GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 439 AIRFOIL (goe439-il) Reynolds number: 200,000 Max Cl/Cd: 80.62 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe439-il-200000-n5.txt Download as CSV file: xf-goe439-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 439 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2804 0.10206 0.09882 -0.0338 1.0000 0.0208
-8.000 -0.2839 0.09997 0.09680 -0.0327 1.0000 0.0208
-7.750 -0.2862 0.09787 0.09477 -0.0321 0.9992 0.0208
-7.500 -0.2665 0.09340 0.09030 -0.0377 0.9917 0.0208
-7.250 -0.2437 0.08861 0.08551 -0.0441 0.9833 0.0208
-7.000 -0.2209 0.08378 0.08067 -0.0504 0.9749 0.0209
-6.750 -0.1975 0.07915 0.07601 -0.0566 0.9663 0.0209
-6.500 -0.1732 0.07428 0.07111 -0.0628 0.9581 0.0208
-6.250 -0.1637 0.06968 0.06651 -0.0618 0.9514 0.0179
-6.000 -0.1377 0.06468 0.06147 -0.0690 0.9406 0.0159
-5.750 -0.1081 0.05884 0.05557 -0.0778 0.9288 0.0145
-5.500 -0.0733 0.05116 0.04774 -0.0885 0.9162 0.0132
-5.250 -0.0425 0.04647 0.04292 -0.0945 0.9042 0.0134
-5.000 -0.0130 0.04347 0.03980 -0.0984 0.8926 0.0146
-4.750 0.0188 0.03927 0.03539 -0.1030 0.8807 0.0158
-4.500 0.0517 0.03333 0.02910 -0.1077 0.8689 0.0155
-4.250 0.0824 0.02682 0.02205 -0.1108 0.8571 0.0154
-4.000 0.1107 0.02042 0.01477 -0.1121 0.8458 0.0160
-3.750 0.1384 0.01772 0.01140 -0.1122 0.8346 0.0177
-3.500 0.1664 0.01624 0.00943 -0.1120 0.8235 0.0201
-3.000 0.2207 0.01403 0.00667 -0.1114 0.8008 0.0252
-2.750 0.2479 0.01357 0.00598 -0.1110 0.7894 0.0306
-2.500 0.2745 0.01294 0.00522 -0.1106 0.7782 0.0361
-2.250 0.3014 0.01260 0.00470 -0.1102 0.7671 0.0442
-2.000 0.3279 0.01227 0.00428 -0.1099 0.7557 0.0532
-1.750 0.3543 0.01196 0.00384 -0.1094 0.7443 0.0599
-1.500 0.3808 0.01176 0.00358 -0.1090 0.7330 0.0689
-1.250 0.4074 0.01161 0.00340 -0.1086 0.7216 0.0816
-1.000 0.4339 0.01152 0.00322 -0.1082 0.7103 0.1000
-0.750 0.4603 0.01144 0.00309 -0.1078 0.6981 0.1179
-0.500 0.4866 0.01138 0.00298 -0.1074 0.6860 0.1325
-0.250 0.5129 0.01133 0.00287 -0.1071 0.6737 0.1487
0.000 0.5390 0.01127 0.00280 -0.1067 0.6608 0.1694
0.500 0.5879 0.01056 0.00281 -0.1056 0.6341 0.4542
1.000 0.6500 0.00967 0.00272 -0.1066 0.6046 1.0000
1.250 0.6755 0.00982 0.00273 -0.1060 0.5898 1.0000
1.500 0.7009 0.00998 0.00275 -0.1055 0.5754 1.0000
1.750 0.7263 0.01016 0.00279 -0.1049 0.5610 1.0000
2.250 0.7769 0.01053 0.00295 -0.1039 0.5338 1.0000
2.500 0.8022 0.01073 0.00306 -0.1034 0.5208 1.0000
2.750 0.8274 0.01093 0.00319 -0.1029 0.5086 1.0000
3.000 0.8526 0.01114 0.00335 -0.1024 0.4968 1.0000
3.250 0.8777 0.01137 0.00351 -0.1019 0.4856 1.0000
3.750 0.9275 0.01183 0.00390 -0.1008 0.4608 1.0000
4.000 0.9522 0.01206 0.00411 -0.1003 0.4482 1.0000
