GOE 504 AIRFOIL (goe504-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 504 AIRFOIL (goe504-il) Reynolds number: 500,000 Max Cl/Cd: 91.73 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe504-il-500000.txt Download as CSV file: xf-goe504-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 504 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.2935 0.08050 0.07811 -0.1005 0.9829 0.0234
-12.750 -0.3312 0.06819 0.06567 -0.1104 0.9775 0.0229
-12.500 -0.3668 0.05512 0.05233 -0.1250 0.9726 0.0225
-12.250 -0.3849 0.04629 0.04320 -0.1369 0.9665 0.0225
-12.000 -0.3931 0.04024 0.03685 -0.1449 0.9589 0.0224
-11.750 -0.3918 0.03616 0.03242 -0.1500 0.9504 0.0227
-11.500 -0.3895 0.03306 0.02894 -0.1517 0.9397 0.0231
-11.250 -0.3910 0.03153 0.02713 -0.1493 0.9248 0.0234
-11.000 -0.3908 0.03055 0.02587 -0.1462 0.9096 0.0236
-10.750 -0.3920 0.02794 0.02297 -0.1433 0.8951 0.0242
-10.500 -0.3781 0.02636 0.02131 -0.1421 0.8830 0.0247
-10.250 -0.3581 0.02558 0.02052 -0.1414 0.8721 0.0253
-10.000 -0.3425 0.02460 0.01940 -0.1400 0.8609 0.0258
-9.750 -0.3282 0.02390 0.01855 -0.1381 0.8489 0.0267
-9.500 -0.3143 0.02306 0.01752 -0.1361 0.8375 0.0274
-9.250 -0.2988 0.02231 0.01654 -0.1342 0.8273 0.0280
-9.000 -0.2826 0.02192 0.01592 -0.1323 0.8172 0.0285
-8.750 -0.2659 0.02063 0.01444 -0.1307 0.8076 0.0290
-8.250 -0.2249 0.01842 0.01215 -0.1289 0.7906 0.0306
-8.000 -0.2037 0.01785 0.01150 -0.1279 0.7828 0.0317
-7.750 -0.1836 0.01728 0.01086 -0.1266 0.7744 0.0324
-7.500 -0.1619 0.01677 0.01022 -0.1256 0.7671 0.0331
-7.250 -0.1412 0.01629 0.00968 -0.1243 0.7593 0.0337
-7.000 -0.1185 0.01601 0.00926 -0.1233 0.7522 0.0343
-6.750 -0.1015 0.01506 0.00828 -0.1216 0.7449 0.0353
-6.500 -0.0825 0.01446 0.00762 -0.1201 0.7379 0.0362
-6.250 -0.0624 0.01401 0.00713 -0.1187 0.7311 0.0370
-6.000 -0.0417 0.01364 0.00670 -0.1174 0.7241 0.0378
-5.750 -0.0199 0.01331 0.00629 -0.1163 0.7177 0.0386
-5.500 0.0017 0.01301 0.00594 -0.1151 0.7106 0.0397
-5.250 0.0247 0.01276 0.00560 -0.1142 0.7045 0.0406
-5.000 0.0469 0.01250 0.00529 -0.1131 0.6977 0.0412
-4.750 0.0688 0.01217 0.00489 -0.1119 0.6912 0.0426
-4.500 0.0921 0.01194 0.00459 -0.1110 0.6850 0.0442
-4.250 0.1152 0.01173 0.00434 -0.1101 0.6783 0.0463
-4.000 0.1397 0.01160 0.00411 -0.1094 0.6721 0.0487
-3.750 0.1627 0.01138 0.00394 -0.1084 0.6655 0.0557
-3.500 0.1844 0.01104 0.00373 -0.1073 0.6591 0.0958
-3.250 0.2029 0.01046 0.00352 -0.1058 0.6531 0.1975
-3.000 0.2261 0.01032 0.00350 -0.1049 0.6463 0.2364
-2.750 0.2511 0.01030 0.00345 -0.1044 0.6403 0.2581
-2.500 0.2752 0.01026 0.00344 -0.1036 0.6337 0.2752
-2.250 0.2998 0.01026 0.00341 -0.1030 0.6273 0.2897
-2.000 0.3241 0.01023 0.00338 -0.1023 0.6211 0.3007
-1.750 0.3482 0.01021 0.00335 -0.1015 0.6144 0.3103
-1.500 0.3727 0.01023 0.00331 -0.1009 0.6085 0.3208
-1.250 0.3962 0.01018 0.00330 -0.1001 0.6021 0.3315
-1.000 0.4198 0.01017 0.00328 -0.0992 0.5958 0.3455
-0.750 0.4437 0.01017 0.00326 -0.0985 0.5899 0.3585
-0.500 0.4666 0.01012 0.00326 -0.0976 0.5837 0.3721
-0.250 0.4896 0.01011 0.00325 -0.0967 0.5778 0.3922
0.250 0.5308 0.00984 0.00329 -0.0940 0.5660 0.4822
0.500 0.5486 0.00964 0.00333 -0.0920 0.5606 0.5690
0.750 0.5624 0.00933 0.00340 -0.0892 0.5551 0.6763
