GOE 409 AIRFOIL (goe409-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 409 AIRFOIL (goe409-il) Reynolds number: 100,000 Max Cl/Cd: 32.5 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe409-il-100000-n5.txt Download as CSV file: xf-goe409-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 409 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.8031 0.09173 0.08590 -0.0403 1.0000 0.0471
-14.250 -0.8401 0.08229 0.07629 -0.0463 1.0000 0.0469
-14.000 -0.8700 0.07510 0.06891 -0.0502 1.0000 0.0467
-13.750 -0.9020 0.06889 0.06246 -0.0530 1.0000 0.0469
-13.500 -0.9294 0.06404 0.05737 -0.0539 1.0000 0.0471
-13.250 -0.9558 0.06015 0.05318 -0.0534 1.0000 0.0474
-13.000 -0.9542 0.05739 0.05042 -0.0528 1.0000 0.0486
-12.750 -0.9544 0.05540 0.04840 -0.0518 1.0000 0.0499
-12.500 -0.9593 0.05330 0.04618 -0.0502 1.0000 0.0511
-12.250 -0.9643 0.05133 0.04407 -0.0481 1.0000 0.0524
-12.000 -0.9722 0.04937 0.04191 -0.0453 1.0000 0.0537
-11.750 -0.9812 0.04757 0.03987 -0.0417 1.0000 0.0550
-11.500 -0.9900 0.04600 0.03803 -0.0376 1.0000 0.0563
-11.250 -0.9958 0.04465 0.03634 -0.0337 1.0000 0.0577
-11.000 -0.9937 0.04261 0.03408 -0.0309 1.0000 0.0593
-10.750 -0.9799 0.04080 0.03231 -0.0298 1.0000 0.0615
-10.500 -0.9708 0.03948 0.03086 -0.0276 1.0000 0.0634
-10.250 -0.9617 0.03818 0.02940 -0.0252 1.0000 0.0653
-10.000 -0.9517 0.03683 0.02784 -0.0229 1.0000 0.0669
-9.750 -0.9397 0.03547 0.02627 -0.0207 1.0000 0.0680
-9.500 -0.9258 0.03418 0.02477 -0.0187 1.0000 0.0689
-9.250 -0.9118 0.03307 0.02345 -0.0166 1.0000 0.0699
-9.000 -0.8977 0.03213 0.02228 -0.0145 1.0000 0.0709
-8.750 -0.8783 0.03070 0.02078 -0.0134 1.0000 0.0720
-8.500 -0.8587 0.02945 0.01951 -0.0122 1.0000 0.0729
-8.250 -0.8408 0.02841 0.01844 -0.0107 1.0000 0.0738
-8.000 -0.8241 0.02749 0.01749 -0.0090 1.0000 0.0747
-7.750 -0.8084 0.02666 0.01662 -0.0070 1.0000 0.0756
-7.500 -0.7937 0.02589 0.01582 -0.0049 1.0000 0.0766
-7.250 -0.7797 0.02519 0.01508 -0.0026 1.0000 0.0778
-7.000 -0.7662 0.02453 0.01438 -0.0003 1.0000 0.0793
-6.750 -0.7529 0.02391 0.01371 0.0021 1.0000 0.0808
-6.500 -0.7396 0.02334 0.01306 0.0046 1.0000 0.0821
-6.250 -0.7262 0.02279 0.01245 0.0070 1.0000 0.0833
-6.000 -0.7128 0.02228 0.01189 0.0094 1.0000 0.0843
-5.750 -0.7005 0.02168 0.01128 0.0120 1.0000 0.0859
-5.500 -0.6870 0.02116 0.01075 0.0143 1.0000 0.0878
-5.250 -0.6726 0.02070 0.01025 0.0166 1.0000 0.0900
-5.000 -0.6575 0.02028 0.00981 0.0187 1.0000 0.0929
-4.750 -0.6419 0.01989 0.00940 0.0207 1.0000 0.0966
-4.250 -0.5694 0.01872 0.00864 0.0160 0.9863 0.1554
-4.000 -0.5373 0.01808 0.00827 0.0144 0.9801 0.2090
-3.750 -0.5082 0.01732 0.00794 0.0135 0.9741 0.2846
-3.500 -0.4807 0.01671 0.00775 0.0130 0.9678 0.3640
-3.250 -0.4505 0.01631 0.00768 0.0122 0.9616 0.4465
-3.000 -0.4206 0.01606 0.00758 0.0117 0.9550 0.5005
-2.750 -0.3891 0.01583 0.00752 0.0109 0.9486 0.5439
-2.500 -0.3566 0.01564 0.00751 0.0101 0.9427 0.5852
-2.250 -0.3268 0.01549 0.00753 0.0099 0.9353 0.6262
-2.000 -0.2882 0.01541 0.00757 0.0081 0.9307 0.6627
-1.750 -0.2604 0.01536 0.00765 0.0085 0.9217 0.6992
-1.500 -0.2211 0.01545 0.00796 0.0071 0.9169 0.7517
-1.250 -0.1878 0.01567 0.00831 0.0070 0.9094 0.7923
