GOE 679 AIRFOIL (goe679-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 679 AIRFOIL (goe679-il) Reynolds number: 50,000 Max Cl/Cd: 25.15 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe679-il-50000-n5.txt Download as CSV file: xf-goe679-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 679 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3888 0.10413 0.09685 -0.0410 1.0000 0.0931
-9.500 -0.4160 0.09898 0.09179 -0.0413 1.0000 0.0934
-9.250 -0.4657 0.08892 0.08180 -0.0456 0.9984 0.0939
-9.000 -0.5682 0.06941 0.06195 -0.0598 0.9837 0.0938
-8.750 -0.6006 0.06205 0.05421 -0.0624 0.9721 0.0947
-8.500 -0.5777 0.06134 0.05354 -0.0632 0.9651 0.0969
-8.250 -0.5773 0.05751 0.04943 -0.0643 0.9559 0.0994
-8.000 -0.5851 0.05291 0.04433 -0.0638 0.9455 0.1020
-7.750 -0.5699 0.05065 0.04187 -0.0642 0.9376 0.1049
-7.500 -0.5516 0.04917 0.04029 -0.0641 0.9291 0.1080
-7.250 -0.5429 0.04611 0.03668 -0.0635 0.9201 0.1132
-7.000 -0.5144 0.04570 0.03641 -0.0641 0.9124 0.1174
-6.750 -0.5012 0.04363 0.03392 -0.0631 0.9029 0.1242
-6.500 -0.4707 0.04319 0.03359 -0.0640 0.8955 0.1301
-6.250 -0.4545 0.04196 0.03212 -0.0628 0.8854 0.1378
-6.000 -0.4249 0.04090 0.03084 -0.0637 0.8783 0.1481
-5.750 -0.4058 0.04061 0.03064 -0.0624 0.8675 0.1551
-5.500 -0.3737 0.03978 0.02965 -0.0634 0.8606 0.1667
-5.250 -0.3574 0.03922 0.02889 -0.0618 0.8494 0.1770
-5.000 -0.3227 0.03884 0.02858 -0.0629 0.8426 0.1882
-4.750 -0.3058 0.03839 0.02800 -0.0612 0.8312 0.1977
-4.500 -0.2725 0.03773 0.02714 -0.0620 0.8243 0.2106
-4.250 -0.2531 0.03750 0.02700 -0.0606 0.8132 0.2184
-3.750 -0.1975 0.03631 0.02560 -0.0603 0.7957 0.2373
-3.500 -0.1673 0.03561 0.02468 -0.0605 0.7874 0.2475
-3.250 -0.1257 0.03467 0.02373 -0.0622 0.7828 0.2570
-3.000 -0.1120 0.03452 0.02348 -0.0599 0.7689 0.2643
-2.750 -0.0713 0.03361 0.02247 -0.0615 0.7636 0.2746
-2.500 -0.0551 0.03350 0.02233 -0.0595 0.7504 0.2822
-2.250 -0.0147 0.03267 0.02136 -0.0610 0.7442 0.2937
-2.000 0.0053 0.03253 0.02122 -0.0596 0.7319 0.3025
-1.750 0.0444 0.03184 0.02043 -0.0610 0.7248 0.3153
-1.500 0.0697 0.03162 0.02020 -0.0603 0.7137 0.3270
-1.250 0.1070 0.03106 0.01962 -0.0615 0.7052 0.3414
-1.000 0.1357 0.03078 0.01927 -0.0613 0.6951 0.3571
-0.750 0.1665 0.03040 0.01892 -0.0615 0.6854 0.3750
-0.500 0.1971 0.03003 0.01860 -0.0616 0.6761 0.3945
-0.250 0.2239 0.02976 0.01840 -0.0611 0.6655 0.4175
0.000 0.2535 0.02941 0.01815 -0.0610 0.6564 0.4462
0.250 0.2768 0.02917 0.01810 -0.0599 0.6460 0.4808
0.500 0.3050 0.02872 0.01790 -0.0594 0.6371 0.5355
0.750 0.3263 0.02840 0.01803 -0.0577 0.6267 0.6204
1.000 0.4717 0.02774 0.01801 -0.0772 0.6170 0.9277
1.250 0.5543 0.02792 0.01790 -0.0873 0.6055 1.0000
1.500 0.5664 0.02819 0.01799 -0.0847 0.5953 1.0000
1.750 0.5884 0.02827 0.01786 -0.0835 0.5860 1.0000
2.000 0.6013 0.02859 0.01802 -0.0810 0.5762 1.0000
2.250 0.6228 0.02875 0.01800 -0.0797 0.5671 1.0000
2.500 0.6397 0.02905 0.01815 -0.0778 0.5581 1.0000
2.750 0.6558 0.02936 0.01832 -0.0757 0.5488 1.0000
3.000 0.6810 0.02954 0.01833 -0.0751 0.5406 1.0000
3.250 0.6879 0.03009 0.01880 -0.0715 0.5313 1.0000
3.500 0.7283 0.03001 0.01849 -0.0733 0.5239 1.0000
3.750 0.7205 0.03088 0.01937 -0.0675 0.5143 1.0000
4.000 0.7517 0.03099 0.01931 -0.0678 0.5066 1.0000
4.250 0.7569 0.03168 0.01997 -0.0642 0.4982 1.0000
4.500 0.7728 0.03215 0.02034 -0.0622 0.4900 1.0000
4.750 0.8025 0.03234 0.02038 -0.0623 0.4828 1.0000
5.000 0.7978 0.03334 0.02142 -0.0573 0.4741 1.0000
5.250 0.8280 0.03351 0.02145 -0.0575 0.4672 1.0000
5.500 0.8321 0.03440 0.02234 -0.0540 0.4594 1.0000
5.750 0.8410 0.03516 0.02307 -0.0512 0.4515 1.0000
6.000 0.8816 0.03506 0.02279 -0.0528 0.4454 1.0000
6.250 0.8634 0.03672 0.02457 -0.0466 0.4370 1.0000
6.500 0.8809 0.03731 0.02511 -0.0451 0.4301 1.0000
6.750 0.9115 0.03747 0.02515 -0.0452 0.4241 1.0000
7.000 0.8912 0.03950 0.02731 -0.0395 0.4157 1.0000
7.250 0.9145 0.03987 0.02761 -0.0388 0.4094 1.0000
7.500 0.9311 0.04060 0.02829 -0.0374 0.4034 1.0000
7.750 0.9089 0.04312 0.03095 -0.0323 0.3952 1.0000
8.000 0.9361 0.04329 0.03105 -0.0319 0.3896 1.0000
8.250 0.9381 0.04483 0.03261 -0.0294 0.3833 1.0000
8.500 0.9080 0.04840 0.03632 -0.0250 0.3748 1.0000
8.750 0.9401 0.04820 0.03604 -0.0248 0.3703 1.0000
9.000 0.8828 0.05447 0.04251 -0.0202 0.3602 1.0000
9.250 0.8848 0.05656 0.04462 -0.0188 0.3539 1.0000
9.500 0.9250 0.05539 0.04337 -0.0186 0.3510 1.0000
10.000 0.8038 0.07337 0.06167 -0.0162 0.3273 1.0000
10.250 0.8948 0.06565 0.05379 -0.0147 0.3315 1.0000
10.750 0.8339 0.07863 0.06693 -0.0145 0.3139 1.0000
11.250 0.7820 0.09272 0.08118 -0.0165 0.2973 1.0000
11.750 0.7409 0.10556 0.09413 -0.0190 0.2827 1.0000
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Polar data table (+)
Polar graphs
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