4.250 0.9768 0.01231 0.00434 -0.0997 0.4357 1.0000
4.500 1.0013 0.01257 0.00458 -0.0991 0.4243 1.0000
4.750 1.0258 0.01283 0.00486 -0.0986 0.4147 1.0000
5.000 1.0507 0.01308 0.00515 -0.0981 0.4050 1.0000
5.250 1.0750 0.01335 0.00545 -0.0975 0.3956 1.0000
5.500 1.0992 0.01364 0.00580 -0.0970 0.3862 1.0000
5.750 1.1231 0.01393 0.00614 -0.0963 0.3746 1.0000
6.000 1.1458 0.01426 0.00648 -0.0955 0.3587 1.0000
6.250 1.1676 0.01465 0.00685 -0.0946 0.3399 1.0000
6.500 1.1874 0.01513 0.00724 -0.0933 0.3075 1.0000
6.750 1.2053 0.01578 0.00775 -0.0919 0.2677 1.0000
7.000 1.2201 0.01672 0.00840 -0.0901 0.2108 1.0000
7.250 1.2186 0.01919 0.00997 -0.0863 0.0822 1.0000
7.500 1.2248 0.02097 0.01148 -0.0832 0.0273 1.0000
7.750 1.2386 0.02199 0.01263 -0.0811 0.0214 1.0000
8.000 1.2535 0.02285 0.01365 -0.0792 0.0178 1.0000
8.250 1.2649 0.02385 0.01480 -0.0768 0.0156 1.0000
8.500 1.2699 0.02514 0.01626 -0.0735 0.0140 1.0000
8.750 1.2680 0.02684 0.01817 -0.0695 0.0131 1.0000
9.000 1.2729 0.02816 0.01965 -0.0667 0.0124 1.0000
9.250 1.2797 0.02941 0.02102 -0.0644 0.0113 1.0000
9.500 1.2822 0.03104 0.02278 -0.0619 0.0106 1.0000
9.750 1.2827 0.03295 0.02481 -0.0595 0.0102 1.0000
10.000 1.2830 0.03502 0.02699 -0.0574 0.0098 1.0000
10.250 1.2832 0.03726 0.02932 -0.0557 0.0094 1.0000
10.500 1.2835 0.03962 0.03178 -0.0541 0.0091 1.0000
10.750 1.2841 0.04211 0.03436 -0.0527 0.0089 1.0000
11.000 1.2849 0.04472 0.03705 -0.0514 0.0086 1.0000
11.250 1.2866 0.04763 0.03998 -0.0498 0.0082 1.0000
11.500 1.2933 0.04968 0.04221 -0.0490 0.0077 1.0000
11.750 1.2996 0.05194 0.04462 -0.0482 0.0072 1.0000
12.000 1.3059 0.05442 0.04726 -0.0472 0.0069 1.0000
12.250 1.3120 0.05705 0.05006 -0.0462 0.0067 1.0000
12.500 1.3169 0.05988 0.05307 -0.0455 0.0065 1.0000
12.750 1.3201 0.06299 0.05636 -0.0448 0.0064 1.0000
13.000 1.3211 0.06634 0.05992 -0.0444 0.0063 1.0000
13.250 1.3197 0.07000 0.06386 -0.0443 0.0062 1.0000
13.500 1.3162 0.07399 0.06806 -0.0445 0.0061 1.0000
13.750 1.3104 0.07835 0.07264 -0.0451 0.0061 1.0000
14.000 1.3030 0.08299 0.07750 -0.0460 0.0060 1.0000
14.250 1.2937 0.08810 0.08283 -0.0474 0.0060 1.0000
14.500 1.2830 0.09357 0.08852 -0.0492 0.0060 1.0000
14.750 1.2709 0.09951 0.09469 -0.0516 0.0060 1.0000
15.000 1.2577 0.10590 0.10131 -0.0545 0.0060 1.0000
15.250 1.2435 0.11276 0.10839 -0.0579 0.0061 1.0000
15.500 1.2293 0.11993 0.11575 -0.0618 0.0061 1.0000
15.750 1.2144 0.12763 0.12365 -0.0662 0.0061 1.0000
16.000 1.1995 0.13572 0.13193 -0.0711 0.0062 1.0000
16.250 1.1845 0.14430 0.14068 -0.0766 0.0063 1.0000
16.500 1.1696 0.15332 0.14986 -0.0824 0.0064 1.0000
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Polar data table (+)
Polar graphs
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