GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 54 AIRFOIL (goe54-il) Reynolds number: 50,000 Max Cl/Cd: 29.29 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe54-il-50000-n5.txt Download as CSV file: xf-goe54-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 54 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5473 0.12435 0.11754 0.0378 1.0000 0.0611
-9.000 -0.5456 0.12192 0.11517 0.0346 1.0000 0.0630
-8.750 -0.5470 0.12011 0.11344 0.0299 1.0000 0.0637
-8.500 -0.5311 0.11423 0.10758 0.0329 1.0000 0.0665
-8.250 -0.5248 0.11096 0.10436 0.0314 1.0000 0.0692
-8.000 -0.5216 0.10825 0.10171 0.0281 1.0000 0.0715
-7.750 -0.5167 0.10595 0.09946 0.0199 1.0000 0.0728
-7.500 -0.5062 0.10090 0.09449 0.0226 1.0000 0.0747
-7.250 -0.4955 0.09714 0.09074 0.0220 1.0000 0.0778
-7.000 -0.4838 0.09377 0.08739 0.0170 1.0000 0.0820
-6.750 -0.4688 0.09016 0.08377 0.0088 1.0000 0.0849
-6.500 -0.4587 0.08607 0.07977 0.0120 1.0000 0.0896
-6.000 -0.4272 0.07858 0.07230 0.0048 1.0000 0.1011
-5.750 -0.4013 0.07547 0.06900 -0.0045 1.0000 0.1102
-5.500 -0.3907 0.07124 0.06492 -0.0014 1.0000 0.1149
-5.000 -0.3463 0.06434 0.05788 -0.0095 1.0000 0.1395
-4.750 -0.3281 0.06094 0.05452 -0.0104 1.0000 0.1558
-4.500 -0.3116 0.05781 0.05148 -0.0102 1.0000 0.1766
-4.250 -0.2943 0.05489 0.04862 -0.0106 1.0000 0.2096
-3.750 -0.2694 0.04955 0.04363 -0.0067 1.0000 0.3062
-3.500 -0.2557 0.04732 0.04154 -0.0046 1.0000 0.3641
-3.250 -0.2456 0.04474 0.03919 0.0000 1.0000 0.4125
-3.000 -0.2336 0.04216 0.03683 0.0041 1.0000 0.4561
-2.750 -0.2056 0.03943 0.03417 0.0021 1.0000 0.4787
-2.250 -0.0057 0.03330 0.02480 -0.0340 0.7557 0.1340
-2.000 0.0255 0.03238 0.02294 -0.0327 0.6850 0.1115
-1.750 0.0535 0.03115 0.02121 -0.0319 0.6394 0.1013
-1.500 0.0836 0.03045 0.01991 -0.0313 0.6052 0.0949
-1.250 0.1120 0.02933 0.01843 -0.0310 0.5779 0.0932
-1.000 0.1407 0.02840 0.01711 -0.0306 0.5556 0.0903
-0.750 0.1708 0.02782 0.01607 -0.0301 0.5353 0.0858
-0.500 0.1999 0.02730 0.01521 -0.0296 0.5167 0.0831
-0.250 0.2282 0.02655 0.01425 -0.0292 0.4993 0.0815
0.000 0.2564 0.02599 0.01347 -0.0287 0.4830 0.0800
0.250 0.2844 0.02554 0.01284 -0.0280 0.4680 0.0794
0.500 0.3126 0.02523 0.01232 -0.0274 0.4542 0.0806
0.750 0.3407 0.02498 0.01188 -0.0269 0.4409 0.0818
1.000 0.3689 0.02473 0.01155 -0.0264 0.4271 0.0819
1.250 0.3967 0.02455 0.01129 -0.0259 0.4145 0.0818
1.500 0.4243 0.02448 0.01110 -0.0255 0.4038 0.0819
1.750 0.4521 0.02448 0.01102 -0.0252 0.3935 0.0824
2.000 0.4802 0.02458 0.01107 -0.0250 0.3833 0.0835
2.250 0.5080 0.02462 0.01099 -0.0248 0.3749 0.0871
2.500 0.5367 0.02481 0.01122 -0.0249 0.3646 0.0918
2.750 0.5646 0.02507 0.01136 -0.0247 0.3572 0.0952
3.000 0.5930 0.02538 0.01173 -0.0247 0.3483 0.0992
3.250 0.6209 0.02568 0.01198 -0.0246 0.3407 0.1066
3.500 0.6459 0.02470 0.01252 -0.0244 0.3324 0.6201
4.000 0.6983 0.02524 0.01328 -0.0231 0.3165 1.0000
4.250 0.7251 0.02581 0.01374 -0.0228 0.3091 1.0000
4.500 0.7519 0.02644 0.01435 -0.0226 0.3012 1.0000
4.750 0.7783 0.02704 0.01486 -0.0223 0.2945 1.0000
5.000 0.8047 0.02785 0.01573 -0.0223 0.2868 1.0000
5.250 0.8308 0.02836 0.01609 -0.0218 0.2815 1.0000
5.500 0.8567 0.02948 0.01745 -0.0221 0.2735 1.0000
5.750 0.8824 0.03025 0.01820 -0.0218 0.2679 1.0000
6.000 0.9078 0.03123 0.01922 -0.0216 0.2631 1.0000
6.250 0.9324 0.03275 0.02105 -0.0219 0.2567 1.0000
6.500 0.9572 0.03373 0.02209 -0.0217 0.2517 1.0000
6.750 0.9819 0.03469 0.02305 -0.0214 0.2473 1.0000
7.000 1.0039 0.03676 0.02554 -0.0219 0.2402 1.0000
7.250 1.0274 0.03797 0.02689 -0.0217 0.2354 1.0000
7.500 1.0516 0.03894 0.02787 -0.0213 0.2321 1.0000
7.750 1.0687 0.04227 0.03174 -0.0224 0.2267 1.0000
8.000 1.0862 0.04505 0.03487 -0.0230 0.2220 1.0000
8.250 1.1068 0.04663 0.03662 -0.0228 0.2180 1.0000
8.500 1.1306 0.04735 0.03732 -0.0219 0.2147 1.0000
8.750 1.1254 0.05474 0.04549 -0.0256 0.2078 1.0000
9.000 1.1389 0.05719 0.04813 -0.0259 0.2028 1.0000
9.250 1.1695 0.05563 0.04651 -0.0234 0.1979 1.0000
9.500 1.1248 0.06879 0.06026 -0.0319 0.1895 1.0000
9.750 1.1960 0.05884 0.05010 -0.0233 0.1836 1.0000
10.000 1.0607 0.08997 0.08154 -0.0477 0.1774 1.0000
10.250 1.0669 0.09238 0.08401 -0.0480 0.1718 1.0000
10.500 1.0559 0.09833 0.08996 -0.0511 0.1666 1.0000
10.750 1.0353 0.10623 0.09787 -0.0557 0.1605 1.0000
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Polar data table (+)
Polar graphs
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