GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Reynolds number: 200,000 Max Cl/Cd: 69.49 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe315-il-200000-n5.txt Download as CSV file: xf-goe315-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 315 (HANSA-BRANDENBURG III.5) 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 -0.3457 0.08861 0.08511 -0.0212 1.0000 0.0267
-7.750 -0.3443 0.08597 0.08252 -0.0217 1.0000 0.0272
-7.500 -0.3453 0.08344 0.08005 -0.0220 1.0000 0.0279
-7.250 -0.3433 0.08065 0.07731 -0.0238 1.0000 0.0292
-7.000 -0.3378 0.07724 0.07391 -0.0317 1.0000 0.0306
-6.750 -0.3284 0.07361 0.07023 -0.0359 1.0000 0.0309
-6.500 -0.3044 0.06890 0.06542 -0.0418 0.9883 0.0309
-6.250 -0.2813 0.06331 0.05978 -0.0463 0.9723 0.0312
-6.000 -0.2605 0.05958 0.05607 -0.0481 0.9516 0.0319
-5.750 -0.2306 0.05618 0.05260 -0.0521 0.9265 0.0332
-5.500 -0.1930 0.05241 0.04865 -0.0583 0.8991 0.0364
-5.250 -0.1460 0.04892 0.04454 -0.0654 0.8690 0.0390
-5.000 -0.1190 0.04581 0.04111 -0.0671 0.8441 0.0391
-4.750 -0.1037 0.04111 0.03636 -0.0681 0.8238 0.0401
-4.500 -0.0847 0.03911 0.03428 -0.0681 0.8055 0.0415
-4.250 -0.0631 0.03725 0.03225 -0.0682 0.7895 0.0436
-4.000 -0.0311 0.03657 0.03097 -0.0681 0.7752 0.0492
-3.750 -0.0068 0.03487 0.02894 -0.0677 0.7624 0.0494
-3.500 0.0132 0.03106 0.02493 -0.0678 0.7512 0.0502
-3.250 0.0346 0.02885 0.02263 -0.0676 0.7399 0.0513
-2.750 0.0874 0.02430 0.01730 -0.0659 0.7184 0.0386
-2.500 0.1118 0.02254 0.01530 -0.0654 0.7082 0.0379
-2.250 0.1372 0.02111 0.01361 -0.0648 0.6973 0.0376
-2.000 0.1632 0.01991 0.01217 -0.0643 0.6864 0.0377
-1.750 0.1899 0.01925 0.01121 -0.0636 0.6757 0.0388
-1.500 0.2160 0.01820 0.00996 -0.0630 0.6647 0.0387
-1.250 0.2423 0.01724 0.00881 -0.0625 0.6532 0.0385
-1.000 0.2687 0.01644 0.00785 -0.0620 0.6415 0.0385
-0.750 0.2950 0.01579 0.00703 -0.0615 0.6284 0.0386
-0.500 0.3211 0.01524 0.00633 -0.0609 0.6138 0.0388
-0.250 0.3471 0.01479 0.00573 -0.0602 0.5976 0.0390
0.000 0.3725 0.01416 0.00502 -0.0596 0.5823 0.0399
0.250 0.3978 0.01376 0.00457 -0.0590 0.5695 0.0415
0.500 0.4237 0.01348 0.00427 -0.0585 0.5591 0.0428
0.750 0.4496 0.01321 0.00397 -0.0580 0.5505 0.0433
1.000 0.4754 0.01300 0.00374 -0.0575 0.5422 0.0440
1.250 0.5013 0.01284 0.00355 -0.0570 0.5340 0.0449
1.500 0.5272 0.01274 0.00341 -0.0565 0.5254 0.0460
1.750 0.5534 0.01267 0.00330 -0.0560 0.5169 0.0475
2.000 0.5795 0.01267 0.00323 -0.0556 0.5084 0.0493
2.250 0.6058 0.01262 0.00320 -0.0552 0.5002 0.0549
2.500 0.6320 0.01266 0.00320 -0.0548 0.4921 0.0607
2.750 0.6580 0.01256 0.00329 -0.0543 0.4833 0.1200
3.250 0.7309 0.01101 0.00349 -0.0582 0.4526 1.0000
3.500 0.7555 0.01117 0.00356 -0.0575 0.4329 1.0000
3.750 0.7798 0.01136 0.00364 -0.0568 0.4093 1.0000
4.000 0.8036 0.01161 0.00374 -0.0560 0.3811 1.0000
4.250 0.8270 0.01191 0.00390 -0.0551 0.3531 1.0000
4.500 0.8505 0.01224 0.00410 -0.0544 0.3289 1.0000
4.750 0.8735 0.01262 0.00435 -0.0536 0.3061 1.0000
5.000 0.8966 0.01300 0.00464 -0.0528 0.2844 1.0000
