GOE 514 AIRFOIL (goe514-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 514 AIRFOIL (goe514-il) Reynolds number: 500,000 Max Cl/Cd: 69.2 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe514-il-500000.txt Download as CSV file: xf-goe514-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 514 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.4908 0.08378 0.08077 -0.0982 0.9834 0.0185
-14.750 -0.5119 0.07508 0.07192 -0.1060 0.9825 0.0185
-14.500 -0.5499 0.06690 0.06358 -0.1107 0.9769 0.0184
-14.250 -0.5694 0.05964 0.05617 -0.1176 0.9740 0.0183
-14.000 -0.5897 0.05102 0.04736 -0.1276 0.9715 0.0182
-13.750 -0.6073 0.04351 0.03964 -0.1363 0.9660 0.0180
-13.500 -0.6205 0.03869 0.03462 -0.1387 0.9612 0.0182
-13.250 -0.6181 0.03576 0.03154 -0.1396 0.9586 0.0184
-13.000 -0.6085 0.03358 0.02922 -0.1402 0.9569 0.0186
-12.750 -0.6269 0.03269 0.02826 -0.1336 0.9491 0.0188
-12.500 -0.6193 0.03134 0.02681 -0.1319 0.9457 0.0190
-12.250 -0.6067 0.02988 0.02525 -0.1309 0.9435 0.0194
-12.000 -0.5860 0.02845 0.02370 -0.1310 0.9421 0.0196
-11.750 -0.5996 0.02793 0.02310 -0.1239 0.9335 0.0198
-11.500 -0.5814 0.02673 0.02178 -0.1230 0.9307 0.0203
-11.250 -0.5583 0.02556 0.02048 -0.1230 0.9290 0.0207
-11.000 -0.5323 0.02444 0.01921 -0.1233 0.9279 0.0211
-10.750 -0.5067 0.02313 0.01780 -0.1237 0.9269 0.0217
-10.500 -0.5162 0.02276 0.01738 -0.1167 0.9179 0.0220
-10.250 -0.4927 0.02181 0.01639 -0.1163 0.9155 0.0228
-10.000 -0.4629 0.02095 0.01546 -0.1170 0.9140 0.0238
-9.750 -0.4285 0.02006 0.01446 -0.1185 0.9130 0.0248
-9.500 -0.3921 0.01890 0.01322 -0.1207 0.9119 0.0259
-9.250 -0.3523 0.01792 0.01219 -0.1233 0.9108 0.0273
-9.000 -0.3454 0.01754 0.01175 -0.1190 0.9035 0.0283
-8.750 -0.3180 0.01679 0.01092 -0.1189 0.8997 0.0300
-8.500 -0.2840 0.01601 0.01011 -0.1202 0.8974 0.0325
-8.250 -0.2455 0.01522 0.00927 -0.1225 0.8954 0.0364
-8.000 -0.2056 0.01449 0.00854 -0.1250 0.8936 0.0434
-7.750 -0.2018 0.01425 0.00830 -0.1198 0.8850 0.0483
-7.500 -0.1669 0.01378 0.00784 -0.1212 0.8812 0.0580
-7.250 -0.1268 0.01332 0.00735 -0.1236 0.8781 0.0661
-7.000 -0.1090 0.01313 0.00711 -0.1213 0.8711 0.0705
-6.750 -0.0832 0.01268 0.00665 -0.1207 0.8647 0.0766
-6.500 -0.0454 0.01225 0.00614 -0.1227 0.8603 0.0825
-6.250 -0.0362 0.01198 0.00589 -0.1186 0.8503 0.0868
-6.000 -0.0030 0.01160 0.00546 -0.1196 0.8444 0.0934
-5.750 0.0095 0.01137 0.00526 -0.1161 0.8338 0.0999
-5.500 0.0413 0.01107 0.00499 -0.1168 0.8264 0.1134
-5.250 0.0579 0.01095 0.00489 -0.1142 0.8147 0.1274
