GOE 624 AIRFOIL (goe624-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 624 AIRFOIL (goe624-il) Reynolds number: 100,000 Max Cl/Cd: 50.23 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe624-il-100000-n5.txt Download as CSV file: xf-goe624-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 624 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2077 0.09517 0.08999 -0.0713 0.9561 0.0543
-9.750 -0.2078 0.08943 0.08425 -0.0757 0.9452 0.0536
-9.500 -0.2134 0.08269 0.07748 -0.0810 0.9343 0.0530
-9.250 -0.2804 0.06238 0.05707 -0.0995 0.9145 0.0519
-9.000 -0.3273 0.05130 0.04547 -0.1063 0.8978 0.0519
-8.750 -0.3284 0.04707 0.04094 -0.1074 0.8887 0.0524
-8.500 -0.3182 0.04505 0.03877 -0.1072 0.8786 0.0530
-8.250 -0.3078 0.04216 0.03557 -0.1073 0.8710 0.0536
-8.000 -0.2991 0.03926 0.03232 -0.1068 0.8614 0.0542
-7.750 -0.2851 0.03655 0.02922 -0.1065 0.8541 0.0549
-7.500 -0.2695 0.03423 0.02651 -0.1058 0.8463 0.0557
-7.250 -0.2515 0.03210 0.02397 -0.1052 0.8383 0.0568
-7.000 -0.2302 0.03000 0.02134 -0.1047 0.8325 0.0584
-6.750 -0.2080 0.02937 0.02071 -0.1040 0.8232 0.0596
-6.500 -0.1832 0.02848 0.01968 -0.1036 0.8160 0.0612
-6.250 -0.1604 0.02745 0.01843 -0.1029 0.8066 0.0631
-6.000 -0.1357 0.02620 0.01687 -0.1022 0.7986 0.0650
-5.750 -0.1112 0.02540 0.01599 -0.1017 0.7901 0.0667
-5.500 -0.0860 0.02475 0.01526 -0.1012 0.7821 0.0689
-5.250 -0.0596 0.02400 0.01432 -0.1007 0.7757 0.0726
-5.000 -0.0349 0.02348 0.01378 -0.1003 0.7670 0.0761
-4.750 -0.0081 0.02289 0.01307 -0.0999 0.7607 0.0808
-4.500 0.0172 0.02236 0.01250 -0.0995 0.7528 0.0856
-4.250 0.0435 0.02187 0.01192 -0.0991 0.7455 0.0922
-4.000 0.0701 0.02142 0.01145 -0.0988 0.7391 0.0994
-3.750 0.0957 0.02107 0.01103 -0.0983 0.7308 0.1077
-3.500 0.1230 0.02070 0.01061 -0.0981 0.7245 0.1166
-3.250 0.1485 0.02042 0.01035 -0.0977 0.7164 0.1260
-3.000 0.1753 0.02014 0.01005 -0.0975 0.7093 0.1378
-2.750 0.2023 0.01993 0.00977 -0.0972 0.7024 0.1505
-2.500 0.2282 0.01965 0.00955 -0.0968 0.6942 0.1615
-2.250 0.2558 0.01930 0.00917 -0.0966 0.6882 0.1729
-2.000 0.2812 0.01912 0.00902 -0.0961 0.6793 0.1868
-1.750 0.3084 0.01883 0.00875 -0.0958 0.6726 0.2053
-1.500 0.3344 0.01861 0.00861 -0.0955 0.6650 0.2310
-1.250 0.3608 0.01835 0.00846 -0.0952 0.6572 0.2700
-1.000 0.3875 0.01804 0.00831 -0.0949 0.6503 0.3265
-0.750 0.4125 0.01774 0.00829 -0.0945 0.6417 0.4094
-0.500 0.4371 0.01722 0.00820 -0.0936 0.6354 0.5449
-0.250 0.4566 0.01681 0.00841 -0.0913 0.6271 0.7234
0.000 0.4969 0.01660 0.00843 -0.0924 0.6197 0.9026
0.250 0.5506 0.01666 0.00838 -0.0974 0.6109 0.9874
0.500 0.5832 0.01677 0.00831 -0.0985 0.6028 1.0000
0.750 0.6070 0.01691 0.00829 -0.0977 0.5956 1.0000
1.000 0.6301 0.01710 0.00837 -0.0969 0.5875 1.0000
1.250 0.6556 0.01722 0.00831 -0.0964 0.5814 1.0000
1.500 0.6782 0.01746 0.00849 -0.0956 0.5728 1.0000
1.750 0.7032 0.01762 0.00852 -0.0950 0.5659 1.0000
2.000 0.7274 0.01785 0.00865 -0.0944 0.5587 1.0000
2.250 0.7516 0.01807 0.00880 -0.0938 0.5515 1.0000
2.500 0.7781 0.01824 0.00882 -0.0935 0.5461 1.0000
2.750 0.8009 0.01855 0.00911 -0.0928 0.5383 1.0000
3.000 0.8260 0.01877 0.00924 -0.0924 0.5320 1.0000
3.250 0.8513 0.01902 0.00941 -0.0920 0.5262 1.0000
3.500 0.8748 0.01933 0.00970 -0.0914 0.5195 1.0000
3.750 0.9005 0.01956 0.00985 -0.0910 0.5140 1.0000
4.000 0.9249 0.01987 0.01011 -0.0906 0.5082 1.0000
