GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.96 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe318-il-1000000-n5.txt Download as CSV file: xf-goe318-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.5) 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5581 0.14284 0.14063 0.0374 0.7567 0.0055
-11.750 -0.5521 0.13957 0.13732 0.0360 0.7465 0.0056
-7.750 -0.5438 0.02352 0.01952 -0.0414 0.6537 0.0164
-7.500 -0.5145 0.02459 0.02064 -0.0412 0.6473 0.0164
-7.250 -0.4867 0.02480 0.02083 -0.0412 0.6417 0.0166
-7.000 -0.4584 0.02550 0.02154 -0.0410 0.6359 0.0167
-6.750 -0.4308 0.02580 0.02181 -0.0410 0.6304 0.0168
-6.500 -0.4041 0.02519 0.02111 -0.0411 0.6259 0.0171
-6.250 -0.3778 0.02402 0.01981 -0.0414 0.6213 0.0174
-6.000 -0.3550 0.01894 0.01411 -0.0419 0.6174 0.0194
-5.750 -0.3286 0.01703 0.01185 -0.0420 0.6135 0.0203
-5.500 -0.3007 0.01651 0.01120 -0.0421 0.6091 0.0206
-5.250 -0.2736 0.01519 0.00962 -0.0422 0.6035 0.0210
-5.000 -0.2459 0.01441 0.00870 -0.0423 0.5983 0.0214
-4.750 -0.2176 0.01415 0.00840 -0.0423 0.5931 0.0218
-4.500 -0.1893 0.01380 0.00797 -0.0424 0.5877 0.0220
-4.250 -0.1610 0.01335 0.00741 -0.0425 0.5826 0.0223
-4.000 -0.1325 0.01287 0.00685 -0.0425 0.5783 0.0226
-3.750 -0.1040 0.01242 0.00631 -0.0426 0.5733 0.0229
-3.500 -0.0755 0.01200 0.00578 -0.0427 0.5678 0.0233
-3.250 -0.0469 0.01165 0.00537 -0.0427 0.5611 0.0238
-3.000 -0.0183 0.01131 0.00494 -0.0428 0.5543 0.0243
-2.750 0.0104 0.01094 0.00450 -0.0428 0.5492 0.0247
-2.500 0.0391 0.01062 0.00412 -0.0429 0.5422 0.0251
-2.250 0.0678 0.01034 0.00378 -0.0430 0.5350 0.0254
-2.000 0.0966 0.01009 0.00346 -0.0431 0.5263 0.0257
-1.750 0.1253 0.00986 0.00318 -0.0432 0.5166 0.0259
-1.500 0.1541 0.00968 0.00294 -0.0433 0.5053 0.0261
-1.250 0.1829 0.00951 0.00271 -0.0434 0.4946 0.0263
-1.000 0.2118 0.00935 0.00251 -0.0435 0.4851 0.0264
-0.750 0.2406 0.00922 0.00233 -0.0437 0.4751 0.0265
-0.500 0.2695 0.00905 0.00209 -0.0438 0.4640 0.0268
-0.250 0.2984 0.00883 0.00181 -0.0440 0.4529 0.0279
0.000 0.3273 0.00875 0.00168 -0.0442 0.4410 0.0286
0.250 0.3562 0.00872 0.00160 -0.0443 0.4283 0.0293
0.500 0.3851 0.00872 0.00154 -0.0445 0.4147 0.0301
0.750 0.4140 0.00873 0.00151 -0.0447 0.4015 0.0310
1.000 0.4428 0.00876 0.00149 -0.0449 0.3881 0.0319
1.250 0.4717 0.00881 0.00148 -0.0451 0.3745 0.0327
1.500 0.5005 0.00887 0.00149 -0.0453 0.3600 0.0335
1.750 0.5292 0.00896 0.00151 -0.0455 0.3442 0.0343
2.000 0.5579 0.00905 0.00155 -0.0457 0.3271 0.0361
2.250 0.5865 0.00916 0.00161 -0.0459 0.3088 0.0420
2.500 0.6151 0.00918 0.00172 -0.0462 0.2913 0.1123
2.750 0.6432 0.00842 0.00192 -0.0470 0.2770 0.5619
3.750 0.7526 0.00795 0.00234 -0.0467 0.2452 1.0000
4.000 0.7810 0.00811 0.00246 -0.0468 0.2401 1.0000
4.250 0.8095 0.00823 0.00257 -0.0470 0.2372 1.0000
4.500 0.8379 0.00836 0.00270 -0.0472 0.2342 1.0000
