GOE 566 AIRFOIL (goe566-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 566 AIRFOIL (goe566-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.05 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe566-il-1000000-n5.txt Download as CSV file: xf-goe566-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 566 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -1.0066 0.03241 0.02972 -0.0640 1.0000 0.0058
-12.500 -1.0093 0.02864 0.02564 -0.0622 1.0000 0.0059
-12.250 -1.0049 0.02589 0.02266 -0.0604 1.0000 0.0062
-12.000 -0.9948 0.02398 0.02055 -0.0587 1.0000 0.0064
-11.750 -0.9818 0.02251 0.01893 -0.0570 1.0000 0.0066
-11.500 -0.9676 0.02126 0.01755 -0.0553 1.0000 0.0068
-11.250 -0.9466 0.02008 0.01622 -0.0549 0.9990 0.0070
-11.000 -0.9193 0.01897 0.01496 -0.0557 0.9964 0.0074
-10.750 -0.8923 0.01797 0.01382 -0.0563 0.9931 0.0077
-10.500 -0.8648 0.01711 0.01281 -0.0568 0.9896 0.0079
-10.250 -0.8363 0.01619 0.01177 -0.0576 0.9867 0.0085
-10.000 -0.8075 0.01541 0.01090 -0.0583 0.9830 0.0091
-9.750 -0.7771 0.01472 0.01012 -0.0592 0.9786 0.0098
-9.500 -0.7449 0.01409 0.00940 -0.0605 0.9745 0.0106
-9.250 -0.7147 0.01353 0.00877 -0.0613 0.9678 0.0115
-9.000 -0.6831 0.01311 0.00831 -0.0624 0.9630 0.0126
-8.750 -0.6540 0.01274 0.00788 -0.0628 0.9563 0.0137
-8.500 -0.6245 0.01234 0.00740 -0.0633 0.9497 0.0145
-8.250 -0.5962 0.01218 0.00725 -0.0634 0.9423 0.0157
-8.000 -0.5677 0.01210 0.00716 -0.0636 0.9350 0.0168
-7.750 -0.5406 0.01196 0.00699 -0.0634 0.9275 0.0178
-7.500 -0.5138 0.01178 0.00673 -0.0632 0.9202 0.0186
-7.250 -0.4873 0.01160 0.00648 -0.0629 0.9135 0.0190
-7.000 -0.4616 0.01127 0.00608 -0.0625 0.9065 0.0197
-6.750 -0.4351 0.01109 0.00588 -0.0622 0.9000 0.0205
-6.500 -0.4083 0.01101 0.00579 -0.0619 0.8932 0.0212
-6.250 -0.3816 0.01087 0.00559 -0.0617 0.8874 0.0219
-6.000 -0.3549 0.01071 0.00541 -0.0614 0.8812 0.0226
-5.500 -0.3019 0.01033 0.00492 -0.0608 0.8688 0.0240
-5.250 -0.2754 0.01014 0.00467 -0.0604 0.8622 0.0245
-5.000 -0.2488 0.00993 0.00441 -0.0601 0.8563 0.0249
-4.750 -0.2221 0.00976 0.00420 -0.0598 0.8500 0.0252
-4.500 -0.1956 0.00954 0.00393 -0.0595 0.8439 0.0254
-4.250 -0.1693 0.00929 0.00363 -0.0591 0.8360 0.0255
-4.000 -0.1446 0.00879 0.00303 -0.0584 0.8265 0.0263
-3.750 -0.1190 0.00851 0.00268 -0.0579 0.8160 0.0271
-3.500 -0.0925 0.00830 0.00244 -0.0575 0.8063 0.0280
-3.250 -0.0662 0.00815 0.00224 -0.0571 0.7946 0.0288
-3.000 -0.0400 0.00802 0.00205 -0.0566 0.7797 0.0294
-2.750 -0.0137 0.00792 0.00187 -0.0562 0.7638 0.0300
-2.500 0.0123 0.00784 0.00172 -0.0557 0.7449 0.0306
-2.250 0.0384 0.00778 0.00157 -0.0552 0.7256 0.0311
-2.000 0.0647 0.00773 0.00144 -0.0548 0.7064 0.0317
-1.750 0.0909 0.00770 0.00132 -0.0544 0.6868 0.0322
-1.500 0.1171 0.00768 0.00123 -0.0540 0.6679 0.0327
-1.250 0.1435 0.00767 0.00114 -0.0536 0.6480 0.0333
-1.000 0.1696 0.00770 0.00107 -0.0531 0.6248 0.0338
-0.750 0.1956 0.00772 0.00100 -0.0527 0.6001 0.0366
-0.500 0.2219 0.00772 0.00096 -0.0523 0.5796 0.0419
-0.250 0.2482 0.00770 0.00093 -0.0519 0.5604 0.0551
0.000 0.2735 0.00762 0.00091 -0.0514 0.5339 0.1061
0.250 0.2984 0.00766 0.00093 -0.0509 0.4946 0.1442
0.500 0.3226 0.00774 0.00098 -0.0503 0.4500 0.1935
0.750 0.3463 0.00771 0.00103 -0.0496 0.4123 0.2809
1.000 0.3635 0.00694 0.00110 -0.0479 0.3780 0.6222
1.500 0.4064 0.00681 0.00129 -0.0452 0.3125 0.8084
1.750 0.4281 0.00678 0.00140 -0.0438 0.2841 0.8872
2.000 0.4960 0.00697 0.00159 -0.0527 0.2543 0.9798
2.250 0.5399 0.00717 0.00170 -0.0564 0.2396 0.9955
