GOE 369 AIRFOIL (goe369-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 369 AIRFOIL (goe369-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.85 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe369-il-1000000.txt Download as CSV file: xf-goe369-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 369 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3529 0.09324 0.09169 -0.0102 1.0000 0.0068
-7.750 -0.3488 0.09068 0.08914 -0.0109 1.0000 0.0068
-7.500 -0.3478 0.08821 0.08670 -0.0113 1.0000 0.0068
-7.250 -0.3429 0.08531 0.08382 -0.0133 1.0000 0.0068
-7.000 -0.3345 0.08215 0.08068 -0.0160 1.0000 0.0069
-6.750 -0.3248 0.07899 0.07752 -0.0185 1.0000 0.0069
-6.500 -0.3051 0.07492 0.07345 -0.0236 0.9975 0.0069
-6.250 -0.2836 0.06977 0.06829 -0.0283 0.9797 0.0070
-6.000 -0.2299 0.06423 0.06268 -0.0408 0.9484 0.0074
-5.750 -0.1882 0.06006 0.05811 -0.0495 0.8436 0.0081
-5.500 -0.1724 0.05738 0.05519 -0.0511 0.7980 0.0087
-5.250 -0.1487 0.05433 0.05199 -0.0539 0.7740 0.0093
-5.000 -0.1230 0.05122 0.04871 -0.0568 0.7552 0.0094
-4.750 -0.0970 0.04802 0.04536 -0.0592 0.7398 0.0095
-4.500 -0.0729 0.04503 0.04225 -0.0608 0.7262 0.0095
-4.250 -0.0481 0.04206 0.03914 -0.0621 0.7142 0.0095
-4.000 -0.0252 0.03796 0.03489 -0.0635 0.7032 0.0097
-3.750 -0.0038 0.03560 0.03242 -0.0641 0.6918 0.0099
-3.500 0.0202 0.03341 0.03011 -0.0647 0.6812 0.0101
-3.250 0.0461 0.03117 0.02774 -0.0652 0.6720 0.0104
-3.000 0.0726 0.02899 0.02539 -0.0655 0.6631 0.0109
-2.750 0.1007 0.02667 0.02291 -0.0656 0.6550 0.0120
-2.500 0.1333 0.02443 0.02039 -0.0647 0.6481 0.0127
-2.250 0.1576 0.02107 0.01680 -0.0646 0.6419 0.0133
-2.000 0.1828 0.01993 0.01554 -0.0645 0.6354 0.0140
-1.750 0.2098 0.01857 0.01402 -0.0641 0.6290 0.0152
-1.500 0.2404 0.01776 0.01295 -0.0629 0.6221 0.0168
-1.250 0.2673 0.01631 0.01126 -0.0623 0.6154 0.0169
-1.000 0.2923 0.01356 0.00826 -0.0618 0.6088 0.0177
-0.750 0.3189 0.01264 0.00721 -0.0613 0.6021 0.0183
-0.500 0.3468 0.01063 0.00484 -0.0602 0.5957 0.0161
-0.250 0.3740 0.01002 0.00405 -0.0596 0.5894 0.0166
0.000 0.4007 0.00919 0.00316 -0.0592 0.5831 0.0182
0.250 0.4275 0.00885 0.00278 -0.0588 0.5763 0.0193
0.500 0.4546 0.00851 0.00239 -0.0584 0.5691 0.0208
0.750 0.4815 0.00839 0.00220 -0.0580 0.5606 0.0221
1.000 0.5076 0.00793 0.00175 -0.0576 0.5512 0.0250
1.250 0.5344 0.00779 0.00158 -0.0572 0.5393 0.0272
1.500 0.5612 0.00771 0.00145 -0.0568 0.5268 0.0291
1.750 0.5878 0.00757 0.00125 -0.0564 0.5142 0.0323
2.000 0.6146 0.00753 0.00115 -0.0561 0.5008 0.0349
2.250 0.6414 0.00754 0.00110 -0.0558 0.4837 0.0378
2.500 0.6681 0.00759 0.00108 -0.0554 0.4641 0.0414
2.750 0.6945 0.00765 0.00114 -0.0551 0.4428 0.0754
3.000 0.7384 0.00606 0.00139 -0.0595 0.4105 1.0000
3.250 0.7634 0.00631 0.00150 -0.0589 0.3809 1.0000
3.500 0.7883 0.00658 0.00162 -0.0583 0.3528 1.0000
3.750 0.8132 0.00685 0.00176 -0.0577 0.3269 1.0000
