GOE 548 AIRFOIL (goe548-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 548 AIRFOIL (goe548-il) Reynolds number: 100,000 Max Cl/Cd: 53.71 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe548-il-100000.txt Download as CSV file: xf-goe548-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 548 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4542 0.09478 0.09014 -0.0366 1.0000 0.1519
-8.750 -0.4878 0.09219 0.08769 -0.0374 1.0000 0.1571
-8.500 -0.5261 0.08947 0.08513 -0.0375 1.0000 0.1578
-8.250 -0.4913 0.08653 0.08213 -0.0330 1.0000 0.1657
-8.000 -0.5216 0.08416 0.07989 -0.0317 1.0000 0.1695
-7.750 -0.5778 0.08117 0.07699 -0.0318 1.0000 0.1717
-7.000 -0.6710 0.05103 0.04517 -0.0317 1.0000 0.0748
-6.750 -0.6653 0.04693 0.04096 -0.0298 1.0000 0.0730
-6.500 -0.6609 0.04338 0.03704 -0.0273 1.0000 0.0721
-6.250 -0.6532 0.04004 0.03329 -0.0250 1.0000 0.0710
-6.000 -0.6428 0.03675 0.02950 -0.0226 1.0000 0.0695
-5.750 -0.6294 0.03395 0.02619 -0.0203 1.0000 0.0691
-5.500 -0.6141 0.03191 0.02370 -0.0183 1.0000 0.0712
-5.250 -0.5977 0.03045 0.02176 -0.0163 1.0000 0.0744
-5.000 -0.5795 0.02831 0.01933 -0.0146 1.0000 0.0774
-4.750 -0.5611 0.02693 0.01789 -0.0133 1.0000 0.0818
-4.500 -0.5425 0.02618 0.01682 -0.0116 1.0000 0.0885
-4.250 -0.5237 0.02472 0.01549 -0.0104 1.0000 0.0953
-4.000 -0.5049 0.02394 0.01455 -0.0090 1.0000 0.1037
-3.750 -0.4869 0.02309 0.01378 -0.0076 1.0000 0.1129
-3.500 -0.4556 0.02248 0.01322 -0.0087 0.9959 0.1284
-3.250 -0.4220 0.02184 0.01276 -0.0102 0.9898 0.1510
-3.000 -0.3927 0.02052 0.01248 -0.0112 0.9844 0.2986
-2.750 -0.3703 0.01980 0.01269 -0.0104 0.9774 0.5054
-2.500 -0.3370 0.01992 0.01316 -0.0113 0.9715 0.6162
-2.250 -0.3117 0.01980 0.01330 -0.0105 0.9640 0.7015
-2.000 -0.2725 0.02003 0.01375 -0.0118 0.9589 0.7997
-1.750 -0.1956 0.02056 0.01440 -0.0203 0.9564 0.9220
-1.500 -0.0919 0.02153 0.01506 -0.0350 0.9563 0.9770
-1.250 -0.0253 0.02187 0.01512 -0.0440 0.9523 1.0000
-1.000 0.0091 0.02190 0.01496 -0.0468 0.9448 1.0000
-0.750 0.0285 0.02186 0.01477 -0.0465 0.9342 1.0000
-0.500 0.0560 0.02199 0.01475 -0.0474 0.9255 1.0000
-0.250 0.0937 0.02216 0.01477 -0.0499 0.9182 1.0000
0.000 0.1167 0.02233 0.01484 -0.0497 0.9083 1.0000
0.250 0.1616 0.02249 0.01490 -0.0534 0.9026 1.0000
0.500 0.1818 0.02267 0.01500 -0.0525 0.8917 1.0000
0.750 0.2114 0.02286 0.01512 -0.0532 0.8829 1.0000
1.000 0.2489 0.02296 0.01517 -0.0553 0.8756 1.0000
1.250 0.2716 0.02316 0.01535 -0.0547 0.8650 1.0000
1.500 0.3180 0.02312 0.01530 -0.0583 0.8598 1.0000
1.750 0.3376 0.02333 0.01549 -0.0570 0.8483 1.0000
2.000 0.3648 0.02346 0.01563 -0.0570 0.8386 1.0000