-5.000 0.0800 0.01088 0.00482 -0.1128 0.8035 0.1410
-4.750 0.1051 0.01080 0.00470 -0.1120 0.7917 0.1521
-4.500 0.1309 0.01082 0.00458 -0.1113 0.7786 0.1596
-4.250 0.1519 0.01069 0.00443 -0.1097 0.7644 0.1664
-4.000 0.1737 0.01070 0.00433 -0.1082 0.7504 0.1718
-3.750 0.1958 0.01075 0.00425 -0.1068 0.7377 0.1756
-3.500 0.2172 0.01065 0.00411 -0.1053 0.7257 0.1806
-3.250 0.2374 0.01066 0.00405 -0.1036 0.7135 0.1847
-3.000 0.2549 0.01068 0.00400 -0.1012 0.7016 0.1884
-2.750 0.2727 0.01071 0.00393 -0.0989 0.6902 0.1910
-2.500 0.2885 0.01068 0.00384 -0.0962 0.6787 0.1943
-2.250 0.3021 0.01064 0.00379 -0.0931 0.6674 0.1980
-2.000 0.3175 0.01065 0.00375 -0.0903 0.6561 0.2013
-1.750 0.3317 0.01069 0.00372 -0.0873 0.6437 0.2046
-1.500 0.3448 0.01072 0.00369 -0.0840 0.6301 0.2073
-1.250 0.3577 0.01076 0.00367 -0.0808 0.6159 0.2102
-1.000 0.3694 0.01082 0.00369 -0.0773 0.5997 0.2143
-0.750 0.3798 0.01093 0.00373 -0.0735 0.5808 0.2179
-0.500 0.3904 0.01107 0.00378 -0.0699 0.5606 0.2220
-0.250 0.3993 0.01126 0.00386 -0.0659 0.5378 0.2270
0.000 0.4089 0.01146 0.00398 -0.0622 0.5135 0.2336
0.250 0.4196 0.01171 0.00410 -0.0587 0.4919 0.2403
0.500 0.4316 0.01191 0.00424 -0.0556 0.4746 0.2476
0.750 0.4465 0.01213 0.00438 -0.0530 0.4609 0.2565
1.000 0.4622 0.01233 0.00453 -0.0506 0.4498 0.2653
1.250 0.4791 0.01255 0.00469 -0.0485 0.4398 0.2751
1.500 0.4968 0.01271 0.00482 -0.0465 0.4319 0.2833
1.750 0.5153 0.01290 0.00497 -0.0448 0.4247 0.2911
2.000 0.5331 0.01311 0.00512 -0.0429 0.4186 0.2978
2.250 0.5535 0.01321 0.00525 -0.0415 0.4131 0.3045
2.500 0.5730 0.01340 0.00539 -0.0400 0.4076 0.3107
2.750 0.5906 0.01360 0.00555 -0.0381 0.4024 0.3165
3.000 0.6108 0.01372 0.00569 -0.0368 0.3980 0.3224
3.250 0.6309 0.01387 0.00584 -0.0354 0.3931 0.3280
3.500 0.6497 0.01403 0.00598 -0.0338 0.3888 0.3334
3.750 0.6688 0.01426 0.00617 -0.0323 0.3843 0.3392
4.000 0.6895 0.01439 0.00633 -0.0311 0.3809 0.3451
4.250 0.7091 0.01451 0.00648 -0.0297 0.3773 0.3508
4.500 0.7286 0.01467 0.00666 -0.0283 0.3737 0.3578
4.750 0.7479 0.01489 0.00684 -0.0269 0.3701 0.3645
5.000 0.7681 0.01510 0.00705 -0.0258 0.3663 0.3717
5.250 0.7876 0.01522 0.00724 -0.0244 0.3632 0.3820
5.500 0.8070 0.01536 0.00744 -0.0231 0.3600 0.3934
5.750 0.8262 0.01551 0.00765 -0.0218 0.3570 0.4101
6.000 0.8433 0.01545 0.00784 -0.0202 0.3541 0.5055
6.250 1.1148 0.01611 0.00966 -0.0735 0.3440 1.0000
6.500 1.1291 0.01633 0.00988 -0.0712 0.3408 1.0000
