GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.09 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe346-il-1000000-n5.txt Download as CSV file: xf-goe346-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4428 0.09492 0.09329 -0.0124 1.0000 0.0071
-8.500 -0.4452 0.08980 0.08819 -0.0151 1.0000 0.0076
-8.250 -0.4444 0.08580 0.08421 -0.0176 1.0000 0.0078
-8.000 -0.4341 0.08289 0.08131 -0.0205 1.0000 0.0080
-7.750 -0.4231 0.07997 0.07840 -0.0234 1.0000 0.0081
-7.500 -0.4043 0.07637 0.07479 -0.0285 0.9953 0.0084
-7.250 -0.3811 0.07228 0.07068 -0.0348 0.9869 0.0089
-7.000 -0.3554 0.06316 0.06146 -0.0470 0.9742 0.0103
-6.750 -0.3303 0.06025 0.05851 -0.0512 0.9641 0.0105
-6.500 -0.3063 0.05746 0.05567 -0.0547 0.9526 0.0108
-6.250 -0.2829 0.05459 0.05271 -0.0578 0.9405 0.0112
-6.000 -0.2592 0.05137 0.04939 -0.0608 0.9288 0.0118
-5.750 -0.2304 0.04366 0.04143 -0.0673 0.9177 0.0136
-5.500 -0.2062 0.04184 0.03952 -0.0686 0.9079 0.0138
-5.250 -0.1813 0.03998 0.03756 -0.0698 0.8988 0.0141
-5.000 -0.1559 0.03803 0.03549 -0.0710 0.8900 0.0146
-4.750 -0.1289 0.03545 0.03278 -0.0725 0.8815 0.0154
-4.500 -0.0960 0.02834 0.02523 -0.0752 0.8749 0.0174
-4.250 -0.0700 0.02723 0.02403 -0.0757 0.8679 0.0177
-4.000 -0.0441 0.02625 0.02297 -0.0760 0.8611 0.0180
-3.750 -0.0173 0.02486 0.02147 -0.0764 0.8538 0.0183
-3.500 0.0100 0.02321 0.01966 -0.0768 0.8466 0.0187
-3.250 0.0380 0.02136 0.01764 -0.0771 0.8386 0.0191
-3.000 0.0662 0.01940 0.01545 -0.0773 0.8309 0.0196
-2.750 0.0951 0.01713 0.01291 -0.0773 0.8222 0.0207
-2.500 0.1237 0.01522 0.01073 -0.0772 0.8127 0.0215
-2.250 0.1514 0.01408 0.00938 -0.0771 0.7999 0.0218
-2.000 0.1790 0.01315 0.00825 -0.0770 0.7834 0.0220
-1.750 0.2063 0.01234 0.00723 -0.0769 0.7626 0.0221
-1.500 0.2336 0.01102 0.00559 -0.0768 0.7405 0.0225
-1.250 0.2609 0.01022 0.00458 -0.0767 0.7177 0.0226
-1.000 0.2882 0.00956 0.00374 -0.0766 0.6960 0.0229
-0.750 0.3155 0.00925 0.00331 -0.0765 0.6712 0.0233
-0.500 0.3429 0.00905 0.00301 -0.0764 0.6470 0.0236
-0.250 0.3705 0.00892 0.00281 -0.0763 0.6270 0.0241
0.000 0.3981 0.00881 0.00261 -0.0763 0.6042 0.0246
0.250 0.4254 0.00872 0.00242 -0.0762 0.5780 0.0252
0.500 0.4527 0.00865 0.00225 -0.0761 0.5525 0.0257
0.750 0.4801 0.00859 0.00210 -0.0760 0.5285 0.0261
1.000 0.5070 0.00861 0.00198 -0.0759 0.4934 0.0264
1.250 0.5332 0.00879 0.00191 -0.0758 0.4322 0.0267
1.500 0.5591 0.00906 0.00189 -0.0756 0.3624 0.0270
1.750 0.5858 0.00922 0.00190 -0.0755 0.3234 0.0276
2.000 0.6128 0.00932 0.00189 -0.0754 0.2961 0.0280
2.250 0.6399 0.00942 0.00188 -0.0753 0.2695 0.0282
2.500 0.6666 0.00960 0.00191 -0.0752 0.2365 0.0285
2.750 0.6932 0.00979 0.00197 -0.0751 0.2054 0.0289
3.000 0.7202 0.00994 0.00205 -0.0750 0.1873 0.0294
3.250 0.7473 0.01005 0.00210 -0.0749 0.1722 0.0313
3.500 0.7743 0.01020 0.00219 -0.0748 0.1583 0.0338
3.750 0.8012 0.01035 0.00231 -0.0747 0.1463 0.0361
4.000 0.8279 0.01054 0.00246 -0.0746 0.1311 0.0390