4.000 0.8384 0.00709 0.00190 -0.0572 0.3052 1.0000
4.250 0.8635 0.00734 0.00206 -0.0567 0.2842 1.0000
4.500 0.8884 0.00763 0.00223 -0.0562 0.2584 1.0000
4.750 0.9127 0.00798 0.00243 -0.0556 0.2250 1.0000
5.000 0.9364 0.00841 0.00268 -0.0549 0.1906 1.0000
5.250 0.9607 0.00877 0.00292 -0.0543 0.1706 1.0000
5.500 0.9854 0.00907 0.00317 -0.0538 0.1563 1.0000
5.750 1.0102 0.00936 0.00340 -0.0533 0.1451 1.0000
6.000 1.0354 0.00959 0.00361 -0.0529 0.1362 1.0000
6.250 1.0603 0.00985 0.00384 -0.0524 0.1263 1.0000
6.500 1.0850 0.01014 0.00411 -0.0519 0.1157 1.0000
6.750 1.1094 0.01046 0.00437 -0.0514 0.1064 1.0000
7.000 1.1342 0.01073 0.00465 -0.0509 0.1005 1.0000
7.250 1.1583 0.01107 0.00495 -0.0504 0.0943 1.0000
7.500 1.1829 0.01134 0.00527 -0.0499 0.0906 1.0000
7.750 1.2073 0.01162 0.00558 -0.0494 0.0874 1.0000
8.000 1.2309 0.01200 0.00594 -0.0488 0.0821 1.0000
8.250 1.2552 0.01227 0.00626 -0.0483 0.0779 1.0000
8.500 1.2793 0.01256 0.00656 -0.0478 0.0738 1.0000
8.750 1.3020 0.01300 0.00699 -0.0472 0.0675 1.0000
9.000 1.3265 0.01323 0.00727 -0.0467 0.0647 1.0000
9.250 1.3495 0.01361 0.00764 -0.0461 0.0591 1.0000
9.500 1.3723 0.01399 0.00804 -0.0455 0.0542 1.0000
9.750 1.3943 0.01444 0.00847 -0.0448 0.0483 1.0000
10.000 1.4163 0.01489 0.00893 -0.0441 0.0435 1.0000
10.250 1.4367 0.01547 0.00948 -0.0432 0.0369 1.0000
10.500 1.4567 0.01607 0.01009 -0.0422 0.0301 1.0000
10.750 1.4698 0.01734 0.01120 -0.0404 0.0139 1.0000
11.000 1.4851 0.01834 0.01225 -0.0388 0.0099 1.0000
11.250 1.5002 0.01932 0.01330 -0.0372 0.0083 1.0000
11.500 1.5148 0.02028 0.01436 -0.0355 0.0072 1.0000
11.750 1.5301 0.02108 0.01526 -0.0340 0.0068 1.0000
12.000 1.5431 0.02200 0.01628 -0.0322 0.0062 1.0000
12.250 1.5527 0.02303 0.01740 -0.0300 0.0058 1.0000
12.500 1.5544 0.02429 0.01878 -0.0266 0.0054 1.0000
12.750 1.5472 0.02617 0.02083 -0.0226 0.0050 1.0000
13.000 1.5518 0.02741 0.02218 -0.0204 0.0049 1.0000
13.250 1.5557 0.02884 0.02371 -0.0187 0.0048 1.0000
13.500 1.5566 0.03069 0.02569 -0.0172 0.0046 1.0000
13.750 1.5556 0.03295 0.02807 -0.0163 0.0045 1.0000
14.000 1.5561 0.03529 0.03052 -0.0158 0.0043 1.0000
14.250 1.5532 0.03817 0.03354 -0.0156 0.0042 1.0000
14.500 1.5524 0.04096 0.03644 -0.0158 0.0040 1.0000
14.750 1.5432 0.04491 0.04054 -0.0164 0.0040 1.0000
15.000 1.5430 0.04786 0.04357 -0.0169 0.0038 1.0000
15.250 1.5327 0.05225 0.04810 -0.0180 0.0038 1.0000
15.500 1.5191 0.05730 0.05329 -0.0196 0.0037 1.0000
15.750 1.5072 0.06231 0.05842 -0.0213 0.0037 1.0000
16.000 1.4919 0.06806 0.06430 -0.0236 0.0036 1.0000
16.250 1.4742 0.07459 0.07097 -0.0265 0.0036 1.0000
16.500 1.4545 0.08192 0.07845 -0.0300 0.0035 1.0000
16.750 1.4348 0.08958 0.08625 -0.0337 0.0036 1.0000
17.000 1.4145 0.09766 0.09448 -0.0377 0.0037 1.0000
17.250 1.3905 0.10671 0.10367 -0.0424 0.0037 1.0000
17.500 1.3670 0.11591 0.11301 -0.0472 0.0037 1.0000
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