1.000 0.5763 0.00907 0.00350 -0.0861 0.5493 0.7907
1.250 0.6164 0.00908 0.00373 -0.0885 0.5435 0.8952
1.500 0.6817 0.00931 0.00397 -0.0967 0.5362 0.9390
1.750 0.7320 0.00958 0.00414 -0.1016 0.5297 0.9565
2.000 0.7708 0.00977 0.00432 -0.1040 0.5234 0.9701
2.250 0.8109 0.01000 0.00447 -0.1068 0.5169 0.9796
2.500 0.8529 0.01021 0.00462 -0.1101 0.5107 0.9860
2.750 0.8941 0.01038 0.00476 -0.1132 0.5037 0.9923
3.000 0.9369 0.01059 0.00488 -0.1167 0.4972 0.9972
3.250 0.9732 0.01069 0.00498 -0.1189 0.4908 1.0000
3.500 0.9854 0.01080 0.00505 -0.1160 0.4854 1.0000
3.750 0.9979 0.01093 0.00514 -0.1131 0.4804 1.0000
4.000 1.0099 0.01101 0.00523 -0.1101 0.4748 1.0000
4.250 1.0181 0.01112 0.00530 -0.1063 0.4695 1.0000
4.500 1.0275 0.01124 0.00539 -0.1027 0.4642 1.0000
4.750 1.0390 0.01134 0.00550 -0.0996 0.4586 1.0000
5.000 1.0509 0.01151 0.00563 -0.0966 0.4532 1.0000
5.250 1.0648 0.01168 0.00579 -0.0941 0.4481 1.0000
5.500 1.0796 0.01183 0.00595 -0.0918 0.4424 1.0000
5.750 1.0935 0.01206 0.00613 -0.0893 0.4368 1.0000
6.000 1.1093 0.01226 0.00634 -0.0873 0.4312 1.0000
6.250 1.1248 0.01248 0.00656 -0.0852 0.4251 1.0000
6.500 1.1390 0.01279 0.00681 -0.0829 0.4194 1.0000
6.750 1.1563 0.01300 0.00707 -0.0813 0.4133 1.0000
7.000 1.1714 0.01330 0.00736 -0.0793 0.4073 1.0000
7.250 1.1862 0.01362 0.00767 -0.0773 0.3999 1.0000
7.500 1.2008 0.01397 0.00801 -0.0754 0.3928 1.0000
7.750 1.2152 0.01436 0.00839 -0.0734 0.3855 1.0000
8.000 1.2290 0.01478 0.00880 -0.0715 0.3772 1.0000
8.250 1.2427 0.01524 0.00924 -0.0696 0.3688 1.0000
8.500 1.2563 0.01573 0.00973 -0.0677 0.3613 1.0000
8.750 1.2705 0.01624 0.01024 -0.0660 0.3537 1.0000
9.000 1.2843 0.01679 0.01079 -0.0644 0.3467 1.0000
9.250 1.2973 0.01740 0.01140 -0.0627 0.3389 1.0000
9.500 1.3078 0.01815 0.01212 -0.0607 0.3294 1.0000
9.750 1.3213 0.01881 0.01280 -0.0592 0.3211 1.0000
10.000 1.3304 0.01970 0.01366 -0.0573 0.3129 1.0000
10.250 1.3433 0.02046 0.01444 -0.0559 0.3038 1.0000
10.500 1.3522 0.02146 0.01542 -0.0541 0.2941 1.0000
10.750 1.3589 0.02264 0.01657 -0.0523 0.2833 1.0000
11.000 1.3650 0.02391 0.01782 -0.0505 0.2697 1.0000
11.250 1.3685 0.02542 0.01928 -0.0486 0.2550 1.0000
11.500 1.3685 0.02725 0.02103 -0.0465 0.2384 1.0000
11.750 1.3685 0.02916 0.02288 -0.0446 0.2208 1.0000
12.000 1.3596 0.03183 0.02542 -0.0423 0.1973 1.0000
12.250 1.3484 0.03481 0.02826 -0.0400 0.1711 1.0000
12.500 1.3246 0.03899 0.03222 -0.0373 0.1346 1.0000
12.750 1.2996 0.04353 0.03658 -0.0350 0.1026 1.0000
13.000 1.2669 0.04908 0.04195 -0.0328 0.0625 1.0000
13.250 1.2429 0.05408 0.04688 -0.0314 0.0322 1.0000
13.500 1.2344 0.05770 0.05051 -0.0307 0.0229 1.0000
13.750 1.2332 0.06061 0.05349 -0.0302 0.0208 1.0000
14.000 1.2314 0.06365 0.05660 -0.0299 0.0193 1.0000
14.250 1.2308 0.06659 0.05964 -0.0297 0.0184 1.0000
14.500 1.2309 0.06951 0.06264 -0.0295 0.0180 1.0000
14.750 1.2296 0.07263 0.06586 -0.0294 0.0175 1.0000
15.000 1.2271 0.07594 0.06926 -0.0294 0.0169 1.0000
15.250 1.2220 0.07960 0.07302 -0.0295 0.0165 1.0000
15.500 1.2165 0.08337 0.07688 -0.0297 0.0162 1.0000
15.750 1.2089 0.08749 0.08111 -0.0299 0.0159 1.0000
16.000 1.1977 0.09217 0.08589 -0.0304 0.0155 1.0000
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