GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Reynolds number: 500,000 Max Cl/Cd: 82.97 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe346-il-500000-n5.txt Download as CSV file: xf-goe346-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4290 0.09856 0.09624 -0.0118 1.0000 0.0099
-8.500 -0.4270 0.09430 0.09201 -0.0140 1.0000 0.0102
-8.250 -0.4243 0.09063 0.08836 -0.0160 1.0000 0.0104
-8.000 -0.4182 0.08822 0.08598 -0.0171 1.0000 0.0105
-7.750 -0.4105 0.08561 0.08339 -0.0190 1.0000 0.0108
-7.500 -0.4008 0.08293 0.08073 -0.0213 1.0000 0.0112
-7.250 -0.3921 0.07994 0.07775 -0.0238 1.0000 0.0117
-7.000 -0.3840 0.07650 0.07432 -0.0265 0.9994 0.0123
-6.750 -0.3575 0.07071 0.06849 -0.0351 0.9938 0.0128
-6.500 -0.3271 0.06368 0.06137 -0.0453 0.9867 0.0136
-6.250 -0.3015 0.06122 0.05887 -0.0489 0.9810 0.0139
-6.000 -0.2729 0.05826 0.05586 -0.0535 0.9758 0.0148
-5.750 -0.2430 0.05402 0.05153 -0.0589 0.9684 0.0158
-5.500 -0.2022 0.04603 0.04325 -0.0681 0.9608 0.0173
-5.250 -0.1787 0.04470 0.04191 -0.0693 0.9536 0.0178
-5.000 -0.1530 0.04303 0.04018 -0.0709 0.9458 0.0186
-4.750 -0.1248 0.04026 0.03727 -0.0731 0.9366 0.0195
-4.500 -0.0966 0.03706 0.03388 -0.0750 0.9260 0.0201
-4.250 -0.0599 0.03239 0.02880 -0.0770 0.9168 0.0224
-4.000 -0.0381 0.03070 0.02704 -0.0776 0.9075 0.0231
-3.750 -0.0136 0.02941 0.02567 -0.0780 0.8998 0.0238
-3.500 0.0133 0.02746 0.02354 -0.0785 0.8926 0.0243
-3.250 0.0410 0.02548 0.02138 -0.0789 0.8854 0.0246
-3.000 0.0689 0.02352 0.01921 -0.0792 0.8782 0.0248
-2.750 0.0966 0.02207 0.01759 -0.0793 0.8709 0.0259
-2.500 0.1249 0.02023 0.01552 -0.0794 0.8634 0.0260
-2.250 0.1534 0.01853 0.01359 -0.0794 0.8557 0.0261
-2.000 0.1816 0.01710 0.01193 -0.0793 0.8481 0.0265
-1.750 0.2098 0.01585 0.01048 -0.0792 0.8394 0.0267
-1.500 0.2376 0.01478 0.00922 -0.0790 0.8289 0.0270
-1.250 0.2652 0.01400 0.00825 -0.0787 0.8154 0.0277
-1.000 0.2926 0.01310 0.00715 -0.0784 0.7979 0.0276
-0.750 0.3196 0.01231 0.00614 -0.0780 0.7763 0.0275
-0.500 0.3466 0.01168 0.00530 -0.0776 0.7525 0.0276
-0.250 0.3735 0.01120 0.00462 -0.0772 0.7297 0.0280
0.000 0.4007 0.01083 0.00411 -0.0769 0.7096 0.0285
0.250 0.4280 0.01057 0.00375 -0.0767 0.6916 0.0289
0.500 0.4552 0.01039 0.00349 -0.0765 0.6738 0.0293
0.750 0.4825 0.01020 0.00323 -0.0764 0.6559 0.0296
1.000 0.5095 0.00974 0.00269 -0.0762 0.6358 0.0302
1.250 0.5364 0.00950 0.00239 -0.0760 0.6114 0.0315
1.500 0.5632 0.00944 0.00225 -0.0758 0.5833 0.0322
1.750 0.5893 0.00951 0.00214 -0.0755 0.5409 0.0324
2.000 0.6149 0.00968 0.00209 -0.0752 0.4919 0.0326
2.250 0.6408 0.00988 0.00208 -0.0749 0.4405 0.0331
2.500 0.6665 0.01013 0.00212 -0.0747 0.3865 0.0339
2.750 0.6922 0.01043 0.00221 -0.0744 0.3371 0.0351
3.000 0.7182 0.01069 0.00231 -0.0742 0.3014 0.0369
3.250 0.7441 0.01098 0.00245 -0.0740 0.2658 0.0388
3.500 0.7701 0.01126 0.00259 -0.0738 0.2344 0.0404
