GOE 633 AIRFOIL (goe633-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 633 AIRFOIL (goe633-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.63 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe633-il-1000000-n5.txt Download as CSV file: xf-goe633-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 633 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7889 0.09551 0.09316 -0.0320 1.0000 0.0211
-15.750 -0.8573 0.08029 0.07772 -0.0420 1.0000 0.0212
-15.500 -0.8998 0.07040 0.06770 -0.0487 1.0000 0.0212
-15.250 -0.9461 0.06005 0.05720 -0.0562 1.0000 0.0212
-15.000 -0.9878 0.04940 0.04639 -0.0650 1.0000 0.0212
-14.750 -1.0175 0.03701 0.03366 -0.0797 1.0000 0.0212
-14.500 -1.0262 0.03395 0.03046 -0.0800 1.0000 0.0212
-14.250 -0.9775 0.03064 0.02684 -0.0902 0.9039 0.0214
-14.000 -0.9831 0.02963 0.02539 -0.0866 0.8127 0.0215
-13.750 -0.9827 0.02862 0.02422 -0.0834 0.7918 0.0216
-13.500 -0.9810 0.02766 0.02311 -0.0801 0.7782 0.0217
-13.250 -0.9793 0.02672 0.02205 -0.0766 0.7666 0.0217
-13.000 -0.9705 0.02589 0.02109 -0.0741 0.7580 0.0218
-12.750 -0.9588 0.02507 0.02015 -0.0719 0.7492 0.0218
-12.500 -0.9451 0.02429 0.01927 -0.0700 0.7420 0.0219
-12.250 -0.9302 0.02353 0.01840 -0.0682 0.7348 0.0220
-12.000 -0.9155 0.02272 0.01748 -0.0664 0.7284 0.0220
-11.750 -0.9019 0.02171 0.01636 -0.0644 0.7227 0.0222
-11.500 -0.8859 0.02087 0.01542 -0.0627 0.7163 0.0223
-11.250 -0.8681 0.02016 0.01463 -0.0612 0.7105 0.0225
-11.000 -0.8487 0.01951 0.01392 -0.0598 0.7053 0.0226
-10.750 -0.8282 0.01894 0.01329 -0.0586 0.6999 0.0227
-10.500 -0.8069 0.01844 0.01271 -0.0575 0.6947 0.0229
-10.250 -0.7851 0.01794 0.01215 -0.0564 0.6899 0.0230
-10.000 -0.7629 0.01745 0.01160 -0.0554 0.6845 0.0231
-9.750 -0.7403 0.01700 0.01109 -0.0544 0.6791 0.0233
-9.500 -0.7173 0.01659 0.01060 -0.0535 0.6744 0.0234
-9.250 -0.6933 0.01620 0.01017 -0.0527 0.6703 0.0237
-9.000 -0.6694 0.01581 0.00972 -0.0518 0.6654 0.0239
-8.750 -0.6454 0.01543 0.00929 -0.0510 0.6601 0.0241
-8.500 -0.6213 0.01505 0.00884 -0.0502 0.6554 0.0242
-8.250 -0.5968 0.01467 0.00840 -0.0494 0.6509 0.0244
-8.000 -0.5722 0.01430 0.00798 -0.0487 0.6462 0.0246
-7.750 -0.5474 0.01395 0.00757 -0.0480 0.6416 0.0247
-7.500 -0.5222 0.01364 0.00720 -0.0473 0.6373 0.0249
-7.250 -0.4968 0.01331 0.00684 -0.0467 0.6327 0.0251
-7.000 -0.4712 0.01302 0.00648 -0.0460 0.6275 0.0253
-6.750 -0.4456 0.01274 0.00615 -0.0454 0.6226 0.0254
-6.500 -0.4195 0.01248 0.00585 -0.0449 0.6186 0.0256
-6.250 -0.3932 0.01222 0.00556 -0.0444 0.6138 0.0257
-6.000 -0.3669 0.01199 0.00528 -0.0439 0.6075 0.0258
