GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.23 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe322-il-1000000-n5.txt Download as CSV file: xf-goe322-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2526 0.09270 0.08982 -0.0334 0.6572 0.0143
-9.000 -0.2487 0.08896 0.08608 -0.0356 0.6541 0.0147
-8.750 -0.2655 0.08034 0.07748 -0.0413 0.6519 0.0160
-8.500 -0.2582 0.07762 0.07475 -0.0435 0.6483 0.0161
-8.250 -0.2522 0.07489 0.07202 -0.0460 0.6451 0.0162
-8.000 -0.2402 0.07182 0.06895 -0.0499 0.6421 0.0164
-7.750 -0.2273 0.06824 0.06535 -0.0544 0.6387 0.0165
-7.500 -0.2131 0.06430 0.06137 -0.0593 0.6351 0.0168
-7.000 -0.2017 0.03670 0.03314 -0.0828 0.6307 0.0194
-6.750 -0.1960 0.02242 0.01798 -0.0864 0.6287 0.0206
-6.500 -0.1730 0.01954 0.01469 -0.0867 0.6249 0.0209
-6.250 -0.1473 0.01792 0.01280 -0.0869 0.6201 0.0212
-6.000 -0.1207 0.01676 0.01140 -0.0869 0.6153 0.0214
-5.750 -0.0934 0.01577 0.01022 -0.0870 0.6112 0.0216
-5.500 -0.0656 0.01498 0.00927 -0.0871 0.6065 0.0218
-5.250 -0.0375 0.01431 0.00844 -0.0872 0.6008 0.0220
-5.000 -0.0092 0.01373 0.00773 -0.0873 0.5947 0.0222
-4.750 0.0192 0.01325 0.00712 -0.0874 0.5865 0.0224
-4.500 0.0479 0.01291 0.00667 -0.0875 0.5788 0.0226
-4.250 0.0767 0.01262 0.00627 -0.0877 0.5704 0.0227
-4.000 0.1054 0.01231 0.00586 -0.0878 0.5625 0.0228
-3.750 0.1339 0.01182 0.00528 -0.0879 0.5543 0.0230
-3.500 0.1624 0.01134 0.00472 -0.0880 0.5479 0.0233
-3.250 0.1912 0.01103 0.00437 -0.0882 0.5424 0.0236
-3.000 0.2201 0.01080 0.00409 -0.0884 0.5369 0.0238
-2.750 0.2491 0.01060 0.00385 -0.0885 0.5316 0.0241
-2.500 0.2781 0.01041 0.00364 -0.0887 0.5259 0.0243
-2.250 0.3071 0.01025 0.00344 -0.0889 0.5202 0.0245
-2.000 0.3361 0.01010 0.00325 -0.0891 0.5158 0.0248
-1.750 0.3653 0.00995 0.00308 -0.0893 0.5111 0.0251
-1.500 0.3943 0.00983 0.00292 -0.0895 0.5056 0.0254
-1.250 0.4233 0.00973 0.00279 -0.0897 0.4998 0.0257
-1.000 0.4525 0.00963 0.00266 -0.0899 0.4929 0.0260
-0.750 0.4813 0.00958 0.00256 -0.0901 0.4851 0.0263
-0.500 0.5105 0.00951 0.00248 -0.0903 0.4789 0.0268
-0.250 0.5396 0.00948 0.00242 -0.0905 0.4724 0.0271
0.000 0.5686 0.00944 0.00236 -0.0907 0.4657 0.0274
0.250 0.5974 0.00939 0.00226 -0.0909 0.4556 0.0282
0.500 0.6263 0.00937 0.00222 -0.0912 0.4462 0.0289
0.750 0.6549 0.00941 0.00221 -0.0913 0.4352 0.0297
1.000 0.6836 0.00945 0.00221 -0.0916 0.4237 0.0304
1.250 0.7122 0.00950 0.00222 -0.0918 0.4131 0.0313
1.500 0.7407 0.00959 0.00225 -0.0919 0.4014 0.0322
1.750 0.7688 0.00970 0.00231 -0.0921 0.3874 0.0341
2.250 0.8243 0.00994 0.00252 -0.0924 0.3555 0.0753
2.500 0.8521 0.01010 0.00263 -0.0925 0.3430 0.0869
2.750 0.8799 0.01018 0.00277 -0.0927 0.3317 0.1264
3.000 0.9076 0.01030 0.00289 -0.0928 0.3229 0.1540
3.250 0.9347 0.00979 0.00311 -0.0933 0.3153 0.5122
3.500 0.9598 0.00888 0.00331 -0.0929 0.3093 1.0000
3.750 0.9876 0.00903 0.00342 -0.0930 0.3039 1.0000
4.000 1.0151 0.00922 0.00356 -0.0931 0.2978 1.0000
4.250 1.0426 0.00939 0.00369 -0.0932 0.2927 1.0000
4.500 1.0703 0.00955 0.00382 -0.0933 0.2876 1.0000
