GOE 559 AIRFOIL (goe559-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 559 AIRFOIL (goe559-il) Reynolds number: 200,000 Max Cl/Cd: 50.22 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe559-il-200000.txt Download as CSV file: xf-goe559-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 559 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3263 0.08848 0.08548 -0.0402 1.0000 0.0102
-7.750 -0.3278 0.08573 0.08279 -0.0407 1.0000 0.0101
-7.500 -0.3334 0.08282 0.07997 -0.0410 1.0000 0.0106
-7.250 -0.3429 0.08046 0.07770 -0.0404 1.0000 0.0104
-7.000 -0.3573 0.07852 0.07586 -0.0390 1.0000 0.0102
-6.750 -0.3643 0.07558 0.07298 -0.0398 0.9988 0.0105
-6.500 -0.3339 0.06930 0.06661 -0.0502 0.9891 0.0105
-6.250 -0.3002 0.06333 0.06048 -0.0595 0.9771 0.0118
-6.000 -0.2708 0.05844 0.05541 -0.0656 0.9646 0.0119
-5.750 -0.2329 0.05533 0.05192 -0.0707 0.9505 0.0126
-5.500 -0.2038 0.05103 0.04726 -0.0744 0.9349 0.0130
-4.000 -0.0727 0.01114 0.00559 -0.0718 0.7346 0.0243
-3.750 -0.0532 0.00956 0.00362 -0.0705 0.7174 0.0294
-3.500 -0.0341 0.00793 0.00161 -0.0695 0.7022 0.0360
-2.500 0.0502 0.01839 0.01058 -0.0709 0.6720 0.1458
-2.250 0.0788 0.01702 0.00898 -0.0701 0.6594 0.1441
-2.000 0.1122 0.01673 0.00821 -0.0687 0.6480 0.1075
-1.750 0.1437 0.01611 0.00740 -0.0677 0.6379 0.0745
-1.500 0.1727 0.01553 0.00662 -0.0665 0.6281 0.0490
-1.250 0.1982 0.01488 0.00586 -0.0654 0.6188 0.0362
-1.000 0.2227 0.01436 0.00510 -0.0643 0.6109 0.0279
-0.750 0.2466 0.01390 0.00451 -0.0633 0.6024 0.0241
-0.500 0.2711 0.01354 0.00390 -0.0627 0.5955 0.0263
-0.250 0.2969 0.01337 0.00348 -0.0621 0.5883 0.0269
0.000 0.4122 0.01076 0.00335 -0.0804 0.5789 1.0000
0.250 0.4350 0.01086 0.00326 -0.0797 0.5730 1.0000
0.500 0.4582 0.01101 0.00326 -0.0792 0.5678 1.0000
0.750 0.4815 0.01113 0.00333 -0.0787 0.5618 1.0000
1.000 0.5049 0.01129 0.00342 -0.0782 0.5569 1.0000
1.250 0.5287 0.01146 0.00361 -0.0778 0.5522 1.0000
1.500 0.5524 0.01162 0.00381 -0.0774 0.5474 1.0000
1.750 0.5636 0.01127 0.00320 -0.0738 0.4977 1.0000
2.000 0.5730 0.01141 0.00281 -0.0702 0.3852 1.0000
2.250 0.5706 0.01381 0.00378 -0.0655 0.0266 1.0000
2.500 0.5928 0.01407 0.00417 -0.0644 0.0245 1.0000
2.750 0.6135 0.01447 0.00477 -0.0630 0.0213 1.0000
3.000 0.6346 0.01485 0.00548 -0.0616 0.0233 1.0000
3.250 0.6537 0.01538 0.00624 -0.0599 0.0265 1.0000
3.500 0.6744 0.01580 0.00687 -0.0582 0.0319 1.0000
3.750 0.6930 0.01636 0.00762 -0.0561 0.0385 1.0000
4.000 0.7106 0.01695 0.00841 -0.0538 0.0469 1.0000
4.250 0.7184 0.01811 0.00968 -0.0500 0.0551 1.0000
4.500 0.7405 0.01845 0.01014 -0.0480 0.0669 1.0000
4.750 0.7621 0.01883 0.01066 -0.0459 0.0739 1.0000
5.000 0.7733 0.02003 0.01186 -0.0426 0.0765 1.0000
5.250 0.7888 0.02147 0.01323 -0.0398 0.0769 1.0000
5.500 0.8112 0.02290 0.01464 -0.0382 0.0725 1.0000
5.750 0.8508 0.02880 0.02009 -0.0414 0.0426 1.0000
6.000 0.8640 0.03064 0.02212 -0.0395 0.0257 1.0000
6.250 0.8941 0.03515 0.02667 -0.0402 0.0188 1.0000
6.500 0.9091 0.03474 0.02664 -0.0370 0.0165 1.0000
6.750 0.9311 0.03699 0.02911 -0.0355 0.0141 1.0000
7.000 0.9508 0.04021 0.03250 -0.0344 0.0127 1.0000
7.250 0.9726 0.04654 0.03888 -0.0347 0.0114 1.0000
7.500 0.9862 0.05320 0.04572 -0.0335 0.0108 1.0000
7.750 0.9950 0.05468 0.04754 -0.0304 0.0107 1.0000
8.000 1.0020 0.05473 0.04798 -0.0266 0.0104 1.0000
8.250 1.0121 0.05502 0.04859 -0.0233 0.0099 1.0000
8.500 1.0212 0.05650 0.05036 -0.0203 0.0093 1.0000
8.750 1.0265 0.05886 0.05297 -0.0174 0.0087 1.0000
9.000 1.0282 0.06151 0.05585 -0.0146 0.0084 1.0000
9.250 1.0267 0.06420 0.05876 -0.0118 0.0081 1.0000
9.500 1.0217 0.06697 0.06173 -0.0088 0.0079 1.0000
9.750 1.0130 0.06945 0.06438 -0.0056 0.0078 1.0000
10.000 0.9997 0.07204 0.06713 -0.0024 0.0077 1.0000
10.250 0.9855 0.07481 0.07004 0.0000 0.0076 1.0000
10.500 0.9707 0.07778 0.07316 0.0016 0.0076 1.0000
10.750 0.9548 0.08111 0.07664 0.0023 0.0075 1.0000
11.000 0.9373 0.08494 0.08060 0.0023 0.0075 1.0000
11.250 0.9208 0.08901 0.08480 0.0016 0.0075 1.0000
11.500 0.9056 0.09326 0.08917 0.0002 0.0077 1.0000
11.750 0.8880 0.09827 0.09430 -0.0018 0.0077 1.0000
12.000 0.8719 0.10352 0.09964 -0.0043 0.0078 1.0000
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Polar data table (+)
Polar graphs
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