3.750 0.7964 0.01149 0.00273 -0.0736 0.2111 0.0475
4.000 0.8183 0.00997 0.00304 -0.0729 0.1939 1.0000
4.500 0.8707 0.01052 0.00342 -0.0724 0.1638 1.0000
4.750 0.8968 0.01081 0.00364 -0.0722 0.1482 1.0000
5.000 0.9226 0.01112 0.00389 -0.0719 0.1304 1.0000
5.250 0.9470 0.01165 0.00421 -0.0715 0.0938 1.0000
5.750 0.9947 0.01287 0.00511 -0.0705 0.0389 1.0000
6.000 1.0201 0.01321 0.00549 -0.0702 0.0359 1.0000
6.250 1.0452 0.01359 0.00590 -0.0698 0.0335 1.0000
6.500 1.0699 0.01403 0.00637 -0.0693 0.0312 1.0000
6.750 1.0939 0.01455 0.00695 -0.0688 0.0286 1.0000
7.000 1.1185 0.01496 0.00741 -0.0683 0.0275 1.0000
7.250 1.1432 0.01532 0.00782 -0.0679 0.0261 1.0000
7.500 1.1675 0.01574 0.00830 -0.0675 0.0244 1.0000
7.750 1.1912 0.01620 0.00882 -0.0669 0.0225 1.0000
8.000 1.2132 0.01692 0.00957 -0.0662 0.0201 1.0000
8.250 1.2373 0.01728 0.00999 -0.0657 0.0190 1.0000
8.500 1.2606 0.01774 0.01051 -0.0651 0.0174 1.0000
8.750 1.2836 0.01822 0.01101 -0.0645 0.0158 1.0000
9.000 1.3050 0.01888 0.01170 -0.0637 0.0141 1.0000
9.250 1.3270 0.01943 0.01234 -0.0630 0.0131 1.0000
9.500 1.3484 0.02003 0.01299 -0.0622 0.0120 1.0000
9.750 1.3689 0.02069 0.01370 -0.0613 0.0111 1.0000
10.000 1.3869 0.02163 0.01470 -0.0600 0.0102 1.0000
10.250 1.4052 0.02247 0.01567 -0.0588 0.0098 1.0000
10.500 1.4230 0.02331 0.01662 -0.0575 0.0092 1.0000
10.750 1.4402 0.02415 0.01756 -0.0562 0.0087 1.0000
11.000 1.4568 0.02499 0.01848 -0.0548 0.0082 1.0000
11.250 1.4715 0.02594 0.01951 -0.0533 0.0077 1.0000
11.500 1.4812 0.02725 0.02093 -0.0510 0.0073 1.0000
11.750 1.4883 0.02848 0.02229 -0.0483 0.0071 1.0000
12.000 1.4951 0.02971 0.02368 -0.0457 0.0069 1.0000
12.250 1.5004 0.03110 0.02522 -0.0432 0.0067 1.0000
12.500 1.5046 0.03265 0.02692 -0.0409 0.0065 1.0000
12.750 1.5076 0.03438 0.02880 -0.0387 0.0063 1.0000
13.000 1.5096 0.03630 0.03086 -0.0368 0.0062 1.0000
13.250 1.5106 0.03842 0.03313 -0.0352 0.0060 1.0000
13.500 1.5103 0.04079 0.03565 -0.0338 0.0059 1.0000
13.750 1.5092 0.04338 0.03838 -0.0329 0.0058 1.0000
14.000 1.5060 0.04639 0.04155 -0.0323 0.0057 1.0000
14.250 1.5018 0.04970 0.04501 -0.0321 0.0056 1.0000
14.500 1.4961 0.05342 0.04888 -0.0324 0.0055 1.0000
14.750 1.4881 0.05771 0.05332 -0.0333 0.0054 1.0000
15.000 1.4781 0.06255 0.05832 -0.0347 0.0053 1.0000
15.250 1.4652 0.06817 0.06410 -0.0368 0.0053 1.0000
15.500 1.4504 0.07444 0.07054 -0.0395 0.0053 1.0000
15.750 1.4335 0.08140 0.07766 -0.0427 0.0052 1.0000
16.000 1.4151 0.08899 0.08542 -0.0464 0.0052 1.0000
16.250 1.3955 0.09702 0.09360 -0.0504 0.0052 1.0000
16.500 1.3752 0.10544 0.10218 -0.0546 0.0052 1.0000
16.750 1.3541 0.11417 0.11106 -0.0590 0.0053 1.0000
17.000 1.3327 0.12306 0.12009 -0.0635 0.0053 1.0000
17.250 1.3115 0.13219 0.12937 -0.0683 0.0053 1.0000
17.500 1.2900 0.14168 0.13899 -0.0734 0.0053 1.0000
17.750 1.2691 0.15135 0.14880 -0.0788 0.0054 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)