4.250 0.9485 0.02020 0.01044 -0.0900 0.5020 1.0000
4.500 0.9742 0.02046 0.01062 -0.0897 0.4970 1.0000
4.750 0.9983 0.02080 0.01094 -0.0892 0.4915 1.0000
5.000 1.0212 0.02117 0.01132 -0.0886 0.4855 1.0000
5.250 1.0465 0.02146 0.01156 -0.0883 0.4805 1.0000
5.500 1.0707 0.02181 0.01189 -0.0878 0.4752 1.0000
5.750 1.0923 0.02223 0.01235 -0.0870 0.4691 1.0000
6.000 1.1169 0.02253 0.01260 -0.0866 0.4635 1.0000
6.250 1.1393 0.02291 0.01298 -0.0859 0.4572 1.0000
6.500 1.1596 0.02332 0.01342 -0.0849 0.4502 1.0000
6.750 1.1849 0.02359 0.01361 -0.0846 0.4445 1.0000
7.000 1.2031 0.02411 0.01421 -0.0833 0.4379 1.0000
7.250 1.2238 0.02454 0.01467 -0.0824 0.4318 1.0000
7.500 1.2490 0.02487 0.01493 -0.0821 0.4270 1.0000
7.750 1.2654 0.02547 0.01565 -0.0807 0.4210 1.0000
8.000 1.2841 0.02598 0.01623 -0.0796 0.4153 1.0000
8.250 1.3075 0.02637 0.01659 -0.0791 0.4105 1.0000
8.500 1.3238 0.02699 0.01729 -0.0777 0.4050 1.0000
8.750 1.3383 0.02762 0.01803 -0.0760 0.3989 1.0000
9.000 1.3588 0.02804 0.01845 -0.0751 0.3936 1.0000
9.250 1.3709 0.02871 0.01920 -0.0731 0.3879 1.0000
9.500 1.3797 0.02948 0.02008 -0.0707 0.3817 1.0000
9.750 1.3974 0.02999 0.02061 -0.0695 0.3764 1.0000
10.000 1.4072 0.03085 0.02157 -0.0675 0.3708 1.0000
10.250 1.4141 0.03185 0.02270 -0.0652 0.3645 1.0000
10.500 1.4305 0.03244 0.02329 -0.0641 0.3590 1.0000
10.750 1.4340 0.03370 0.02471 -0.0618 0.3526 1.0000
11.000 1.4402 0.03485 0.02595 -0.0598 0.3459 1.0000
11.250 1.4537 0.03561 0.02672 -0.0586 0.3400 1.0000
11.500 1.4499 0.03751 0.02881 -0.0562 0.3324 1.0000
11.750 1.4613 0.03842 0.02972 -0.0549 0.3260 1.0000
12.000 1.4571 0.04059 0.03205 -0.0529 0.3184 1.0000
12.250 1.4628 0.04200 0.03350 -0.0516 0.3113 1.0000
12.500 1.4600 0.04424 0.03586 -0.0500 0.3037 1.0000
12.750 1.4621 0.04608 0.03774 -0.0488 0.2961 1.0000
13.000 1.4586 0.04858 0.04035 -0.0476 0.2885 1.0000
13.250 1.4592 0.05073 0.04256 -0.0465 0.2813 1.0000
13.500 1.4573 0.05326 0.04516 -0.0456 0.2743 1.0000
13.750 1.4542 0.05599 0.04796 -0.0448 0.2671 1.0000
14.000 1.4575 0.05809 0.05009 -0.0442 0.2610 1.0000
14.250 1.4495 0.06164 0.05378 -0.0437 0.2543 1.0000
14.500 1.4600 0.06295 0.05507 -0.0431 0.2490 1.0000
14.750 1.4490 0.06708 0.05936 -0.0429 0.2428 1.0000
15.000 1.4479 0.06997 0.06232 -0.0427 0.2371 1.0000
15.250 1.4553 0.07175 0.06411 -0.0423 0.2320 1.0000
15.500 1.4405 0.07665 0.06917 -0.0426 0.2260 1.0000
15.750 1.4464 0.07869 0.07124 -0.0423 0.2208 1.0000
16.000 1.4431 0.08207 0.07472 -0.0425 0.2157 1.0000
16.250 1.4308 0.08684 0.07964 -0.0431 0.2100 1.0000
16.500 1.4423 0.08810 0.08088 -0.0428 0.2054 1.0000
16.750 1.4296 0.09306 0.08599 -0.0436 0.2002 1.0000
17.000 1.4187 0.09782 0.09087 -0.0446 0.1946 1.0000
17.250 1.4370 0.09800 0.09102 -0.0441 0.1902 1.0000
17.500 1.4095 0.10550 0.09873 -0.0461 0.1844 1.0000
17.750 1.4042 0.10951 0.10283 -0.0471 0.1791 1.0000
18.000 1.4293 0.10851 0.10175 -0.0462 0.1750 1.0000
18.250 1.3849 0.11920 0.11274 -0.0500 0.1686 1.0000
18.500 1.3909 0.12142 0.11499 -0.0506 0.1637 1.0000
18.750 1.3899 0.12483 0.11846 -0.0517 0.1588 1.0000
19.000 1.3573 0.13399 0.12779 -0.0555 0.1525 1.0000
19.250 1.3829 0.13268 0.12642 -0.0547 0.1481 1.0000
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Polar data table (+)
Polar graphs
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