GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Reynolds number: 50,000 Max Cl/Cd: 29.31 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe323-il-50000-n5.txt Download as CSV file: xf-goe323-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3005 0.11487 0.10895 -0.0131 1.0000 0.1044
-9.000 -0.2946 0.11284 0.10685 -0.0179 0.9006 0.1091
-8.750 -0.3009 0.11240 0.10636 -0.0245 0.8692 0.1108
-8.500 -0.2858 0.10729 0.10120 -0.0236 0.8520 0.1124
-8.250 -0.2694 0.10322 0.09704 -0.0221 0.8373 0.1154
-8.000 -0.2603 0.10037 0.09412 -0.0227 0.8246 0.1189
-7.750 -0.2555 0.09797 0.09168 -0.0248 0.8133 0.1232
-7.500 -0.2612 0.09719 0.09087 -0.0344 0.8027 0.1269
-7.250 -0.2498 0.09297 0.08663 -0.0340 0.7951 0.1286
-7.000 -0.2334 0.08925 0.08289 -0.0311 0.7874 0.1325
-6.750 -0.2231 0.08664 0.08022 -0.0334 0.7802 0.1393
-6.500 -0.2153 0.08399 0.07751 -0.0412 0.7732 0.1453
-6.250 -0.2001 0.08060 0.07413 -0.0383 0.7666 0.1502
-5.750 -0.1728 0.07486 0.06827 -0.0449 0.7546 0.1642
-5.500 -0.1567 0.07214 0.06552 -0.0456 0.7490 0.1711
-5.250 -0.1409 0.06931 0.06256 -0.0493 0.7443 0.1805
-5.000 -0.1229 0.06672 0.05995 -0.0504 0.7384 0.1890
-4.750 -0.1054 0.06395 0.05712 -0.0524 0.7330 0.1993
-4.500 -0.0872 0.06149 0.05456 -0.0542 0.7284 0.2142
-4.250 -0.0693 0.05912 0.05217 -0.0549 0.7233 0.2317
-3.750 0.0176 0.04955 0.04114 -0.0688 0.7141 0.0938
-3.500 0.0414 0.04717 0.03858 -0.0693 0.7099 0.0901
-3.250 0.0691 0.04470 0.03574 -0.0708 0.7044 0.0852
-3.000 0.0982 0.04279 0.03331 -0.0716 0.6997 0.0815
-2.750 0.1244 0.04112 0.03133 -0.0718 0.6957 0.0813
-2.500 0.1515 0.03976 0.02963 -0.0723 0.6908 0.0819
-2.250 0.1783 0.03853 0.02808 -0.0726 0.6855 0.0822
-2.000 0.2049 0.03726 0.02655 -0.0725 0.6810 0.0819
-1.750 0.2317 0.03615 0.02517 -0.0724 0.6767 0.0817
-1.500 0.2583 0.03531 0.02414 -0.0726 0.6707 0.0816
-1.250 0.2854 0.03448 0.02305 -0.0723 0.6656 0.0818
-1.000 0.3126 0.03366 0.02200 -0.0718 0.6614 0.0832
-0.750 0.3378 0.03323 0.02159 -0.0721 0.6540 0.0858
-0.500 0.3647 0.03270 0.02092 -0.0716 0.6483 0.0884
-0.250 0.3914 0.03227 0.02033 -0.0710 0.6424 0.0900
0.000 0.4182 0.03202 0.01993 -0.0707 0.6349 0.0917
0.250 0.4459 0.03159 0.01931 -0.0698 0.6297 0.0942
0.500 0.4703 0.03155 0.01927 -0.0695 0.6219 0.0985
0.750 0.4955 0.03135 0.01904 -0.0689 0.6156 0.1045
1.000 0.5213 0.03118 0.01872 -0.0680 0.6101 0.1099
1.250 0.5444 0.03132 0.01894 -0.0678 0.6016 0.1172
1.500 0.5707 0.03106 0.01866 -0.0670 0.5962 0.1320
1.750 0.5939 0.03126 0.01904 -0.0668 0.5877 0.1573
2.000 0.6249 0.02914 0.01888 -0.0667 0.5812 1.0000
2.250 0.6492 0.02956 0.01899 -0.0659 0.5740 1.0000
2.500 0.6724 0.03004 0.01929 -0.0653 0.5655 1.0000
2.750 0.6999 0.02998 0.01899 -0.0642 0.5606 1.0000
3.000 0.7195 0.03088 0.01986 -0.0638 0.5494 1.0000
3.250 0.7470 0.03076 0.01955 -0.0628 0.5441 1.0000
3.500 0.7663 0.03165 0.02045 -0.0624 0.5327 1.0000
3.750 0.7941 0.03146 0.02010 -0.0613 0.5273 1.0000
4.000 0.8128 0.03237 0.02103 -0.0608 0.5155 1.0000
4.500 0.8591 0.03303 0.02161 -0.0593 0.4980 1.0000
4.750 0.8818 0.03339 0.02194 -0.0585 0.4890 1.0000
5.000 0.9054 0.03361 0.02215 -0.0576 0.4803 1.0000
5.250 0.9244 0.03437 0.02294 -0.0569 0.4695 1.0000
5.500 0.9517 0.03411 0.02261 -0.0560 0.4627 1.0000
5.750 0.9678 0.03517 0.02375 -0.0553 0.4509 1.0000
6.000 0.9931 0.03514 0.02369 -0.0544 0.4436 1.0000
6.250 1.0116 0.03587 0.02446 -0.0536 0.4332 1.0000
6.500 1.0284 0.03679 0.02544 -0.0528 0.4229 1.0000
6.750 1.0548 0.03661 0.02523 -0.0519 0.4161 1.0000
7.000 1.0676 0.03796 0.02667 -0.0511 0.4053 1.0000
7.250 1.0972 0.03744 0.02609 -0.0501 0.3996 1.0000
7.500 1.1061 0.03919 0.02797 -0.0494 0.3889 1.0000
7.750 1.1351 0.03878 0.02751 -0.0484 0.3832 1.0000
8.000 1.1426 0.04064 0.02948 -0.0476 0.3731 1.0000
8.250 1.1709 0.04034 0.02916 -0.0466 0.3674 1.0000
8.500 1.1746 0.04257 0.03152 -0.0457 0.3580 1.0000
8.750 1.2071 0.04196 0.03086 -0.0448 0.3531 1.0000
9.000 1.1988 0.04525 0.03432 -0.0438 0.3438 1.0000
9.250 1.2298 0.04483 0.03389 -0.0429 0.3383 1.0000
9.500 1.2166 0.04860 0.03782 -0.0420 0.3300 1.0000
9.750 1.2355 0.04931 0.03856 -0.0411 0.3241 1.0000
10.000 1.2510 0.05047 0.03977 -0.0403 0.3186 1.0000
10.250 1.2221 0.05669 0.04617 -0.0410 0.3098 1.0000
10.500 1.2661 0.05439 0.04389 -0.0391 0.3058 1.0000
10.750 1.1869 0.06766 0.05735 -0.0426 0.2941 1.0000
11.000 1.2325 0.06442 0.05416 -0.0402 0.2906 1.0000
11.250 1.1423 0.08097 0.07081 -0.0456 0.2771 1.0000
11.500 1.1910 0.07650 0.06643 -0.0425 0.2744 1.0000
12.000 1.1579 0.08806 0.07812 -0.0450 0.2581 1.0000
12.500 1.1258 0.10033 0.09052 -0.0482 0.2423 1.0000
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Polar data table (+)
Polar graphs
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