6.750 1.1431 0.01660 0.01012 -0.0690 0.3377 1.0000
7.000 1.1579 0.01694 0.01040 -0.0669 0.3338 1.0000
7.250 1.1735 0.01719 0.01068 -0.0650 0.3312 1.0000
7.500 1.1895 0.01744 0.01096 -0.0632 0.3289 1.0000
7.750 1.2054 0.01771 0.01125 -0.0613 0.3265 1.0000
8.000 1.2212 0.01800 0.01156 -0.0595 0.3240 1.0000
8.250 1.2371 0.01832 0.01187 -0.0578 0.3215 1.0000
8.500 1.2529 0.01869 0.01221 -0.0561 0.3184 1.0000
8.750 1.2695 0.01905 0.01257 -0.0546 0.3154 1.0000
9.000 1.2851 0.01937 0.01295 -0.0529 0.3133 1.0000
9.250 1.3012 0.01971 0.01333 -0.0513 0.3110 1.0000
9.500 1.3171 0.02007 0.01371 -0.0497 0.3085 1.0000
9.750 1.3321 0.02048 0.01414 -0.0481 0.3058 1.0000
10.000 1.3460 0.02095 0.01458 -0.0463 0.3023 1.0000
10.250 1.3609 0.02141 0.01506 -0.0447 0.2988 1.0000
10.500 1.3748 0.02185 0.01558 -0.0430 0.2958 1.0000
10.750 1.3881 0.02234 0.01612 -0.0413 0.2922 1.0000
11.000 1.4017 0.02288 0.01666 -0.0397 0.2889 1.0000
11.250 1.4148 0.02348 0.01724 -0.0381 0.2857 1.0000
11.500 1.4284 0.02405 0.01788 -0.0366 0.2824 1.0000
11.750 1.4420 0.02462 0.01853 -0.0352 0.2788 1.0000
12.000 1.4545 0.02528 0.01922 -0.0336 0.2750 1.0000
12.250 1.4655 0.02604 0.01998 -0.0320 0.2711 1.0000
12.500 1.4770 0.02682 0.02079 -0.0305 0.2673 1.0000
12.750 1.4900 0.02753 0.02159 -0.0293 0.2625 1.0000
13.000 1.5010 0.02840 0.02249 -0.0278 0.2584 1.0000
13.250 1.5096 0.02944 0.02352 -0.0263 0.2543 1.0000
13.500 1.5218 0.03030 0.02447 -0.0251 0.2493 1.0000
13.750 1.5304 0.03142 0.02563 -0.0237 0.2430 1.0000
14.000 1.5371 0.03271 0.02693 -0.0223 0.2367 1.0000
14.250 1.5471 0.03383 0.02811 -0.0212 0.2308 1.0000
14.500 1.5497 0.03551 0.02978 -0.0196 0.2239 1.0000
14.750 1.5559 0.03700 0.03131 -0.0185 0.2142 1.0000
15.000 1.5580 0.03883 0.03316 -0.0171 0.2055 1.0000
15.250 1.5552 0.04114 0.03546 -0.0156 0.1953 1.0000
15.500 1.5473 0.04399 0.03827 -0.0140 0.1804 1.0000
15.750 1.5332 0.04752 0.04175 -0.0124 0.1642 1.0000
16.000 1.5222 0.05087 0.04509 -0.0111 0.1539 1.0000
16.250 1.5006 0.05544 0.04963 -0.0098 0.1392 1.0000
16.500 1.4828 0.05984 0.05405 -0.0089 0.1301 1.0000
16.750 1.4686 0.06399 0.05823 -0.0084 0.1226 1.0000
17.000 1.4521 0.06854 0.06283 -0.0081 0.1171 1.0000
17.250 1.4324 0.07365 0.06799 -0.0080 0.1092 1.0000
17.500 1.4108 0.07915 0.07353 -0.0082 0.1013 1.0000
17.750 1.3905 0.08462 0.07906 -0.0087 0.0951 1.0000
18.000 1.3674 0.09057 0.08503 -0.0094 0.0841 1.0000
18.250 1.3420 0.09692 0.09140 -0.0103 0.0726 1.0000
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