GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 483 AIRFOIL (goe483-il) Reynolds number: 100,000 Max Cl/Cd: 62.7 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe483-il-100000.txt Download as CSV file: xf-goe483-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 483 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3068 0.10587 0.10121 -0.0257 1.0000 0.0509
-7.750 -0.3108 0.10526 0.10070 -0.0265 1.0000 0.0511
-7.500 -0.3099 0.10442 0.09996 -0.0296 1.0000 0.0513
-7.250 -0.3057 0.10304 0.09862 -0.0327 1.0000 0.0515
-7.000 -0.2962 0.09371 0.08931 -0.0246 1.0000 0.0532
-6.750 -0.2923 0.09079 0.08645 -0.0234 1.0000 0.0545
-6.500 -0.2917 0.08856 0.08429 -0.0225 1.0000 0.0559
-6.250 -0.2938 0.08674 0.08256 -0.0215 1.0000 0.0573
-6.000 -0.2977 0.08520 0.08110 -0.0204 1.0000 0.0585
-5.750 -0.3017 0.08370 0.07967 -0.0194 1.0000 0.0598
-5.500 -0.3033 0.08220 0.07821 -0.0196 1.0000 0.0616
-5.250 -0.2953 0.08153 0.07754 -0.0243 1.0000 0.0636
-5.000 -0.2716 0.08122 0.07710 -0.0333 1.0000 0.0644
-4.750 -0.2788 0.07614 0.07216 -0.0283 1.0000 0.0652
-4.500 -0.2799 0.07284 0.06893 -0.0247 1.0000 0.0665
-4.250 -0.2743 0.07020 0.06631 -0.0238 1.0000 0.0688
-4.000 -0.2611 0.06778 0.06387 -0.0254 1.0000 0.0730
-3.750 -0.2110 0.06341 0.05932 -0.0365 0.9949 0.0796
-3.250 -0.1205 0.05502 0.05070 -0.0514 0.9822 0.0942
-3.000 -0.0613 0.05181 0.04717 -0.0617 0.9741 0.1056
-2.750 -0.0273 0.04759 0.04298 -0.0648 0.9686 0.1119
-2.500 0.0184 0.04427 0.03944 -0.0709 0.9600 0.1225
-2.250 0.0757 0.04173 0.03654 -0.0786 0.9534 0.1471
-2.000 0.1170 0.03867 0.03331 -0.0826 0.9449 0.1611
-1.750 0.1879 0.03335 0.02712 -0.0908 0.9411 0.1186
-1.500 0.2197 0.03093 0.02477 -0.0927 0.9309 0.1354
-1.250 0.2830 0.02383 0.01620 -0.0979 0.9284 0.0926
-1.000 0.3230 0.02255 0.01469 -0.1000 0.9182 0.1078
-0.750 0.3725 0.02100 0.01283 -0.1035 0.9115 0.1253
-0.500 0.4141 0.02000 0.01167 -0.1055 0.9015 0.1507
-0.250 0.4517 0.01946 0.01103 -0.1066 0.8899 0.1882
0.000 0.4878 0.01896 0.01054 -0.1076 0.8782 0.2252
0.250 0.5230 0.01838 0.00994 -0.1084 0.8665 0.2590
0.500 0.5557 0.01773 0.00929 -0.1085 0.8542 0.2868
0.750 0.5870 0.01709 0.00867 -0.1082 0.8413 0.3174
1.000 0.6155 0.01650 0.00815 -0.1075 0.8272 0.3546
1.250 0.6419 0.01586 0.00779 -0.1067 0.8123 0.4262
1.500 0.6748 0.01472 0.00747 -0.1066 0.7974 1.0000
1.750 0.7007 0.01479 0.00734 -0.1054 0.7812 1.0000
2.000 0.7264 0.01487 0.00728 -0.1043 0.7653 1.0000
2.250 0.7521 0.01494 0.00721 -0.1032 0.7495 1.0000
2.500 0.7777 0.01502 0.00717 -0.1021 0.7340 1.0000
2.750 0.8035 0.01510 0.00715 -0.1011 0.7185 1.0000
3.000 0.8281 0.01527 0.00727 -0.1001 0.7010 1.0000
3.250 0.8532 0.01541 0.00741 -0.0992 0.6840 1.0000
3.500 0.8786 0.01556 0.00749 -0.0982 0.6674 1.0000
3.750 0.9042 0.01570 0.00758 -0.0973 0.6510 1.0000
4.000 0.9296 0.01589 0.00771 -0.0964 0.6343 1.0000
4.250 0.9542 0.01614 0.00797 -0.0955 0.6159 1.0000
4.500 0.9793 0.01640 0.00827 -0.0946 0.5984 1.0000
4.750 1.0046 0.01671 0.00854 -0.0938 0.5816 1.0000
5.000 1.0296 0.01709 0.00893 -0.0930 0.5646 1.0000
5.250 1.0540 0.01755 0.00944 -0.0922 0.5470 1.0000
5.500 1.0786 0.01803 0.00998 -0.0914 0.5301 1.0000
5.750 1.1022 0.01837 0.01034 -0.0902 0.5086 1.0000
6.000 1.1226 0.01846 0.01045 -0.0884 0.4780 1.0000
6.250 1.1420 0.01849 0.01050 -0.0865 0.4446 1.0000
6.500 1.1623 0.01864 0.01073 -0.0848 0.4144 1.0000
6.750 1.1781 0.01879 0.01083 -0.0824 0.3589 1.0000
7.000 1.1892 0.01982 0.01140 -0.0796 0.2524 1.0000
7.250 1.1880 0.02317 0.01329 -0.0763 0.0753 1.0000
7.500 1.1997 0.02516 0.01517 -0.0739 0.0561 1.0000
7.750 1.2122 0.02685 0.01699 -0.0717 0.0492 1.0000
8.000 1.2221 0.02861 0.01889 -0.0693 0.0441 1.0000
8.250 1.2266 0.03076 0.02115 -0.0663 0.0421 1.0000
8.500 1.2362 0.03257 0.02306 -0.0637 0.0412 1.0000
8.750 1.2500 0.03453 0.02510 -0.0616 0.0404 1.0000
9.000 1.2724 0.03688 0.02750 -0.0603 0.0399 1.0000
9.250 1.3018 0.03976 0.03056 -0.0599 0.0396 1.0000
9.500 1.3253 0.04253 0.03359 -0.0590 0.0382 1.0000
9.750 1.3454 0.04562 0.03700 -0.0578 0.0373 1.0000
10.000 1.3627 0.04951 0.04131 -0.0563 0.0385 1.0000
10.250 1.3746 0.05390 0.04611 -0.0545 0.0399 1.0000
10.500 1.3869 0.06027 0.05275 -0.0537 0.0417 1.0000
10.750 1.3892 0.06150 0.05459 -0.0500 0.0444 1.0000
11.000 1.3693 0.06549 0.05921 -0.0459 0.0469 1.0000
11.250 1.3532 0.06966 0.06372 -0.0429 0.0488 1.0000
11.500 1.3396 0.07432 0.06861 -0.0410 0.0506 1.0000
11.750 1.3358 0.07904 0.07361 -0.0396 0.0549 1.0000
12.000 1.3081 0.08320 0.07803 -0.0390 0.0552 1.0000
12.250 1.2823 0.08815 0.08321 -0.0399 0.0553 1.0000
12.500 1.2567 0.09393 0.08918 -0.0421 0.0553 1.0000
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Polar data table (+)
Polar graphs
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