GOE 504 AIRFOIL (goe504-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 504 AIRFOIL (goe504-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.1 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe504-il-1000000-n5.txt Download as CSV file: xf-goe504-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.6200 0.11268 0.11040 -0.0710 0.9999 0.0086
-18.250 -0.6538 0.10213 0.09970 -0.0774 0.9995 0.0088
-18.000 -0.6806 0.09303 0.09046 -0.0833 0.9990 0.0087
-17.750 -0.6979 0.08563 0.08297 -0.0885 0.9983 0.0088
-17.500 -0.7136 0.07868 0.07590 -0.0936 0.9972 0.0088
-17.250 -0.7335 0.07163 0.06874 -0.0986 0.9939 0.0089
-17.000 -0.7543 0.06497 0.06197 -0.1033 0.9916 0.0089
-16.750 -0.7711 0.05880 0.05570 -0.1080 0.9888 0.0090
-16.500 -0.7856 0.05264 0.04942 -0.1132 0.9857 0.0091
-16.250 -0.8012 0.04636 0.04301 -0.1185 0.9817 0.0091
-16.000 -0.8084 0.04088 0.03740 -0.1235 0.9767 0.0092
-15.750 -0.8049 0.03592 0.03230 -0.1295 0.9732 0.0094
-15.500 -0.7998 0.03161 0.02784 -0.1350 0.9673 0.0093
-15.250 -0.7841 0.02839 0.02448 -0.1403 0.9622 0.0096
-15.000 -0.7625 0.02597 0.02193 -0.1451 0.9575 0.0098
-14.750 -0.7381 0.02398 0.01986 -0.1494 0.9511 0.0103
-14.500 -0.7086 0.02243 0.01821 -0.1535 0.9449 0.0106
-14.250 -0.6865 0.02131 0.01700 -0.1552 0.9339 0.0109
-14.000 -0.6667 0.02040 0.01599 -0.1559 0.9220 0.0113
-13.750 -0.6515 0.01961 0.01509 -0.1554 0.9073 0.0116
-13.500 -0.6396 0.01897 0.01434 -0.1538 0.8909 0.0120
-13.250 -0.6315 0.01839 0.01361 -0.1513 0.8714 0.0122
-13.000 -0.6247 0.01788 0.01296 -0.1482 0.8530 0.0124
-12.750 -0.6171 0.01746 0.01243 -0.1451 0.8362 0.0127
-12.500 -0.6086 0.01711 0.01199 -0.1420 0.8205 0.0130
-12.250 -0.5974 0.01686 0.01166 -0.1392 0.8073 0.0134
-12.000 -0.5829 0.01657 0.01129 -0.1371 0.7952 0.0138
-11.750 -0.5668 0.01630 0.01094 -0.1352 0.7841 0.0142
-11.250 -0.5323 0.01572 0.01021 -0.1318 0.7643 0.0151
-11.000 -0.5143 0.01545 0.00984 -0.1302 0.7555 0.0155
-10.750 -0.4956 0.01514 0.00947 -0.1287 0.7466 0.0160
-10.500 -0.4749 0.01494 0.00923 -0.1275 0.7389 0.0164
-10.250 -0.4528 0.01477 0.00902 -0.1266 0.7313 0.0169
-10.000 -0.4317 0.01457 0.00876 -0.1254 0.7242 0.0173
-9.750 -0.4099 0.01434 0.00849 -0.1244 0.7168 0.0178
-9.500 -0.3881 0.01416 0.00823 -0.1234 0.7100 0.0183
-9.250 -0.3658 0.01393 0.00795 -0.1225 0.7041 0.0188
-9.000 -0.3438 0.01371 0.00766 -0.1215 0.6971 0.0191
-8.750 -0.3221 0.01347 0.00736 -0.1204 0.6910 0.0195
-8.500 -0.3002 0.01319 0.00704 -0.1195 0.6850 0.0200
-8.250 -0.2775 0.01300 0.00680 -0.1185 0.6786 0.0204
-8.000 -0.2540 0.01281 0.00658 -0.1178 0.6730 0.0208
-7.750 -0.2300 0.01266 0.00639 -0.1171 0.6666 0.0214
-7.500 -0.2073 0.01248 0.00615 -0.1162 0.6605 0.0219
-7.250 -0.1833 0.01228 0.00591 -0.1155 0.6548 0.0224
-7.000 -0.1597 0.01212 0.00569 -0.1147 0.6483 0.0229
-6.750 -0.1359 0.01196 0.00548 -0.1140 0.6424 0.0233
-6.500 -0.1112 0.01183 0.00531 -0.1134 0.6366 0.0235
-6.250 -0.0896 0.01153 0.00494 -0.1123 0.6304 0.0240
-6.000 -0.0667 0.01127 0.00465 -0.1114 0.6247 0.0246
-5.750 -0.0429 0.01109 0.00443 -0.1106 0.6180 0.0252
-5.500 -0.0194 0.01095 0.00423 -0.1098 0.6119 0.0257
-5.250 0.0052 0.01079 0.00404 -0.1092 0.6058 0.0261
-5.000 0.0290 0.01066 0.00386 -0.1084 0.5990 0.0266
-4.750 0.0533 0.01053 0.00369 -0.1077 0.5930 0.0271
-4.500 0.0779 0.01042 0.00354 -0.1071 0.5866 0.0276
-4.250 0.1017 0.01033 0.00339 -0.1063 0.5802 0.0280
