GOE 113 AIRFOIL (goe113-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 113 AIRFOIL (goe113-il) Reynolds number: 200,000 Max Cl/Cd: 69.96 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe113-il-200000.txt Download as CSV file: xf-goe113-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 113 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4520 0.09753 0.09408 -0.0063 1.0000 0.0248
-7.750 -0.4481 0.09471 0.09131 -0.0096 1.0000 0.0259
-7.500 -0.4437 0.09194 0.08859 -0.0150 1.0000 0.0265
-7.250 -0.4317 0.08837 0.08502 -0.0218 1.0000 0.0268
-7.000 -0.4187 0.08444 0.08107 -0.0270 1.0000 0.0269
-6.750 -0.4055 0.08043 0.07701 -0.0305 1.0000 0.0270
-6.500 -0.3920 0.07641 0.07293 -0.0334 1.0000 0.0270
-6.250 -0.3782 0.07245 0.06889 -0.0356 1.0000 0.0271
-6.000 -0.3756 0.06549 0.06198 -0.0365 1.0000 0.0277
-5.750 -0.3680 0.06147 0.05798 -0.0361 1.0000 0.0284
-5.500 -0.3566 0.05801 0.05451 -0.0362 1.0000 0.0291
-5.250 -0.3422 0.05460 0.05104 -0.0370 1.0000 0.0300
-5.000 -0.3254 0.05115 0.04751 -0.0380 1.0000 0.0311
-4.750 -0.3066 0.04769 0.04392 -0.0391 1.0000 0.0325
-4.500 -0.2857 0.04426 0.04029 -0.0400 1.0000 0.0344
-4.250 -0.2542 0.04238 0.03794 -0.0405 1.0000 0.0381
-4.000 -0.2344 0.03766 0.03287 -0.0410 1.0000 0.0394
-3.750 -0.2196 0.03417 0.02950 -0.0409 1.0000 0.0418
-3.500 -0.1923 0.03523 0.02997 -0.0395 1.0000 0.0515
-3.250 -0.1773 0.02956 0.02448 -0.0404 1.0000 0.0555
-3.000 -0.1536 0.02802 0.02252 -0.0398 1.0000 0.0665
-2.750 -0.1346 0.02597 0.02053 -0.0394 1.0000 0.0735
-2.500 -0.1128 0.02480 0.01898 -0.0390 1.0000 0.0939
-2.250 -0.0764 0.02244 0.01664 -0.0423 0.9964 0.1240
-2.000 -0.0379 0.02057 0.01486 -0.0462 0.9911 0.1820
-1.750 0.0206 0.01744 0.01032 -0.0457 0.9869 0.0633
-1.500 0.0658 0.01592 0.00855 -0.0488 0.9820 0.0637
-1.250 0.1075 0.01437 0.00686 -0.0513 0.9738 0.0619
-1.000 0.1515 0.01332 0.00577 -0.0543 0.9663 0.0623
-0.750 0.1952 0.01253 0.00498 -0.0574 0.9565 0.0657
-0.500 0.2346 0.01172 0.00422 -0.0595 0.9411 0.0661
-0.250 0.2705 0.01111 0.00358 -0.0608 0.9191 0.0685
0.000 0.3046 0.01072 0.00312 -0.0616 0.8943 0.0739
0.250 0.3354 0.01042 0.00277 -0.0617 0.8663 0.0885
0.500 0.3616 0.00793 0.00264 -0.0607 0.8388 1.0000
0.750 0.3876 0.00806 0.00249 -0.0598 0.8083 1.0000
1.000 0.4131 0.00823 0.00241 -0.0589 0.7803 1.0000
1.250 0.4387 0.00842 0.00240 -0.0582 0.7547 1.0000
1.500 0.4643 0.00861 0.00241 -0.0575 0.7300 1.0000
1.750 0.4901 0.00881 0.00244 -0.0568 0.7073 1.0000
2.000 0.5162 0.00899 0.00251 -0.0564 0.6858 1.0000
2.250 0.5422 0.00919 0.00258 -0.0559 0.6664 1.0000
2.500 0.5686 0.00935 0.00268 -0.0555 0.6475 1.0000
2.750 0.5951 0.00953 0.00280 -0.0551 0.6299 1.0000
3.000 0.6215 0.00972 0.00296 -0.0548 0.6129 1.0000
3.250 0.6479 0.00990 0.00311 -0.0544 0.5952 1.0000
3.500 0.6743 0.01008 0.00327 -0.0541 0.5762 1.0000
3.750 0.7003 0.01028 0.00344 -0.0537 0.5564 1.0000
4.000 0.7255 0.01047 0.00357 -0.0531 0.5216 1.0000
4.250 0.7498 0.01075 0.00373 -0.0523 0.4729 1.0000
4.500 0.7745 0.01107 0.00393 -0.0517 0.4206 1.0000
4.750 0.7959 0.01182 0.00418 -0.0508 0.3180 1.0000
5.000 0.8174 0.01275 0.00466 -0.0502 0.2459 1.0000
5.250 0.8414 0.01337 0.00513 -0.0497 0.2113 1.0000
5.500 0.8658 0.01396 0.00565 -0.0493 0.1695 1.0000
5.750 0.8850 0.01544 0.00641 -0.0483 0.0538 1.0000
6.000 0.9071 0.01658 0.00751 -0.0473 0.0317 1.0000
6.250 0.9306 0.01745 0.00851 -0.0464 0.0279 1.0000
6.500 0.9526 0.01855 0.00983 -0.0454 0.0260 1.0000
6.750 0.9717 0.02000 0.01146 -0.0439 0.0253 1.0000
7.000 0.9917 0.02129 0.01290 -0.0426 0.0246 1.0000
7.250 1.0119 0.02258 0.01429 -0.0414 0.0229 1.0000
7.500 1.0315 0.02435 0.01614 -0.0399 0.0227 1.0000
7.750 1.0525 0.02641 0.01830 -0.0385 0.0229 1.0000
8.000 1.0745 0.02890 0.02095 -0.0373 0.0236 1.0000
8.250 1.0961 0.03240 0.02466 -0.0362 0.0247 1.0000
8.500 1.1209 0.03402 0.02648 -0.0351 0.0266 1.0000
8.750 1.1512 0.04716 0.04118 -0.0307 0.0703 1.0000
14.000 0.7140 0.15476 0.15159 -0.0489 0.0648 1.0000
14.250 0.7139 0.15768 0.15452 -0.0498 0.0627 1.0000
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Polar data table (+)
Polar graphs
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