2.500 0.5803 0.00731 0.00177 -0.0592 0.2300 0.9998
2.750 0.6056 0.00743 0.00186 -0.0587 0.2224 1.0000
3.000 0.6298 0.00755 0.00195 -0.0579 0.2169 1.0000
3.250 0.6542 0.00767 0.00204 -0.0572 0.2108 1.0000
3.500 0.6782 0.00783 0.00215 -0.0564 0.2014 1.0000
3.750 0.7019 0.00802 0.00227 -0.0556 0.1881 1.0000
4.000 0.7261 0.00817 0.00239 -0.0549 0.1790 1.0000
4.250 0.7501 0.00835 0.00252 -0.0541 0.1666 1.0000
4.500 0.7735 0.00859 0.00267 -0.0532 0.1494 1.0000
4.750 0.7936 0.00911 0.00296 -0.0519 0.1040 1.0000
5.000 0.8167 0.00939 0.00318 -0.0510 0.0925 1.0000
5.250 0.8404 0.00961 0.00338 -0.0502 0.0877 1.0000
5.500 0.8642 0.00982 0.00359 -0.0494 0.0828 1.0000
5.750 0.8884 0.01001 0.00378 -0.0487 0.0796 1.0000
6.000 0.9119 0.01025 0.00401 -0.0479 0.0744 1.0000
6.250 0.9353 0.01051 0.00425 -0.0471 0.0683 1.0000
6.500 0.9589 0.01074 0.00447 -0.0463 0.0606 1.0000
6.750 0.9793 0.01128 0.00484 -0.0451 0.0371 1.0000
7.000 1.0017 0.01163 0.00517 -0.0442 0.0318 1.0000
7.250 1.0249 0.01192 0.00548 -0.0434 0.0287 1.0000
7.500 1.0481 0.01220 0.00578 -0.0426 0.0266 1.0000
7.750 1.0704 0.01257 0.00614 -0.0417 0.0235 1.0000
8.000 1.0930 0.01289 0.00648 -0.0408 0.0212 1.0000
8.250 1.1157 0.01321 0.00682 -0.0400 0.0192 1.0000
8.500 1.1374 0.01361 0.00721 -0.0390 0.0162 1.0000
8.750 1.1593 0.01398 0.00760 -0.0381 0.0145 1.0000
9.000 1.1805 0.01440 0.00802 -0.0371 0.0126 1.0000
9.250 1.2015 0.01483 0.00846 -0.0361 0.0111 1.0000
9.500 1.2226 0.01524 0.00891 -0.0350 0.0102 1.0000
9.750 1.2429 0.01569 0.00938 -0.0339 0.0094 1.0000
10.000 1.2623 0.01621 0.00994 -0.0327 0.0086 1.0000
10.250 1.2816 0.01670 0.01048 -0.0314 0.0081 1.0000
10.500 1.3008 0.01718 0.01101 -0.0302 0.0077 1.0000
10.750 1.3192 0.01768 0.01156 -0.0288 0.0072 1.0000
11.000 1.3368 0.01822 0.01213 -0.0274 0.0068 1.0000
11.250 1.3530 0.01879 0.01274 -0.0257 0.0064 1.0000
11.500 1.3653 0.01947 0.01349 -0.0234 0.0060 1.0000
11.750 1.3775 0.02009 0.01418 -0.0211 0.0058 1.0000
12.000 1.3903 0.02070 0.01485 -0.0189 0.0056 1.0000
12.250 1.4017 0.02141 0.01563 -0.0167 0.0055 1.0000
12.500 1.4131 0.02214 0.01643 -0.0146 0.0053 1.0000
12.750 1.4237 0.02294 0.01730 -0.0126 0.0050 1.0000
13.000 1.4338 0.02380 0.01823 -0.0106 0.0049 1.0000
13.250 1.4429 0.02476 0.01926 -0.0087 0.0047 1.0000
13.500 1.4498 0.02591 0.02050 -0.0067 0.0045 1.0000
13.750 1.4564 0.02714 0.02181 -0.0049 0.0045 1.0000
14.000 1.4617 0.02851 0.02326 -0.0032 0.0043 1.0000
14.250 1.4645 0.03016 0.02501 -0.0015 0.0042 1.0000
14.500 1.4653 0.03207 0.02703 0.0001 0.0041 1.0000
14.750 1.4695 0.03377 0.02882 0.0011 0.0040 1.0000
15.000 1.4713 0.03581 0.03097 0.0021 0.0040 1.0000
15.250 1.4703 0.03823 0.03351 0.0028 0.0039 1.0000
15.500 1.4685 0.04089 0.03628 0.0032 0.0038 1.0000
15.750 1.4702 0.04329 0.03877 0.0033 0.0037 1.0000
16.000 1.4663 0.04647 0.04207 0.0031 0.0037 1.0000
16.250 1.4603 0.05012 0.04584 0.0025 0.0036 1.0000
16.500 1.4529 0.05412 0.04997 0.0015 0.0036 1.0000
16.750 1.4440 0.05860 0.05457 0.0000 0.0035 1.0000
17.000 1.4265 0.06469 0.06082 -0.0024 0.0036 1.0000
17.250 1.4142 0.07030 0.06655 -0.0049 0.0035 1.0000
17.500 1.3958 0.07724 0.07364 -0.0082 0.0035 1.0000
17.750 1.3748 0.08480 0.08135 -0.0119 0.0035 1.0000
18.000 1.3470 0.09385 0.09055 -0.0164 0.0036 1.0000
18.250 1.3241 0.10210 0.09893 -0.0206 0.0035 1.0000
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Polar data table (+)
Polar graphs
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