4.750 0.8662 0.00851 0.00283 -0.0474 0.2309 1.0000
5.000 0.8944 0.00870 0.00298 -0.0476 0.2263 1.0000
5.250 0.9226 0.00884 0.00313 -0.0477 0.2234 1.0000
5.500 0.9508 0.00898 0.00328 -0.0479 0.2206 1.0000
5.750 0.9789 0.00914 0.00344 -0.0481 0.2176 1.0000
6.000 1.0068 0.00933 0.00362 -0.0482 0.2136 1.0000
6.250 1.0346 0.00953 0.00381 -0.0484 0.2083 1.0000
6.500 1.0625 0.00968 0.00398 -0.0485 0.2050 1.0000
6.750 1.0901 0.00988 0.00417 -0.0487 0.1992 1.0000
7.000 1.1176 0.01011 0.00439 -0.0488 0.1940 1.0000
7.250 1.1451 0.01032 0.00459 -0.0490 0.1845 1.0000
7.500 1.1717 0.01067 0.00486 -0.0491 0.1656 1.0000
7.750 1.1926 0.01209 0.00584 -0.0490 0.0922 1.0000
8.000 1.2149 0.01317 0.00667 -0.0488 0.0499 1.0000
8.250 1.2390 0.01383 0.00724 -0.0487 0.0340 1.0000
8.500 1.2625 0.01455 0.00788 -0.0486 0.0188 1.0000
8.750 1.2870 0.01507 0.00839 -0.0484 0.0146 1.0000
9.000 1.3112 0.01559 0.00893 -0.0483 0.0122 1.0000
9.250 1.3356 0.01605 0.00942 -0.0481 0.0110 1.0000
9.500 1.3595 0.01655 0.00994 -0.0479 0.0101 1.0000
9.750 1.3826 0.01711 0.01054 -0.0477 0.0092 1.0000
10.000 1.4048 0.01775 0.01122 -0.0474 0.0084 1.0000
10.250 1.4274 0.01829 0.01181 -0.0471 0.0080 1.0000
10.500 1.4492 0.01889 0.01245 -0.0467 0.0075 1.0000
10.750 1.4700 0.01953 0.01313 -0.0463 0.0070 1.0000
11.000 1.4895 0.02027 0.01391 -0.0457 0.0065 1.0000
11.250 1.5067 0.02119 0.01489 -0.0450 0.0061 1.0000
11.500 1.5241 0.02200 0.01576 -0.0443 0.0059 1.0000
11.750 1.5397 0.02289 0.01672 -0.0435 0.0057 1.0000
12.000 1.5508 0.02391 0.01781 -0.0421 0.0055 1.0000
12.250 1.5584 0.02528 0.01926 -0.0411 0.0053 1.0000
12.500 1.5664 0.02695 0.02102 -0.0407 0.0051 1.0000
12.750 1.5741 0.02880 0.02296 -0.0407 0.0050 1.0000
13.000 1.5806 0.03087 0.02510 -0.0407 0.0048 1.0000
13.250 1.5854 0.03316 0.02747 -0.0408 0.0047 1.0000
13.500 1.5882 0.03572 0.03011 -0.0409 0.0046 1.0000
13.750 1.5882 0.03861 0.03309 -0.0411 0.0044 1.0000
14.000 1.5853 0.04187 0.03645 -0.0413 0.0043 1.0000
14.250 1.5789 0.04556 0.04024 -0.0416 0.0042 1.0000
14.500 1.5760 0.04888 0.04366 -0.0420 0.0042 1.0000
14.750 1.5720 0.05234 0.04722 -0.0423 0.0041 1.0000
15.000 1.5661 0.05612 0.05109 -0.0428 0.0041 1.0000
15.250 1.5585 0.06015 0.05523 -0.0435 0.0040 1.0000
15.500 1.5518 0.06430 0.05949 -0.0443 0.0039 1.0000
15.750 1.5431 0.06887 0.06417 -0.0454 0.0039 1.0000
16.000 1.5337 0.07364 0.06905 -0.0466 0.0038 1.0000
16.250 1.5240 0.07857 0.07408 -0.0479 0.0038 1.0000
16.500 1.5138 0.08365 0.07926 -0.0494 0.0038 1.0000
16.750 1.5029 0.08889 0.08461 -0.0509 0.0037 1.0000
17.000 1.4916 0.09431 0.09012 -0.0526 0.0037 1.0000
17.250 1.4799 0.09984 0.09575 -0.0544 0.0036 1.0000
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Polar data table (+)
Polar graphs
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