GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 399 AIRFOIL (goe399-il) Reynolds number: 200,000 Max Cl/Cd: 76.86 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe399-il-200000-n5.txt Download as CSV file: xf-goe399-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 399 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3532 0.10804 0.10444 -0.0288 1.0000 0.0188
-9.000 -0.3496 0.10499 0.10143 -0.0297 1.0000 0.0188
-8.750 -0.3443 0.09964 0.09611 -0.0280 1.0000 0.0199
-8.500 -0.2610 0.08333 0.08009 -0.0314 1.0000 0.0178
-8.250 -0.2607 0.08005 0.07685 -0.0312 1.0000 0.0173
-8.000 -0.3369 0.09105 0.08762 -0.0285 1.0000 0.0174
-7.750 -0.3378 0.08837 0.08499 -0.0282 1.0000 0.0169
-7.500 -0.3417 0.08598 0.08267 -0.0275 1.0000 0.0165
-7.250 -0.3482 0.08384 0.08061 -0.0263 1.0000 0.0161
-7.000 -0.3518 0.08127 0.07811 -0.0261 1.0000 0.0158
-6.750 -0.3530 0.07845 0.07534 -0.0268 0.9995 0.0155
-6.500 -0.3272 0.07290 0.06976 -0.0352 0.9922 0.0152
-6.250 -0.2988 0.06727 0.06408 -0.0439 0.9853 0.0152
-6.000 -0.2679 0.06173 0.05847 -0.0525 0.9780 0.0161
-5.750 -0.2344 0.05529 0.05191 -0.0618 0.9698 0.0172
-5.500 -0.1986 0.04852 0.04494 -0.0703 0.9632 0.0175
-5.250 -0.1636 0.04106 0.03717 -0.0776 0.9550 0.0181
-5.000 -0.1318 0.03327 0.02895 -0.0827 0.9459 0.0193
-4.750 -0.1008 0.03343 0.02907 -0.0844 0.9394 0.0213
-4.500 -0.0714 0.02941 0.02470 -0.0863 0.9287 0.0233
-4.250 -0.0423 0.02315 0.01765 -0.0875 0.9182 0.0269
-4.000 -0.0135 0.02002 0.01391 -0.0881 0.9078 0.0301
-3.750 0.0162 0.01920 0.01290 -0.0887 0.8963 0.0326
-3.500 0.0448 0.01815 0.01152 -0.0887 0.8834 0.0366
-3.250 0.0734 0.01678 0.00970 -0.0886 0.8700 0.0387
-3.000 0.1011 0.01562 0.00826 -0.0885 0.8565 0.0414
-2.750 0.1287 0.01483 0.00729 -0.0883 0.8439 0.0430
-2.500 0.1562 0.01419 0.00646 -0.0880 0.8321 0.0447
-2.250 0.1835 0.01361 0.00572 -0.0877 0.8206 0.0464
-2.000 0.2105 0.01311 0.00508 -0.0873 0.8094 0.0479
-1.750 0.2375 0.01278 0.00459 -0.0869 0.7984 0.0503
-1.500 0.2640 0.01250 0.00420 -0.0865 0.7871 0.0520
-1.250 0.2899 0.01201 0.00367 -0.0860 0.7764 0.0535
-1.000 0.3161 0.01170 0.00331 -0.0855 0.7663 0.0556
-0.750 0.3424 0.01150 0.00306 -0.0851 0.7560 0.0589
-0.500 0.3686 0.01134 0.00283 -0.0846 0.7454 0.0644
-0.250 0.3948 0.01117 0.00264 -0.0842 0.7353 0.0741
0.000 0.4210 0.01105 0.00250 -0.0837 0.7255 0.0883
0.250 0.4471 0.01095 0.00241 -0.0833 0.7149 0.1076
0.500 0.4727 0.01077 0.00240 -0.0829 0.7044 0.1646
1.000 0.5512 0.00896 0.00241 -0.0880 0.6822 1.0000
1.250 0.5767 0.00906 0.00242 -0.0874 0.6695 1.0000
1.500 0.6020 0.00918 0.00244 -0.0868 0.6546 1.0000
1.750 0.6269 0.00931 0.00245 -0.0860 0.6371 1.0000
2.000 0.6518 0.00944 0.00250 -0.0853 0.6182 1.0000
2.250 0.6768 0.00958 0.00256 -0.0846 0.6006 1.0000
2.500 0.7018 0.00973 0.00264 -0.0840 0.5841 1.0000
