0000
14.500 1.4973 0.04231 0.03451 -0.0276 0.2102 1.0000
14.750 1.5001 0.04410 0.03646 -0.0262 0.2057 1.0000
15.000 1.5031 0.04592 0.03834 -0.0248 0.2010 1.0000
15.250 1.5089 0.04750 0.03987 -0.0236 0.1965 1.0000
15.500 1.5118 0.04943 0.04188 -0.0224 0.1921 1.0000
15.750 1.5125 0.05160 0.04416 -0.0213 0.1875 1.0000
16.000 1.5158 0.05352 0.04605 -0.0203 0.1829 1.0000
16.250 1.5195 0.05547 0.04803 -0.0193 0.1783 1.0000
16.500 1.5167 0.05816 0.05085 -0.0186 0.1736 1.0000
16.750 1.5183 0.06035 0.05303 -0.0178 0.1690 1.0000
17.000 1.5210 0.06247 0.05515 -0.0170 0.1641 1.0000
17.250 1.5158 0.06560 0.05841 -0.0166 0.1595 1.0000
17.500 1.5175 0.06787 0.06067 -0.0161 0.1550 1.0000
17.750 1.5172 0.07043 0.06325 -0.0156 0.1503 1.0000
18.000 1.5113 0.07377 0.06673 -0.0155 0.1463 1.0000
18.250 1.5114 0.07638 0.06935 -0.0154 0.1425 1.0000
18.500 1.5182 0.07808 0.07099 -0.0149 0.1387 1.0000
18.750 1.5071 0.08228 0.07540 -0.0154 0.1355 1.0000
19.000 1.5038 0.08547 0.07868 -0.0157 0.1324 1.0000
19.250 1.5058 0.08791 0.08112 -0.0158 0.1296 1.0000
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