4.750 1.0974 0.00975 0.00398 -0.0934 0.2817 1.0000
5.000 1.1246 0.00994 0.00414 -0.0935 0.2767 1.0000
5.250 1.1517 0.01012 0.00430 -0.0935 0.2713 1.0000
5.500 1.1783 0.01035 0.00448 -0.0935 0.2650 1.0000
5.750 1.2051 0.01055 0.00466 -0.0936 0.2598 1.0000
6.000 1.2308 0.01084 0.00489 -0.0935 0.2499 1.0000
6.250 1.2556 0.01119 0.00515 -0.0932 0.2357 1.0000
6.500 1.2802 0.01154 0.00543 -0.0930 0.2231 1.0000
6.750 1.3036 0.01197 0.00577 -0.0926 0.2076 1.0000
7.000 1.3266 0.01241 0.00612 -0.0921 0.1940 1.0000
7.250 1.3496 0.01283 0.00648 -0.0916 0.1833 1.0000
7.500 1.3720 0.01327 0.00686 -0.0911 0.1739 1.0000
7.750 1.3940 0.01371 0.00725 -0.0905 0.1656 1.0000
8.000 1.4166 0.01409 0.00761 -0.0900 0.1599 1.0000
8.250 1.4381 0.01451 0.00801 -0.0893 0.1537 1.0000
8.500 1.4585 0.01498 0.00844 -0.0885 0.1470 1.0000
8.750 1.4788 0.01542 0.00886 -0.0876 0.1404 1.0000
9.000 1.4960 0.01600 0.00940 -0.0863 0.1312 1.0000
9.250 1.4931 0.01744 0.01059 -0.0820 0.0972 1.0000
9.500 1.4668 0.02045 0.01336 -0.0755 0.0443 1.0000
9.750 1.4620 0.02276 0.01559 -0.0729 0.0163 1.0000
10.000 1.4740 0.02397 0.01684 -0.0720 0.0140 1.0000
10.250 1.4864 0.02522 0.01812 -0.0714 0.0129 1.0000
10.500 1.4977 0.02660 0.01955 -0.0707 0.0120 1.0000
10.750 1.5093 0.02797 0.02097 -0.0701 0.0114 1.0000
11.000 1.5207 0.02938 0.02243 -0.0696 0.0110 1.0000
11.250 1.5307 0.03091 0.02400 -0.0690 0.0105 1.0000
11.500 1.5395 0.03256 0.02569 -0.0683 0.0100 1.0000
11.750 1.5468 0.03434 0.02753 -0.0676 0.0096 1.0000
12.000 1.5521 0.03632 0.02956 -0.0669 0.0091 1.0000
12.250 1.5591 0.03814 0.03144 -0.0662 0.0089 1.0000
12.500 1.5649 0.04010 0.03345 -0.0656 0.0086 1.0000
12.750 1.5698 0.04217 0.03558 -0.0650 0.0084 1.0000
13.000 1.5737 0.04432 0.03779 -0.0644 0.0081 1.0000
13.250 1.5766 0.04662 0.04016 -0.0638 0.0079 1.0000
13.500 1.5790 0.04908 0.04268 -0.0633 0.0076 1.0000
13.750 1.5807 0.05169 0.04535 -0.0630 0.0075 1.0000
14.000 1.5812 0.05448 0.04820 -0.0627 0.0072 1.0000
14.250 1.5804 0.05750 0.05130 -0.0625 0.0071 1.0000
14.500 1.5790 0.06067 0.05454 -0.0623 0.0069 1.0000
14.750 1.5792 0.06369 0.05764 -0.0623 0.0068 1.0000
15.000 1.5781 0.06690 0.06092 -0.0624 0.0066 1.0000
15.250 1.5763 0.07024 0.06434 -0.0625 0.0065 1.0000
15.500 1.5741 0.07368 0.06787 -0.0627 0.0064 1.0000
15.750 1.5708 0.07731 0.07157 -0.0629 0.0062 1.0000
16.000 1.5661 0.08114 0.07548 -0.0633 0.0061 1.0000
16.250 1.5606 0.08514 0.07958 -0.0637 0.0060 1.0000
16.500 1.5543 0.08932 0.08385 -0.0643 0.0059 1.0000
16.750 1.5474 0.09364 0.08825 -0.0649 0.0058 1.0000
17.000 1.5398 0.09806 0.09276 -0.0657 0.0057 1.0000
17.250 1.5311 0.10271 0.09751 -0.0666 0.0056 1.0000
17.500 1.5221 0.10750 0.10239 -0.0676 0.0055 1.0000
17.750 1.5120 0.11253 0.10751 -0.0689 0.0055 1.0000
18.000 1.5012 0.11768 0.11275 -0.0702 0.0054 1.0000
18.250 1.4899 0.12299 0.11816 -0.0718 0.0053 1.0000
18.500 1.4785 0.12841 0.12367 -0.0735 0.0053 1.0000
18.750 1.4666 0.13399 0.12935 -0.0754 0.0052 1.0000
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