-1.000 -0.1484 0.01587 0.00855 0.0055 0.9029 0.8177
-0.750 -0.1124 0.01598 0.00866 0.0044 0.8951 0.8349
-0.500 -0.0732 0.01607 0.00876 0.0027 0.8874 0.8481
-0.250 -0.0365 0.01612 0.00881 0.0013 0.8786 0.8590
0.000 0.0000 0.01609 0.00876 0.0000 0.8700 0.8700
0.250 0.0364 0.01612 0.00880 -0.0013 0.8590 0.8786
0.500 0.0732 0.01607 0.00876 -0.0027 0.8481 0.8874
0.750 0.1123 0.01597 0.00866 -0.0044 0.8349 0.8951
1.250 0.1876 0.01568 0.00832 -0.0070 0.7926 0.9094
1.500 0.2213 0.01545 0.00797 -0.0071 0.7524 0.9170
1.750 0.2605 0.01535 0.00766 -0.0085 0.6994 0.9218
2.000 0.2883 0.01541 0.00757 -0.0081 0.6628 0.9308
2.250 0.3268 0.01549 0.00753 -0.0099 0.6262 0.9353
2.500 0.3566 0.01564 0.00751 -0.0101 0.5851 0.9428
2.750 0.3891 0.01583 0.00752 -0.0109 0.5430 0.9486
3.000 0.4204 0.01607 0.00758 -0.0116 0.4991 0.9551
3.250 0.4504 0.01631 0.00768 -0.0122 0.4442 0.9616
3.500 0.4805 0.01672 0.00775 -0.0130 0.3622 0.9678
3.750 0.5080 0.01733 0.00793 -0.0134 0.2832 0.9741
4.000 0.5374 0.01807 0.00827 -0.0145 0.2097 0.9801
4.250 0.5694 0.01872 0.00863 -0.0160 0.1554 0.9863
4.750 0.6418 0.01989 0.00940 -0.0206 0.0965 1.0000
5.000 0.6575 0.02027 0.00980 -0.0186 0.0929 1.0000
5.250 0.6725 0.02069 0.01025 -0.0165 0.0901 1.0000
5.500 0.6869 0.02116 0.01074 -0.0143 0.0878 1.0000
5.750 0.7004 0.02168 0.01128 -0.0120 0.0859 1.0000
6.000 0.7128 0.02227 0.01188 -0.0094 0.0844 1.0000
6.250 0.7261 0.02279 0.01245 -0.0070 0.0833 1.0000
6.500 0.7395 0.02333 0.01306 -0.0046 0.0821 1.0000
6.750 0.7528 0.02391 0.01370 -0.0021 0.0808 1.0000
7.000 0.7661 0.02453 0.01437 0.0003 0.0792 1.0000
7.250 0.7796 0.02518 0.01507 0.0027 0.0777 1.0000
7.500 0.7936 0.02589 0.01582 0.0049 0.0766 1.0000
7.750 0.8084 0.02666 0.01661 0.0070 0.0756 1.0000
8.000 0.8241 0.02748 0.01749 0.0090 0.0747 1.0000
8.250 0.8407 0.02840 0.01843 0.0107 0.0738 1.0000
8.500 0.8587 0.02944 0.01950 0.0122 0.0729 1.0000
8.750 0.8783 0.03069 0.02078 0.0134 0.0720 1.0000
9.000 0.8978 0.03213 0.02228 0.0144 0.0709 1.0000
9.250 0.9120 0.03309 0.02346 0.0166 0.0699 1.0000
9.500 0.9259 0.03419 0.02477 0.0186 0.0689 1.0000
9.750 0.9398 0.03547 0.02627 0.0206 0.0680 1.0000
10.000 0.9517 0.03681 0.02783 0.0229 0.0669 1.0000
10.250 0.9618 0.03816 0.02938 0.0252 0.0653 1.0000
10.500 0.9709 0.03947 0.03084 0.0276 0.0634 1.0000
10.750 0.9801 0.04079 0.03229 0.0297 0.0614 1.0000
11.000 0.9939 0.04261 0.03409 0.0309 0.0593 1.0000
11.250 0.9960 0.04464 0.03633 0.0336 0.0576 1.0000
11.500 0.9901 0.04600 0.03803 0.0376 0.0563 1.0000
11.750 0.9815 0.04756 0.03987 0.0417 0.0549 1.0000
12.000 0.9728 0.04932 0.04185 0.0452 0.0536 1.0000
12.250 0.9648 0.05135 0.04409 0.0480 0.0524 1.0000
12.500 0.9609 0.05324 0.04610 0.0501 0.0509 1.0000
12.750 0.9564 0.05530 0.04828 0.0517 0.0497 1.0000
13.000 0.9555 0.05737 0.05040 0.0527 0.0485 1.0000
13.250 0.9558 0.06017 0.05321 0.0533 0.0474 1.0000
13.500 0.9288 0.06409 0.05743 0.0538 0.0470 1.0000
13.750 0.9009 0.06903 0.06263 0.0527 0.0468 1.0000
14.000 0.8728 0.07497 0.06878 0.0502 0.0468 1.0000
14.250 0.8386 0.08267 0.07668 0.0458 0.0468 1.0000
14.500 0.8033 0.09195 0.08612 0.0399 0.0471 1.0000
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