-5.750 -0.3412 0.01168 0.00491 -0.0432 0.6010 0.0261
-5.500 -0.3151 0.01138 0.00457 -0.0427 0.5943 0.0264
-5.250 -0.2888 0.01115 0.00429 -0.0422 0.5879 0.0267
-5.000 -0.2621 0.01094 0.00405 -0.0417 0.5819 0.0271
-4.750 -0.2352 0.01075 0.00383 -0.0413 0.5741 0.0274
-4.500 -0.2083 0.01059 0.00363 -0.0409 0.5671 0.0278
-4.250 -0.1811 0.01043 0.00344 -0.0405 0.5609 0.0282
-4.000 -0.1539 0.01029 0.00327 -0.0402 0.5548 0.0286
-3.750 -0.1267 0.01015 0.00310 -0.0398 0.5494 0.0291
-3.500 -0.0992 0.01002 0.00294 -0.0395 0.5437 0.0294
-3.250 -0.0719 0.00990 0.00280 -0.0392 0.5383 0.0298
-3.000 -0.0445 0.00980 0.00267 -0.0388 0.5335 0.0301
-2.750 -0.0170 0.00965 0.00251 -0.0385 0.5286 0.0307
-2.500 0.0103 0.00953 0.00237 -0.0382 0.5224 0.0315
-2.250 0.0376 0.00944 0.00226 -0.0378 0.5164 0.0324
-2.000 0.0652 0.00935 0.00216 -0.0375 0.5104 0.0334
-1.750 0.0926 0.00928 0.00207 -0.0372 0.5043 0.0344
-1.500 0.1200 0.00921 0.00199 -0.0369 0.4988 0.0364
-1.250 0.1475 0.00912 0.00191 -0.0366 0.4930 0.0394
-1.000 0.1740 0.00896 0.00180 -0.0362 0.4862 0.0584
-0.750 0.1999 0.00873 0.00172 -0.0357 0.4798 0.1026
-0.500 0.2269 0.00866 0.00168 -0.0353 0.4714 0.1152
-0.250 0.2536 0.00861 0.00165 -0.0349 0.4632 0.1292
0.000 0.2797 0.00852 0.00164 -0.0344 0.4526 0.1600
0.250 0.3064 0.00851 0.00166 -0.0341 0.4409 0.1789
0.500 0.3331 0.00857 0.00168 -0.0337 0.4266 0.1878
0.750 0.3595 0.00861 0.00171 -0.0332 0.4134 0.1981
1.000 0.3861 0.00870 0.00174 -0.0328 0.3998 0.2047
1.250 0.4125 0.00876 0.00179 -0.0324 0.3864 0.2124
1.500 0.4388 0.00885 0.00184 -0.0320 0.3731 0.2194
1.750 0.4650 0.00895 0.00190 -0.0316 0.3607 0.2246
2.000 0.4908 0.00905 0.00198 -0.0311 0.3486 0.2338
2.250 0.5170 0.00914 0.00204 -0.0306 0.3383 0.2413
2.500 0.5431 0.00922 0.00212 -0.0302 0.3305 0.2501
2.750 0.5694 0.00929 0.00219 -0.0298 0.3235 0.2586
3.000 0.5952 0.00938 0.00228 -0.0293 0.3162 0.2686
3.250 0.6216 0.00942 0.00235 -0.0289 0.3116 0.2824
3.750 0.6727 0.00955 0.00254 -0.0279 0.3007 0.3201
4.000 0.6980 0.00954 0.00263 -0.0273 0.2967 0.3564
4.250 0.7154 0.00911 0.00275 -0.0254 0.2924 0.5692
4.500 0.7267 0.00827 0.00294 -0.0216 0.2886 0.9323
4.750 0.7601 0.00848 0.00313 -0.0228 0.2831 0.9518
5.000 0.7951 0.00863 0.00328 -0.0242 0.2793 0.9582
5.250 0.8266 0.00879 0.00343 -0.0250 0.2743 0.9631
5.500 0.8502 0.00896 0.00357 -0.0241 0.2687 0.9685
5.750 0.8870 0.00916 0.00375 -0.0261 0.2634 0.9706
6.000 0.9219 0.00936 0.00393 -0.0277 0.2569 0.9729
6.250 0.9528 0.00959 0.00412 -0.0284 0.2509 0.9751
6.500 0.9819 0.00975 0.00428 -0.0288 0.2464 0.9773
