GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Reynolds number: 200,000 Max Cl/Cd: 73.37 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe325-il-200000-n5.txt Download as CSV file: xf-goe325-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 325 (PFALZ 54) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3211 0.09442 0.09108 -0.0259 1.0000 0.0202
-7.750 -0.3213 0.09174 0.08845 -0.0250 1.0000 0.0195
-7.500 -0.3275 0.08961 0.08638 -0.0235 1.0000 0.0190
-7.250 -0.3370 0.08772 0.08456 -0.0216 1.0000 0.0187
-7.000 -0.3422 0.08531 0.08220 -0.0210 1.0000 0.0184
-6.750 -0.3235 0.08062 0.07751 -0.0276 0.9956 0.0189
-6.500 -0.2962 0.07477 0.07162 -0.0377 0.9896 0.0201
-6.250 -0.2665 0.06884 0.06563 -0.0470 0.9847 0.0202
-6.000 -0.2351 0.06277 0.05947 -0.0559 0.9789 0.0203
-5.750 -0.1936 0.05482 0.05132 -0.0676 0.9735 0.0211
-5.500 -0.1713 0.05353 0.05004 -0.0689 0.9686 0.0228
-5.250 -0.1372 0.05010 0.04649 -0.0741 0.9647 0.0249
-5.000 -0.1055 0.04513 0.04132 -0.0793 0.9571 0.0253
-4.750 -0.0660 0.03980 0.03568 -0.0852 0.9518 0.0270
-4.500 -0.0311 0.03481 0.03027 -0.0882 0.9420 0.0292
-4.250 -0.0003 0.02978 0.02479 -0.0909 0.9324 0.0307
-4.000 0.0260 0.02881 0.02377 -0.0916 0.9200 0.0327
-3.750 0.0540 0.02692 0.02165 -0.0922 0.9076 0.0346
-3.500 0.0822 0.02427 0.01863 -0.0925 0.8946 0.0353
-3.250 0.1107 0.02217 0.01618 -0.0927 0.8802 0.0368
-3.000 0.1395 0.02034 0.01397 -0.0927 0.8633 0.0385
-2.750 0.1683 0.01861 0.01185 -0.0925 0.8425 0.0389
-2.500 0.1968 0.01726 0.01013 -0.0922 0.8165 0.0395
-2.250 0.2246 0.01625 0.00875 -0.0917 0.7852 0.0401
-2.000 0.2514 0.01567 0.00780 -0.0910 0.7507 0.0411
-1.750 0.2779 0.01532 0.00712 -0.0904 0.7169 0.0419
-1.500 0.3043 0.01470 0.00623 -0.0898 0.6840 0.0421
-1.250 0.3305 0.01413 0.00541 -0.0893 0.6502 0.0424
-1.000 0.3565 0.01367 0.00472 -0.0889 0.6167 0.0429
-0.750 0.3826 0.01333 0.00421 -0.0884 0.5885 0.0438
-0.500 0.4090 0.01312 0.00385 -0.0881 0.5671 0.0450
-0.250 0.4357 0.01299 0.00360 -0.0879 0.5497 0.0466
0.000 0.4626 0.01291 0.00341 -0.0877 0.5347 0.0486
0.250 0.4897 0.01287 0.00326 -0.0875 0.5214 0.0511
0.500 0.5168 0.01286 0.00314 -0.0874 0.5095 0.0541
0.750 0.5440 0.01285 0.00310 -0.0873 0.4980 0.0624
1.000 0.5714 0.01281 0.00306 -0.0872 0.4863 0.0781
1.250 0.5987 0.01269 0.00306 -0.0872 0.4747 0.1396
1.750 0.6471 0.01103 0.00318 -0.0856 0.4528 1.0000
2.000 0.6743 0.01119 0.00324 -0.0855 0.4410 1.0000
2.250 0.7014 0.01137 0.00331 -0.0853 0.4290 1.0000
2.500 0.7283 0.01155 0.00339 -0.0852 0.4170 1.0000
2.750 0.7550 0.01175 0.00350 -0.0850 0.4054 1.0000
3.000 0.7817 0.01197 0.00362 -0.0848 0.3946 1.0000
3.250 0.8084 0.01217 0.00377 -0.0847 0.3846 1.0000
3.500 0.8349 0.01241 0.00395 -0.0845 0.3759 1.0000
3.750 0.8614 0.01265 0.00413 -0.0843 0.3673 1.0000
4.000 0.8878 0.01289 0.00434 -0.0841 0.3593 1.0000
4.250 0.9140 0.01316 0.00458 -0.0839 0.3520 1.0000
4.500 0.9403 0.01342 0.00482 -0.0837 0.3457 1.0000