2.750 0.7266 0.00990 0.00274 -0.0833 0.5669 1.0000
3.000 0.7513 0.01009 0.00287 -0.0826 0.5476 1.0000
3.250 0.7754 0.01031 0.00299 -0.0818 0.5255 1.0000
3.500 0.7993 0.01055 0.00314 -0.0810 0.5031 1.0000
3.750 0.8231 0.01082 0.00334 -0.0802 0.4827 1.0000
4.000 0.8468 0.01110 0.00355 -0.0794 0.4642 1.0000
4.250 0.8707 0.01138 0.00378 -0.0786 0.4468 1.0000
4.500 0.8947 0.01167 0.00404 -0.0779 0.4309 1.0000
4.750 0.9185 0.01196 0.00434 -0.0772 0.4148 1.0000
5.000 0.9423 0.01226 0.00464 -0.0764 0.3988 1.0000
5.250 0.9660 0.01257 0.00496 -0.0757 0.3819 1.0000
5.500 0.9891 0.01289 0.00530 -0.0748 0.3599 1.0000
5.750 1.0118 0.01325 0.00565 -0.0740 0.3353 1.0000
6.000 1.0335 0.01368 0.00602 -0.0729 0.3003 1.0000
6.250 1.0512 0.01445 0.00652 -0.0714 0.2431 1.0000
6.500 1.0611 0.01607 0.00743 -0.0691 0.1236 1.0000
6.750 1.0756 0.01732 0.00840 -0.0672 0.0761 1.0000
7.000 1.0937 0.01816 0.00920 -0.0659 0.0600 1.0000
7.250 1.1133 0.01882 0.00993 -0.0646 0.0492 1.0000
7.500 1.1320 0.01955 0.01071 -0.0633 0.0364 1.0000
7.750 1.1490 0.02040 0.01152 -0.0617 0.0240 1.0000
8.000 1.1644 0.02137 0.01251 -0.0599 0.0190 1.0000
8.250 1.1766 0.02257 0.01383 -0.0576 0.0166 1.0000
8.500 1.1899 0.02359 0.01506 -0.0554 0.0153 1.0000
8.750 1.2022 0.02464 0.01623 -0.0533 0.0138 1.0000
9.000 1.2118 0.02579 0.01749 -0.0507 0.0126 1.0000
9.250 1.2178 0.02709 0.01891 -0.0477 0.0119 1.0000
9.500 1.2217 0.02863 0.02057 -0.0446 0.0113 1.0000
9.750 1.2230 0.03061 0.02268 -0.0414 0.0108 1.0000
10.000 1.2256 0.03285 0.02507 -0.0386 0.0104 1.0000
10.250 1.2339 0.03456 0.02693 -0.0366 0.0101 1.0000
10.500 1.2425 0.03624 0.02879 -0.0348 0.0097 1.0000
10.750 1.2502 0.03802 0.03075 -0.0330 0.0092 1.0000
11.000 1.2565 0.03977 0.03266 -0.0314 0.0085 1.0000
11.250 1.2612 0.04205 0.03513 -0.0298 0.0082 1.0000
11.500 1.2644 0.04453 0.03782 -0.0282 0.0080 1.0000
11.750 1.2660 0.04715 0.04071 -0.0269 0.0079 1.0000
12.000 1.2651 0.05005 0.04382 -0.0257 0.0077 1.0000
12.250 1.2626 0.05312 0.04710 -0.0249 0.0076 1.0000
12.500 1.2576 0.05661 0.05081 -0.0243 0.0075 1.0000
12.750 1.2508 0.06037 0.05477 -0.0242 0.0074 1.0000
13.000 1.2423 0.06449 0.05911 -0.0244 0.0073 1.0000
13.250 1.2312 0.06918 0.06404 -0.0252 0.0073 1.0000
13.500 1.2188 0.07425 0.06933 -0.0265 0.0073 1.0000
13.750 1.2050 0.07978 0.07505 -0.0285 0.0072 1.0000
14.000 1.1886 0.08618 0.08170 -0.0311 0.0073 1.0000
14.250 1.1731 0.09273 0.08842 -0.0343 0.0072 1.0000
14.500 1.1524 0.10105 0.09700 -0.0388 0.0074 1.0000
14.750 1.1340 0.10931 0.10544 -0.0436 0.0074 1.0000
15.000 1.1113 0.11940 0.11574 -0.0496 0.0075 1.0000
15.250 1.0847 0.13160 0.12814 -0.0571 0.0077 1.0000
15.500 1.0441 0.15074 0.14740 -0.0684 0.0082 1.0000
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Polar data table (+)
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