6.750 1.0074 0.00994 0.00445 -0.0284 0.2404 0.9801
7.000 1.0345 0.01018 0.00465 -0.0284 0.2336 0.9819
7.250 1.0663 0.01041 0.00486 -0.0294 0.2252 0.9829
7.500 1.0981 0.01070 0.00511 -0.0306 0.2157 0.9843
7.750 1.1303 0.01108 0.00541 -0.0319 0.2020 0.9864
8.000 1.1585 0.01155 0.00578 -0.0324 0.1833 0.9887
8.250 1.1832 0.01212 0.00623 -0.0324 0.1637 0.9913
8.500 1.2053 0.01267 0.00669 -0.0319 0.1479 0.9932
8.750 1.2343 0.01315 0.00711 -0.0327 0.1370 0.9946
9.000 1.2610 0.01359 0.00751 -0.0331 0.1291 0.9960
9.250 1.2854 0.01404 0.00793 -0.0330 0.1231 0.9973
9.500 1.3106 0.01439 0.00829 -0.0331 0.1198 0.9984
9.750 1.3357 0.01476 0.00866 -0.0331 0.1174 0.9993
10.000 1.3570 0.01518 0.00908 -0.0324 0.1142 1.0000
10.250 1.3615 0.01554 0.00945 -0.0283 0.1121 1.0000
10.500 1.3590 0.01589 0.00982 -0.0230 0.1099 1.0000
10.750 1.3627 0.01628 0.01025 -0.0190 0.1086 1.0000
11.000 1.3710 0.01670 0.01071 -0.0161 0.1077 1.0000
11.250 1.3804 0.01720 0.01125 -0.0136 0.1067 1.0000
11.500 1.3901 0.01781 0.01189 -0.0114 0.1051 1.0000
11.750 1.4004 0.01852 0.01263 -0.0096 0.1036 1.0000
12.000 1.4104 0.01936 0.01350 -0.0080 0.1016 1.0000
12.250 1.4202 0.02033 0.01448 -0.0066 0.0995 1.0000
12.500 1.4303 0.02134 0.01553 -0.0053 0.0976 1.0000
12.750 1.4416 0.02234 0.01656 -0.0043 0.0958 1.0000
13.000 1.4545 0.02326 0.01753 -0.0035 0.0945 1.0000
13.250 1.4659 0.02430 0.01861 -0.0026 0.0920 1.0000
13.500 1.4753 0.02554 0.01986 -0.0017 0.0890 1.0000
14.000 1.4910 0.02834 0.02271 0.0000 0.0821 1.0000
14.250 1.4932 0.03025 0.02459 0.0009 0.0739 1.0000
14.500 1.4872 0.03290 0.02716 0.0019 0.0618 1.0000
14.750 1.4810 0.03565 0.02990 0.0028 0.0542 1.0000
15.000 1.4752 0.03847 0.03273 0.0035 0.0483 1.0000
15.250 1.4690 0.04143 0.03571 0.0040 0.0430 1.0000
15.500 1.4631 0.04451 0.03882 0.0043 0.0381 1.0000
15.750 1.4517 0.04830 0.04262 0.0044 0.0307 1.0000
16.250 1.4233 0.05692 0.05127 0.0039 0.0178 1.0000
16.500 1.4196 0.06023 0.05463 0.0036 0.0166 1.0000
16.750 1.4160 0.06356 0.05803 0.0031 0.0158 1.0000
17.000 1.4102 0.06724 0.06177 0.0026 0.0148 1.0000
17.250 1.4055 0.07084 0.06544 0.0020 0.0141 1.0000
17.500 1.4016 0.07439 0.06907 0.0013 0.0138 1.0000
17.750 1.3951 0.07831 0.07306 0.0004 0.0133 1.0000
18.000 1.3884 0.08234 0.07717 -0.0005 0.0128 1.0000
18.250 1.3819 0.08642 0.08133 -0.0015 0.0126 1.0000
18.500 1.3764 0.09040 0.08539 -0.0026 0.0123 1.0000
18.750 1.3704 0.09447 0.08953 -0.0037 0.0121 1.0000
19.000 1.3642 0.09860 0.09374 -0.0049 0.0117 1.0000
19.250 1.3571 0.10293 0.09815 -0.0063 0.0117 1.0000
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