4.250 0.8531 0.01096 0.00271 -0.0743 0.0908 0.0577
5.000 0.9262 0.01036 0.00369 -0.0731 0.0350 1.0000
5.250 0.9525 0.01062 0.00393 -0.0729 0.0324 1.0000
5.500 0.9787 0.01089 0.00419 -0.0727 0.0300 1.0000
5.750 1.0048 0.01117 0.00449 -0.0724 0.0280 1.0000
6.000 1.0311 0.01139 0.00473 -0.0722 0.0275 1.0000
6.250 1.0572 0.01163 0.00499 -0.0720 0.0267 1.0000
6.500 1.0831 0.01189 0.00527 -0.0718 0.0254 1.0000
6.750 1.1088 0.01218 0.00559 -0.0715 0.0240 1.0000
7.000 1.1341 0.01250 0.00591 -0.0712 0.0224 1.0000
7.250 1.1588 0.01291 0.00634 -0.0708 0.0202 1.0000
7.500 1.1843 0.01318 0.00663 -0.0705 0.0195 1.0000
7.750 1.2096 0.01346 0.00695 -0.0702 0.0183 1.0000
8.000 1.2345 0.01378 0.00726 -0.0699 0.0163 1.0000
8.250 1.2588 0.01417 0.00763 -0.0695 0.0140 1.0000
8.500 1.2831 0.01455 0.00803 -0.0690 0.0127 1.0000
8.750 1.3070 0.01497 0.00845 -0.0685 0.0113 1.0000
9.000 1.3303 0.01545 0.00896 -0.0680 0.0100 1.0000
9.250 1.3537 0.01590 0.00946 -0.0674 0.0094 1.0000
9.500 1.3766 0.01638 0.00998 -0.0668 0.0086 1.0000
9.750 1.3988 0.01693 0.01055 -0.0661 0.0078 1.0000
10.000 1.4204 0.01753 0.01120 -0.0653 0.0071 1.0000
10.250 1.4422 0.01807 0.01182 -0.0646 0.0068 1.0000
10.500 1.4634 0.01864 0.01246 -0.0638 0.0064 1.0000
10.750 1.4840 0.01926 0.01313 -0.0629 0.0061 1.0000
11.000 1.5039 0.01991 0.01385 -0.0619 0.0058 1.0000
11.250 1.5228 0.02064 0.01463 -0.0608 0.0054 1.0000
11.500 1.5396 0.02154 0.01562 -0.0594 0.0051 1.0000
11.750 1.5565 0.02235 0.01653 -0.0580 0.0049 1.0000
12.000 1.5732 0.02313 0.01739 -0.0567 0.0048 1.0000
12.250 1.5887 0.02394 0.01830 -0.0551 0.0046 1.0000
12.500 1.6026 0.02480 0.01925 -0.0534 0.0044 1.0000
12.750 1.6139 0.02567 0.02020 -0.0512 0.0043 1.0000
13.000 1.6225 0.02662 0.02124 -0.0487 0.0041 1.0000
13.250 1.6305 0.02765 0.02236 -0.0463 0.0040 1.0000
13.500 1.6370 0.02885 0.02367 -0.0440 0.0039 1.0000
13.750 1.6424 0.03021 0.02512 -0.0418 0.0038 1.0000
14.000 1.6463 0.03176 0.02679 -0.0397 0.0037 1.0000
14.250 1.6482 0.03358 0.02872 -0.0377 0.0036 1.0000
14.500 1.6478 0.03573 0.03099 -0.0359 0.0035 1.0000
14.750 1.6438 0.03837 0.03377 -0.0344 0.0034 1.0000
15.000 1.6388 0.04130 0.03685 -0.0333 0.0033 1.0000
15.250 1.6361 0.04421 0.03988 -0.0327 0.0033 1.0000
15.500 1.6314 0.04753 0.04334 -0.0325 0.0033 1.0000
15.750 1.6249 0.05129 0.04725 -0.0328 0.0032 1.0000
16.000 1.6158 0.05565 0.05176 -0.0336 0.0032 1.0000
16.250 1.6043 0.06062 0.05688 -0.0350 0.0032 1.0000
16.500 1.5900 0.06640 0.06281 -0.0371 0.0032 1.0000
16.750 1.5728 0.07301 0.06958 -0.0398 0.0032 1.0000
17.000 1.5515 0.08067 0.07741 -0.0433 0.0032 1.0000
17.250 1.5269 0.08932 0.08621 -0.0475 0.0032 1.0000
17.500 1.4974 0.09916 0.09622 -0.0523 0.0032 1.0000
17.750 1.4680 0.10915 0.10636 -0.0571 0.0032 1.0000
18.000 1.4364 0.11971 0.11706 -0.0623 0.0032 1.0000
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Polar data table (+)
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