GOE 530 AIRFOIL (goe530-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 530 AIRFOIL (goe530-il) Reynolds number: 100,000 Max Cl/Cd: 50.3 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe530-il-100000-n5.txt Download as CSV file: xf-goe530-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 530 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2162 0.09299 0.08795 -0.0633 0.9605 0.0815
-8.500 -0.2069 0.08832 0.08324 -0.0706 0.9520 0.0816
-8.250 -0.1972 0.08408 0.07897 -0.0752 0.9421 0.0816
-7.750 -0.1705 0.07263 0.06738 -0.0812 0.9270 0.0650
-7.500 -0.1554 0.06816 0.06282 -0.0859 0.9199 0.0650
-7.250 -0.1470 0.06490 0.05950 -0.0873 0.9088 0.0647
-7.000 -0.1295 0.06121 0.05570 -0.0901 0.9026 0.0642
-6.750 -0.1237 0.05823 0.05265 -0.0901 0.8908 0.0636
-6.500 -0.1111 0.05444 0.04869 -0.0918 0.8833 0.0631
-6.250 -0.1061 0.05124 0.04532 -0.0912 0.8720 0.0628
-6.000 -0.0960 0.04757 0.04138 -0.0913 0.8639 0.0633
-5.750 -0.0914 0.04393 0.03740 -0.0897 0.8529 0.0642
-5.500 -0.0833 0.04042 0.03348 -0.0879 0.8432 0.0647
-5.250 -0.0727 0.03735 0.02997 -0.0858 0.8334 0.0649
-5.000 -0.0595 0.03516 0.02747 -0.0837 0.8233 0.0655
-4.750 -0.0377 0.03403 0.02626 -0.0828 0.8149 0.0665
-4.500 -0.0187 0.03285 0.02493 -0.0814 0.8067 0.0679
-4.250 -0.0006 0.03137 0.02318 -0.0797 0.7985 0.0695
-4.000 0.0219 0.02950 0.02088 -0.0786 0.7928 0.0708
-3.750 0.0379 0.02812 0.01914 -0.0762 0.7832 0.0719
-3.500 0.0626 0.02684 0.01755 -0.0754 0.7768 0.0736
-3.250 0.0851 0.02620 0.01690 -0.0744 0.7687 0.0753
-3.000 0.1095 0.02537 0.01591 -0.0734 0.7610 0.0772
-2.750 0.1372 0.02438 0.01464 -0.0730 0.7547 0.0791
-2.500 0.1594 0.02371 0.01370 -0.0715 0.7454 0.0813
-2.250 0.1881 0.02291 0.01286 -0.0714 0.7388 0.0835
-2.000 0.2118 0.02242 0.01233 -0.0704 0.7298 0.0858
-1.750 0.2397 0.02179 0.01159 -0.0700 0.7219 0.0880
-1.500 0.2663 0.02134 0.01098 -0.0693 0.7136 0.0911
-1.250 0.2924 0.02079 0.01046 -0.0688 0.7045 0.0938
-1.000 0.3199 0.02033 0.00998 -0.0684 0.6962 0.0966
-0.750 0.3447 0.01999 0.00962 -0.0675 0.6862 0.0999
-0.500 0.3720 0.01963 0.00919 -0.0670 0.6773 0.1038
-0.250 0.3962 0.01929 0.00892 -0.0660 0.6666 0.1072
0.000 0.4218 0.01902 0.00863 -0.0653 0.6566 0.1113
0.250 0.4469 0.01880 0.00836 -0.0643 0.6457 0.1168
0.500 0.4715 0.01859 0.00819 -0.0635 0.6340 0.1226
0.750 0.5003 0.01839 0.00790 -0.0632 0.6230 0.1302
1.000 0.5262 0.01825 0.00782 -0.0627 0.6093 0.1420
1.250 0.5527 0.01811 0.00772 -0.0622 0.5955 0.1629
1.500 0.5805 0.01779 0.00763 -0.0621 0.5821 0.2385
2.000 0.7729 0.01665 0.00787 -0.0896 0.5409 1.0000
2.250 0.7940 0.01683 0.00792 -0.0881 0.5278 1.0000
2.500 0.8149 0.01704 0.00797 -0.0866 0.5151 1.0000
2.750 0.8351 0.01727 0.00811 -0.0850 0.5021 1.0000
3.000 0.8554 0.01752 0.00824 -0.0835 0.4902 1.0000
3.500 0.8953 0.01806 0.00857 -0.0802 0.4673 1.0000
