GOE 396 AIRFOIL (goe396-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 396 AIRFOIL (goe396-il) Reynolds number: 100,000 Max Cl/Cd: 66.78 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe396-il-100000-n5.txt Download as CSV file: xf-goe396-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 396 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2951 0.09816 0.09379 -0.0272 1.0000 0.0271
-7.000 -0.3050 0.09711 0.09285 -0.0244 1.0000 0.0274
-6.750 -0.3162 0.09616 0.09200 -0.0214 1.0000 0.0276
-6.500 -0.2939 0.09207 0.08790 -0.0269 0.9931 0.0286
-6.250 -0.2701 0.08801 0.08380 -0.0329 0.9858 0.0297
-6.000 -0.2449 0.08405 0.07981 -0.0392 0.9787 0.0310
-5.750 -0.2196 0.08024 0.07598 -0.0455 0.9704 0.0325
-5.500 -0.1865 0.07672 0.07241 -0.0547 0.9616 0.0342
-5.250 -0.1426 0.07285 0.06842 -0.0665 0.9554 0.0349
-5.000 -0.1106 0.06903 0.06452 -0.0730 0.9469 0.0350
-4.750 -0.0708 0.06462 0.05999 -0.0808 0.9425 0.0352
-4.500 -0.0700 0.06034 0.05582 -0.0768 0.9355 0.0380
-4.250 -0.0337 0.05663 0.05199 -0.0828 0.9303 0.0419
-4.000 0.0227 0.05343 0.04848 -0.0940 0.9230 0.0456
-3.500 0.0841 0.04292 0.03770 -0.1007 0.9115 0.0238
-3.250 0.1195 0.03906 0.03363 -0.1046 0.9051 0.0232
-3.000 0.1614 0.03480 0.02908 -0.1093 0.9010 0.0229
-2.750 0.1958 0.03069 0.02459 -0.1117 0.8930 0.0238
-2.500 0.2351 0.02606 0.01936 -0.1146 0.8884 0.0259
-2.250 0.2655 0.02326 0.01604 -0.1154 0.8812 0.0272
-2.000 0.2991 0.02079 0.01292 -0.1163 0.8757 0.0304
-1.750 0.3297 0.01905 0.01064 -0.1165 0.8690 0.0378
-1.500 0.3606 0.01781 0.00908 -0.1168 0.8625 0.0489
-1.250 0.3897 0.01700 0.00806 -0.1168 0.8553 0.0626
-1.000 0.4200 0.01641 0.00727 -0.1170 0.8484 0.0761
-0.750 0.4483 0.01591 0.00667 -0.1168 0.8404 0.0906
-0.500 0.4784 0.01555 0.00624 -0.1170 0.8336 0.1193
-0.250 0.5059 0.01539 0.00602 -0.1168 0.8247 0.1527
0.000 0.5360 0.01521 0.00577 -0.1171 0.8177 0.1871
0.250 0.5623 0.01510 0.00569 -0.1167 0.8083 0.2205
0.500 0.5898 0.01495 0.00554 -0.1165 0.7999 0.2500
0.750 0.6177 0.01478 0.00539 -0.1164 0.7917 0.2900
1.000 0.6432 0.01451 0.00536 -0.1160 0.7821 0.3909
1.500 0.7111 0.01356 0.00514 -0.1183 0.7636 1.0000
1.750 0.7359 0.01367 0.00515 -0.1175 0.7517 1.0000
2.000 0.7609 0.01375 0.00516 -0.1167 0.7391 1.0000
2.250 0.7859 0.01383 0.00518 -0.1159 0.7261 1.0000
2.500 0.8107 0.01391 0.00526 -0.1151 0.7125 1.0000
2.750 0.8356 0.01400 0.00533 -0.1142 0.6986 1.0000
3.000 0.8605 0.01411 0.00542 -0.1134 0.6846 1.0000
3.250 0.8854 0.01423 0.00556 -0.1127 0.6708 1.0000
3.500 0.9105 0.01438 0.00580 -0.1120 0.6586 1.0000
3.750 0.9355 0.01454 0.00602 -0.1112 0.6456 1.0000
4.000 0.9600 0.01472 0.00628 -0.1104 0.6313 1.0000
4.250 0.9846 0.01493 0.00659 -0.1096 0.6176 1.0000
4.500 1.0086 0.01515 0.00699 -0.1087 0.6015 1.0000
4.750 1.0258 0.01536 0.00700 -0.1060 0.5420 1.0000
5.000 1.0419 0.01587 0.00722 -0.1033 0.4690 1.0000
5.250 1.0446 0.01759 0.00779 -0.0990 0.2876 1.0000
5.500 1.0459 0.02022 0.00925 -0.0953 0.1172 1.0000
5.750 1.0549 0.02213 0.01067 -0.0925 0.0256 1.0000
6.000 1.0698 0.02336 0.01206 -0.0902 0.0204 1.0000
6.250 1.0853 0.02448 0.01341 -0.0880 0.0189 1.0000
6.500 1.0998 0.02566 0.01484 -0.0857 0.0175 1.0000
6.750 1.1119 0.02699 0.01638 -0.0832 0.0154 1.0000
7.000 1.1216 0.02852 0.01808 -0.0804 0.0143 1.0000
7.250 1.1307 0.03013 0.01984 -0.0776 0.0139 1.0000
7.500 1.1400 0.03197 0.02178 -0.0748 0.0135 1.0000
7.750 1.1545 0.03399 0.02388 -0.0727 0.0132 1.0000
8.000 1.1774 0.03644 0.02653 -0.0718 0.0130 1.0000
8.250 1.2055 0.03983 0.03004 -0.0718 0.0124 1.0000
8.500 1.2294 0.04399 0.03453 -0.0713 0.0115 1.0000
8.750 1.2435 0.04620 0.03714 -0.0692 0.0111 1.0000
9.000 1.2569 0.04956 0.04087 -0.0674 0.0112 1.0000
9.250 1.2658 0.05347 0.04515 -0.0653 0.0114 1.0000
9.750 1.2768 0.06056 0.05290 -0.0606 0.0120 1.0000
10.000 1.2753 0.06258 0.05524 -0.0573 0.0123 1.0000
10.250 1.2687 0.06466 0.05765 -0.0535 0.0126 1.0000
10.500 1.2583 0.06730 0.06065 -0.0501 0.0130 1.0000
10.750 1.2411 0.07064 0.06436 -0.0471 0.0135 1.0000
11.000 1.2249 0.07446 0.06849 -0.0454 0.0138 1.0000
11.250 1.2071 0.07891 0.07323 -0.0445 0.0141 1.0000
11.500 1.1895 0.08371 0.07827 -0.0447 0.0143 1.0000
11.750 1.1712 0.08898 0.08375 -0.0457 0.0145 1.0000
12.000 1.1526 0.09477 0.08974 -0.0477 0.0146 1.0000
12.250 1.1344 0.10107 0.09620 -0.0506 0.0146 1.0000
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Polar data table (+)
Polar graphs
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