GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 403 AIRFOIL (goe403-il) Reynolds number: 500,000 Max Cl/Cd: 98.56 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe403-il-500000.txt Download as CSV file: xf-goe403-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 403 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3415 0.08984 0.08773 -0.0273 1.0000 0.0182
-7.500 -0.3446 0.08760 0.08554 -0.0268 1.0000 0.0182
-7.250 -0.3462 0.08510 0.08309 -0.0268 1.0000 0.0183
-7.000 -0.3454 0.08239 0.08042 -0.0278 1.0000 0.0183
-6.750 -0.3466 0.07989 0.07796 -0.0280 1.0000 0.0184
-6.500 -0.3143 0.07396 0.07200 -0.0377 0.9959 0.0184
-6.250 -0.2939 0.06523 0.06326 -0.0472 0.9899 0.0193
-6.000 -0.2646 0.06116 0.05915 -0.0530 0.9852 0.0200
-5.750 -0.2327 0.05690 0.05484 -0.0596 0.9797 0.0207
-5.500 -0.1985 0.05238 0.05024 -0.0667 0.9730 0.0222
-5.250 -0.1470 0.03898 0.03651 -0.0825 0.9651 0.0175
-5.000 -0.1071 0.02014 0.01650 -0.0938 0.9557 0.0172
-4.750 -0.0778 0.01624 0.01188 -0.0951 0.9449 0.0190
-4.500 -0.0475 0.01482 0.01025 -0.0961 0.9349 0.0213
-4.250 -0.0166 0.01391 0.00908 -0.0968 0.9242 0.0239
-4.000 0.0135 0.01328 0.00822 -0.0970 0.9124 0.0267
-3.750 0.0407 0.01190 0.00655 -0.0970 0.9001 0.0312
-3.250 0.0956 0.01117 0.00552 -0.0965 0.8757 0.0377
-3.000 0.1225 0.01082 0.00498 -0.0962 0.8643 0.0399
-2.750 0.1483 0.00983 0.00383 -0.0957 0.8537 0.0428
-2.500 0.1748 0.00954 0.00346 -0.0953 0.8435 0.0460
-2.250 0.2013 0.00924 0.00305 -0.0948 0.8332 0.0487
-2.000 0.2278 0.00899 0.00271 -0.0944 0.8227 0.0506
-1.750 0.2544 0.00879 0.00242 -0.0940 0.8125 0.0518
-1.500 0.2806 0.00846 0.00201 -0.0935 0.8024 0.0550
-1.250 0.3071 0.00828 0.00180 -0.0931 0.7917 0.0605
-1.000 0.3335 0.00809 0.00164 -0.0927 0.7801 0.0795
-0.750 0.3600 0.00794 0.00156 -0.0923 0.7680 0.1169
-0.500 0.3865 0.00787 0.00149 -0.0919 0.7547 0.1361
-0.250 0.4128 0.00779 0.00142 -0.0915 0.7398 0.1564
0.000 0.4389 0.00769 0.00137 -0.0911 0.7231 0.1896
0.250 0.4644 0.00748 0.00136 -0.0907 0.7030 0.2789
0.500 0.5008 0.00585 0.00140 -0.0929 0.6794 1.0000
1.000 0.5508 0.00616 0.00138 -0.0915 0.6266 1.0000
1.250 0.5760 0.00634 0.00141 -0.0909 0.6026 1.0000
1.500 0.6013 0.00653 0.00147 -0.0903 0.5829 1.0000
1.750 0.6269 0.00670 0.00154 -0.0898 0.5658 1.0000
2.000 0.6526 0.00688 0.00162 -0.0893 0.5508 1.0000
2.250 0.6777 0.00710 0.00172 -0.0888 0.5309 1.0000
2.500 0.7028 0.00730 0.00183 -0.0882 0.5072 1.0000
2.750 0.7285 0.00748 0.00193 -0.0878 0.4915 1.0000
3.000 0.7541 0.00766 0.00205 -0.0873 0.4751 1.0000
3.250 0.7786 0.00790 0.00214 -0.0867 0.4398 1.0000
3.500 0.8026 0.00822 0.00227 -0.0860 0.3962 1.0000
3.750 0.8230 0.00894 0.00252 -0.0848 0.3020 1.0000
4.000 0.8343 0.01094 0.00343 -0.0826 0.0908 1.0000
4.250 0.8549 0.01186 0.00408 -0.0813 0.0205 1.0000
4.500 0.8798 0.01221 0.00454 -0.0807 0.0180 1.0000
4.750 0.9035 0.01273 0.00521 -0.0798 0.0167 1.0000
5.000 0.9266 0.01331 0.00591 -0.0788 0.0162 1.0000
5.250 0.9486 0.01402 0.00672 -0.0776 0.0161 1.0000
5.500 0.9704 0.01468 0.00746 -0.0766 0.0150 1.0000
5.750 0.9908 0.01551 0.00837 -0.0752 0.0142 1.0000
6.000 1.0094 0.01652 0.00948 -0.0735 0.0139 1.0000
6.250 1.0267 0.01772 0.01076 -0.0716 0.0138 1.0000
6.500 1.0429 0.01929 0.01241 -0.0694 0.0146 1.0000
7.000 1.0957 0.02266 0.01591 -0.0666 0.0288 1.0000
7.250 1.1169 0.02496 0.01833 -0.0657 0.0237 1.0000
7.500 1.1394 0.02625 0.01973 -0.0648 0.0214 1.0000
7.750 1.1615 0.02803 0.02153 -0.0641 0.0194 1.0000
8.250 1.1968 0.03284 0.02680 -0.0614 0.0147 1.0000
8.500 1.2147 0.03452 0.02870 -0.0599 0.0135 1.0000
8.750 1.2302 0.03658 0.03097 -0.0583 0.0126 1.0000
9.000 1.2436 0.03891 0.03348 -0.0566 0.0119 1.0000
9.250 1.2560 0.04166 0.03633 -0.0553 0.0112 1.0000
9.500 1.2665 0.04533 0.04014 -0.0539 0.0107 1.0000
9.750 1.2490 0.05662 0.05191 -0.0509 0.0099 1.0000
10.000 1.2467 0.05981 0.05536 -0.0481 0.0098 1.0000
10.250 1.2407 0.06293 0.05871 -0.0452 0.0098 1.0000
10.500 1.2297 0.06595 0.06196 -0.0421 0.0098 1.0000
10.750 1.2150 0.06852 0.06469 -0.0384 0.0098 1.0000
11.000 1.1966 0.07124 0.06758 -0.0354 0.0098 1.0000
11.250 1.1795 0.07447 0.07095 -0.0337 0.0098 1.0000
11.500 1.1620 0.07814 0.07477 -0.0331 0.0098 1.0000
11.750 1.1446 0.08229 0.07906 -0.0335 0.0098 1.0000
12.000 1.1255 0.08702 0.08393 -0.0349 0.0098 1.0000
12.250 1.1082 0.09219 0.08924 -0.0371 0.0098 1.0000
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Polar data table (+)
Polar graphs
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