2.250 0.4067 0.02334 0.01554 -0.0596 0.8324 1.0000
2.500 0.4287 0.02351 0.01573 -0.0586 0.8214 1.0000
2.750 0.4791 0.02314 0.01545 -0.0625 0.8173 1.0000
3.000 0.5007 0.02325 0.01559 -0.0613 0.8056 1.0000
3.250 0.5353 0.02291 0.01532 -0.0620 0.7952 1.0000
3.500 0.6109 0.02119 0.01378 -0.0689 0.7897 1.0000
3.750 0.6503 0.02034 0.01304 -0.0698 0.7772 1.0000
4.000 0.6924 0.01944 0.01226 -0.0712 0.7646 1.0000
4.250 0.7354 0.01860 0.01153 -0.0727 0.7509 1.0000
4.500 0.7764 0.01793 0.01096 -0.0740 0.7357 1.0000
4.750 0.8109 0.01763 0.01078 -0.0745 0.7203 1.0000
5.000 0.8444 0.01731 0.01053 -0.0746 0.7008 1.0000
5.250 0.8681 0.01701 0.01023 -0.0725 0.6724 1.0000
5.500 0.8778 0.01688 0.01011 -0.0680 0.6389 1.0000
5.750 0.8894 0.01680 0.01005 -0.0640 0.6044 1.0000
6.000 0.9025 0.01682 0.01004 -0.0605 0.5684 1.0000
6.250 0.9125 0.01699 0.01003 -0.0563 0.5193 1.0000
6.500 0.9213 0.01741 0.01023 -0.0522 0.4683 1.0000
6.750 0.9237 0.01805 0.01057 -0.0472 0.3999 1.0000
7.000 0.9218 0.01897 0.01103 -0.0417 0.3152 1.0000
7.250 0.9189 0.02011 0.01171 -0.0363 0.2485 1.0000
7.500 0.9163 0.02144 0.01261 -0.0313 0.1904 1.0000
7.750 0.9160 0.02286 0.01368 -0.0269 0.1269 1.0000
8.000 0.9139 0.02452 0.01490 -0.0223 0.0837 1.0000
8.250 0.9169 0.02595 0.01624 -0.0185 0.0669 1.0000
8.500 0.9226 0.02725 0.01753 -0.0152 0.0595 1.0000
8.750 0.9307 0.02846 0.01880 -0.0124 0.0549 1.0000
9.000 0.9371 0.02987 0.02021 -0.0095 0.0520 1.0000
9.250 0.9474 0.03137 0.02178 -0.0071 0.0500 1.0000
9.500 0.9634 0.03286 0.02336 -0.0054 0.0480 1.0000
9.750 0.9814 0.03432 0.02490 -0.0041 0.0455 1.0000
10.000 1.0031 0.03606 0.02663 -0.0034 0.0433 1.0000
10.250 1.0560 0.03992 0.03056 -0.0068 0.0418 1.0000
10.500 1.0956 0.04372 0.03469 -0.0089 0.0418 1.0000
10.750 1.1135 0.04659 0.03790 -0.0076 0.0421 1.0000
11.000 1.1192 0.04905 0.04077 -0.0045 0.0427 1.0000
11.250 1.1167 0.05205 0.04431 -0.0005 0.0439 1.0000
11.500 1.0998 0.05563 0.04842 0.0045 0.0452 1.0000
11.750 1.0824 0.05936 0.05254 0.0086 0.0462 1.0000
12.000 1.0647 0.06304 0.05654 0.0119 0.0471 1.0000
12.250 1.0447 0.06690 0.06067 0.0146 0.0477 1.0000
12.500 1.0245 0.07091 0.06490 0.0164 0.0482 1.0000
12.750 1.0035 0.07543 0.06960 0.0173 0.0490 1.0000
13.000 0.9816 0.08015 0.07450 0.0174 0.0494 1.0000
13.250 0.9644 0.08535 0.07982 0.0168 0.0503 1.0000
13.500 0.9550 0.09093 0.08544 0.0160 0.0512 1.0000
13.750 0.7781 0.09514 0.09033 0.0131 0.0493 1.0000
14.000 0.7400 0.10329 0.09860 0.0080 0.0498 1.0000
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Polar data table (+)
Polar graphs
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