4.750 0.9666 0.01368 0.00509 -0.0835 0.3398 1.0000
5.000 0.9925 0.01400 0.00537 -0.0832 0.3348 1.0000
5.250 1.0189 0.01425 0.00570 -0.0831 0.3296 1.0000
5.500 1.0448 0.01455 0.00602 -0.0828 0.3244 1.0000
5.750 1.0704 0.01489 0.00635 -0.0825 0.3199 1.0000
6.000 1.0966 0.01517 0.00674 -0.0824 0.3151 1.0000
6.250 1.1218 0.01549 0.00707 -0.0820 0.3079 1.0000
6.500 1.1470 0.01575 0.00740 -0.0817 0.2974 1.0000
6.750 1.1717 0.01605 0.00773 -0.0813 0.2875 1.0000
7.000 1.1959 0.01636 0.00808 -0.0809 0.2755 1.0000
7.250 1.2202 0.01663 0.00840 -0.0804 0.2588 1.0000
7.500 1.2440 0.01696 0.00875 -0.0799 0.2390 1.0000
7.750 1.2668 0.01740 0.00916 -0.0793 0.2143 1.0000
8.000 1.2809 0.01882 0.01003 -0.0778 0.1263 1.0000
8.500 1.2994 0.02280 0.01332 -0.0734 0.0201 1.0000
8.750 1.3159 0.02382 0.01449 -0.0719 0.0174 1.0000
9.000 1.3320 0.02480 0.01564 -0.0704 0.0158 1.0000
9.250 1.3466 0.02582 0.01684 -0.0687 0.0146 1.0000
9.500 1.3585 0.02699 0.01819 -0.0667 0.0138 1.0000
9.750 1.3665 0.02829 0.01966 -0.0642 0.0132 1.0000
10.000 1.3699 0.02973 0.02129 -0.0611 0.0127 1.0000
10.250 1.3708 0.03143 0.02315 -0.0582 0.0123 1.0000
10.500 1.3686 0.03348 0.02534 -0.0554 0.0118 1.0000
10.750 1.3621 0.03605 0.02806 -0.0528 0.0114 1.0000
11.000 1.3523 0.03921 0.03137 -0.0508 0.0110 1.0000
11.250 1.3500 0.04197 0.03427 -0.0497 0.0107 1.0000
11.500 1.3502 0.04469 0.03713 -0.0491 0.0104 1.0000
11.750 1.3482 0.04786 0.04045 -0.0489 0.0101 1.0000
12.000 1.3451 0.05133 0.04405 -0.0489 0.0100 1.0000
12.250 1.3419 0.05490 0.04775 -0.0490 0.0098 1.0000
12.500 1.3390 0.05852 0.05149 -0.0493 0.0096 1.0000
12.750 1.3362 0.06211 0.05520 -0.0495 0.0094 1.0000
13.000 1.3340 0.06565 0.05887 -0.0496 0.0093 1.0000
13.250 1.3320 0.06915 0.06247 -0.0497 0.0091 1.0000
13.500 1.3304 0.07258 0.06605 -0.0498 0.0090 1.0000
13.750 1.3290 0.07601 0.06960 -0.0499 0.0088 1.0000
14.000 1.3279 0.07944 0.07315 -0.0500 0.0087 1.0000
14.250 1.3266 0.08295 0.07678 -0.0502 0.0086 1.0000
14.500 1.3245 0.08668 0.08064 -0.0507 0.0084 1.0000
14.750 1.3219 0.09057 0.08464 -0.0514 0.0082 1.0000
15.000 1.3189 0.09456 0.08875 -0.0524 0.0081 1.0000
15.250 1.3156 0.09862 0.09292 -0.0534 0.0079 1.0000
15.500 1.3125 0.10261 0.09700 -0.0543 0.0077 1.0000
15.750 1.3090 0.10662 0.10109 -0.0548 0.0075 1.0000
16.000 1.3017 0.11176 0.10639 -0.0567 0.0074 1.0000
16.250 1.2929 0.11754 0.11238 -0.0597 0.0073 1.0000
16.500 1.2844 0.12335 0.11839 -0.0627 0.0072 1.0000
16.750 1.2756 0.12939 0.12462 -0.0659 0.0072 1.0000
17.000 1.2662 0.13578 0.13120 -0.0694 0.0071 1.0000
17.250 1.2570 0.14227 0.13786 -0.0731 0.0071 1.0000
17.500 1.2475 0.14907 0.14483 -0.0772 0.0071 1.0000
17.750 1.2375 0.15622 0.15215 -0.0816 0.0071 1.0000
18.000 1.2274 0.16363 0.15972 -0.0864 0.0071 1.0000
18.250 1.2173 0.17142 0.16766 -0.0914 0.0072 1.0000
18.500 1.2072 0.17957 0.17594 -0.0968 0.0072 1.0000
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