5.250 0.9200 0.01337 0.00493 -0.0521 0.2684 1.0000
5.500 0.9434 0.01374 0.00525 -0.0514 0.2547 1.0000
5.750 0.9666 0.01412 0.00559 -0.0507 0.2415 1.0000
6.000 0.9897 0.01451 0.00595 -0.0499 0.2288 1.0000
6.250 1.0128 0.01489 0.00631 -0.0492 0.2167 1.0000
6.500 1.0359 0.01528 0.00669 -0.0485 0.2032 1.0000
6.750 1.0589 0.01566 0.00709 -0.0478 0.1898 1.0000
7.000 1.0814 0.01610 0.00751 -0.0470 0.1732 1.0000
7.250 1.1018 0.01672 0.00800 -0.0460 0.1385 1.0000
7.500 1.1137 0.01820 0.00903 -0.0441 0.0778 1.0000
7.750 1.1316 0.01908 0.00984 -0.0428 0.0531 1.0000
8.000 1.1497 0.01989 0.01060 -0.0415 0.0459 1.0000
8.250 1.1682 0.02063 0.01137 -0.0403 0.0429 1.0000
8.500 1.1864 0.02135 0.01215 -0.0390 0.0412 1.0000
8.750 1.2043 0.02206 0.01300 -0.0377 0.0401 1.0000
9.000 1.2207 0.02284 0.01390 -0.0363 0.0389 1.0000
9.250 1.2349 0.02373 0.01490 -0.0346 0.0375 1.0000
9.500 1.2467 0.02473 0.01600 -0.0327 0.0364 1.0000
9.750 1.2546 0.02585 0.01721 -0.0302 0.0356 1.0000
10.000 1.2567 0.02715 0.01861 -0.0271 0.0347 1.0000
10.250 1.2586 0.02855 0.02008 -0.0244 0.0340 1.0000
10.500 1.2644 0.02981 0.02147 -0.0223 0.0333 1.0000
10.750 1.2690 0.03128 0.02306 -0.0205 0.0325 1.0000
11.000 1.2725 0.03296 0.02485 -0.0190 0.0318 1.0000
11.250 1.2756 0.03483 0.02681 -0.0178 0.0311 1.0000
11.500 1.2782 0.03687 0.02896 -0.0168 0.0303 1.0000
11.750 1.2803 0.03907 0.03123 -0.0161 0.0295 1.0000
12.000 1.2819 0.04141 0.03361 -0.0154 0.0288 1.0000
12.250 1.2826 0.04393 0.03613 -0.0145 0.0279 1.0000
12.500 1.2875 0.04608 0.03839 -0.0139 0.0273 1.0000
12.750 1.2923 0.04827 0.04074 -0.0137 0.0267 1.0000
13.000 1.2963 0.05060 0.04321 -0.0135 0.0258 1.0000
13.250 1.2993 0.05308 0.04583 -0.0135 0.0249 1.0000
13.500 1.3024 0.05560 0.04846 -0.0134 0.0242 1.0000
13.750 1.3051 0.05820 0.05114 -0.0135 0.0235 1.0000
14.000 1.3088 0.06072 0.05372 -0.0134 0.0229 1.0000
14.250 1.3158 0.06289 0.05585 -0.0128 0.0221 1.0000
14.500 1.3137 0.06625 0.05945 -0.0136 0.0217 1.0000
14.750 1.3114 0.06976 0.06318 -0.0145 0.0211 1.0000
15.000 1.3080 0.07351 0.06713 -0.0156 0.0204 1.0000
15.250 1.3049 0.07731 0.07110 -0.0168 0.0198 1.0000
15.500 1.3016 0.08126 0.07521 -0.0182 0.0193 1.0000
15.750 1.2981 0.08532 0.07942 -0.0198 0.0188 1.0000
16.000 1.2944 0.08951 0.08373 -0.0214 0.0185 1.0000
16.250 1.2905 0.09379 0.08814 -0.0232 0.0182 1.0000
16.500 1.2874 0.09801 0.09245 -0.0251 0.0179 1.0000
16.750 1.2850 0.10214 0.09666 -0.0268 0.0176 1.0000
17.000 1.2738 0.10823 0.10297 -0.0299 0.0174 1.0000
17.250 1.2597 0.11515 0.11014 -0.0337 0.0171 1.0000
17.500 1.2461 0.12221 0.11743 -0.0377 0.0169 1.0000
17.750 1.2304 0.13003 0.12547 -0.0425 0.0166 1.0000
18.000 1.2150 0.13797 0.13361 -0.0473 0.0166 1.0000
18.250 1.1972 0.14691 0.14276 -0.0529 0.0164 1.0000
18.500 1.1770 0.15686 0.15289 -0.0593 0.0164 1.0000
18.750 1.1524 0.16864 0.16485 -0.0669 0.0165 1.0000
19.000 1.1157 0.18531 0.18167 -0.0774 0.0169 1.0000
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