3.750 0.9151 0.01836 0.00876 -0.0786 0.4570 1.0000
4.000 0.9345 0.01868 0.00900 -0.0770 0.4467 1.0000
4.250 0.9539 0.01901 0.00925 -0.0754 0.4372 1.0000
4.500 0.9728 0.01935 0.00952 -0.0737 0.4277 1.0000
4.750 0.9915 0.01971 0.00983 -0.0720 0.4184 1.0000
5.000 1.0099 0.02008 0.01013 -0.0702 0.4094 1.0000
5.250 1.0281 0.02045 0.01047 -0.0684 0.4008 1.0000
5.500 1.0457 0.02084 0.01083 -0.0666 0.3920 1.0000
5.750 1.0639 0.02124 0.01117 -0.0648 0.3845 1.0000
6.000 1.0808 0.02164 0.01160 -0.0629 0.3763 1.0000
6.250 1.0988 0.02207 0.01194 -0.0612 0.3695 1.0000
6.500 1.1147 0.02249 0.01242 -0.0591 0.3617 1.0000
6.750 1.1309 0.02293 0.01283 -0.0571 0.3545 1.0000
7.000 1.1472 0.02338 0.01326 -0.0552 0.3480 1.0000
7.250 1.1620 0.02385 0.01378 -0.0530 0.3409 1.0000
7.500 1.1781 0.02431 0.01420 -0.0510 0.3351 1.0000
7.750 1.1932 0.02482 0.01474 -0.0490 0.3292 1.0000
8.000 1.2071 0.02533 0.01530 -0.0467 0.3231 1.0000
8.250 1.2214 0.02581 0.01574 -0.0446 0.3178 1.0000
8.500 1.2320 0.02634 0.01631 -0.0418 0.3119 1.0000
8.750 1.2412 0.02685 0.01687 -0.0388 0.3059 1.0000
9.000 1.2527 0.02735 0.01733 -0.0363 0.3006 1.0000
9.250 1.2618 0.02795 0.01800 -0.0335 0.2950 1.0000
9.500 1.2705 0.02856 0.01868 -0.0308 0.2893 1.0000
9.750 1.2817 0.02915 0.01923 -0.0285 0.2843 1.0000
10.000 1.2906 0.02986 0.02001 -0.0261 0.2791 1.0000
10.250 1.2991 0.03061 0.02086 -0.0237 0.2739 1.0000
10.500 1.3093 0.03133 0.02160 -0.0216 0.2693 1.0000
10.750 1.3214 0.03205 0.02232 -0.0197 0.2653 1.0000
11.000 1.3283 0.03301 0.02343 -0.0175 0.2607 1.0000
11.250 1.3363 0.03393 0.02446 -0.0155 0.2562 1.0000
11.500 1.3454 0.03479 0.02532 -0.0136 0.2517 1.0000
11.750 1.3507 0.03589 0.02651 -0.0115 0.2467 1.0000
12.000 1.3536 0.03716 0.02791 -0.0095 0.2413 1.0000
12.250 1.3597 0.03830 0.02910 -0.0077 0.2367 1.0000
12.500 1.3669 0.03943 0.03027 -0.0061 0.2324 1.0000
12.750 1.3657 0.04117 0.03220 -0.0043 0.2269 1.0000
13.000 1.3666 0.04279 0.03389 -0.0027 0.2213 1.0000
13.250 1.3696 0.04432 0.03545 -0.0013 0.2163 1.0000
13.500 1.3667 0.04652 0.03786 0.0000 0.2110 1.0000
13.750 1.3648 0.04863 0.04007 0.0012 0.2054 1.0000
14.000 1.3637 0.05076 0.04226 0.0021 0.2002 1.0000
14.250 1.3559 0.05378 0.04549 0.0029 0.1940 1.0000
14.500 1.3512 0.05646 0.04822 0.0034 0.1879 1.0000
14.750 1.3398 0.06022 0.05218 0.0036 0.1811 1.0000
15.000 1.3296 0.06394 0.05598 0.0035 0.1741 1.0000
15.250 1.3151 0.06850 0.06071 0.0030 0.1669 1.0000
15.500 1.3004 0.07320 0.06548 0.0023 0.1591 1.0000
15.750 1.2796 0.07916 0.07161 0.0009 0.1511 1.0000
16.000 1.2618 0.08476 0.07726 -0.0005 0.1431 1.0000
16.250 1.2429 0.09073 0.08329 -0.0022 0.1345 1.0000
16.500 1.2253 0.09666 0.08928 -0.0040 0.1268 1.0000
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Polar data table (+)
Polar graphs
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