-4.000 0.1267 0.01022 0.00325 -0.1057 0.5741 0.0283
-3.750 0.1507 0.01015 0.00313 -0.1050 0.5673 0.0286
-3.500 0.1750 0.01004 0.00298 -0.1043 0.5617 0.0292
-3.250 0.1993 0.00994 0.00285 -0.1036 0.5552 0.0299
-3.000 0.2229 0.00988 0.00274 -0.1028 0.5490 0.0308
-2.750 0.2478 0.00981 0.00265 -0.1022 0.5431 0.0318
-2.500 0.2718 0.00977 0.00257 -0.1014 0.5366 0.0328
-2.250 0.2960 0.00974 0.00250 -0.1007 0.5311 0.0338
-2.000 0.3206 0.00970 0.00244 -0.1001 0.5250 0.0354
-1.750 0.3441 0.00967 0.00239 -0.0992 0.5194 0.0390
-1.500 0.3659 0.00946 0.00231 -0.0982 0.5142 0.0829
-1.250 0.3888 0.00934 0.00225 -0.0972 0.5085 0.1080
-1.000 0.4065 0.00900 0.00217 -0.0954 0.5026 0.1992
-0.750 0.4299 0.00894 0.00217 -0.0946 0.4981 0.2230
-0.500 0.4530 0.00890 0.00218 -0.0937 0.4932 0.2433
-0.250 0.4744 0.00891 0.00220 -0.0924 0.4878 0.2568
0.000 0.4963 0.00891 0.00221 -0.0913 0.4827 0.2659
0.250 0.5187 0.00892 0.00222 -0.0902 0.4778 0.2746
0.500 0.5398 0.00895 0.00225 -0.0889 0.4724 0.2851
0.750 0.5619 0.00898 0.00228 -0.0878 0.4679 0.2943
1.000 0.5840 0.00900 0.00232 -0.0867 0.4619 0.3027
1.250 0.6049 0.00906 0.00237 -0.0855 0.4564 0.3127
1.500 0.6260 0.00907 0.00244 -0.0842 0.4512 0.3378
1.750 0.6476 0.00910 0.00252 -0.0831 0.4455 0.3582
2.000 0.6670 0.00917 0.00262 -0.0815 0.4390 0.3814
2.250 0.6887 0.00920 0.00271 -0.0805 0.4341 0.4039
2.500 0.7093 0.00924 0.00281 -0.0792 0.4283 0.4326
2.750 0.7281 0.00929 0.00293 -0.0776 0.4225 0.4709
3.000 0.7477 0.00928 0.00305 -0.0761 0.4167 0.5218
3.250 0.7655 0.00928 0.00319 -0.0743 0.4111 0.5803
3.500 0.7806 0.00922 0.00335 -0.0719 0.4056 0.6632
3.750 0.7943 0.00912 0.00350 -0.0692 0.4009 0.7532
4.000 0.8058 0.00906 0.00369 -0.0659 0.3946 0.8403
4.250 0.9131 0.00920 0.00405 -0.0837 0.3853 0.9536
4.500 0.9771 0.00950 0.00430 -0.0921 0.3773 0.9768
4.750 1.0098 0.00970 0.00448 -0.0935 0.3718 0.9880
5.000 1.0348 0.00998 0.00472 -0.0934 0.3650 0.9989
5.250 1.0597 0.01021 0.00492 -0.0933 0.3594 1.0000
5.500 1.0759 0.01040 0.00510 -0.0913 0.3532 1.0000
5.750 1.0916 0.01064 0.00531 -0.0892 0.3475 1.0000
6.000 1.1090 0.01086 0.00552 -0.0875 0.3429 1.0000
6.250 1.1260 0.01111 0.00575 -0.0858 0.3364 1.0000
6.500 1.1414 0.01144 0.00604 -0.0838 0.3285 1.0000
6.750 1.1552 0.01184 0.00639 -0.0817 0.3169 1.0000
7.000 1.1731 0.01213 0.00667 -0.0803 0.3121 1.0000
7.250 1.1879 0.01255 0.00705 -0.0784 0.3022 1.0000
7.500 1.2041 0.01295 0.00742 -0.0768 0.2944 1.0000
7.750 1.2173 0.01348 0.00789 -0.0748 0.2832 1.0000
8.000 1.2291 0.01409 0.00844 -0.0727 0.2702 1.0000
8.250 1.2458 0.01453 0.00887 -0.0713 0.2635 1.0000
8.500 1.2582 0.01517 0.00947 -0.0695 0.2533 1.0000
8.750 1.2703 0.01586 0.01011 -0.0676 0.2421 1.0000
9.000 1.2806 0.01667 0.01086 -0.0656 0.2290 1.0000
9.250 1.2882 0.01766 0.01177 -0.0634 0.2139 1.0000
9.500 1.2965 0.01866 0.01270 -0.0613 0.2006 1.0000
9.750 1.2979 0.02009 0.01403 -0.0586 0.1810 1.0000
10.000 1.2865 0.02239 0.01613 -0.0548 0.1461 1.0000
10.250 1.2597 0.02592 0.01939 -0.0499 0.0991 1.0000
10.500 1.2326 0.02983 0.02310 -0.0458 0.0510 1.0000
10.750 1.2195 0.03298 0.02616 -0.0431 0.0169 1.0000
11.000 1.2272 0.03455 0.02776 -0.0422 0.0140 1.0000
11.250 1.2365 0.03602 0.02926 -0.0414 0.0127 1.0000
11.500 1.2447 0.03762 0.03090 -0.0406 0.0118 1.0000
11.750 1.2521 0.03932 0.03265 -0.0399 0.0110 1.0000
12.000 1.2599 0.04101 0.03437 -0.0392 0.0107 1.0000
12.250 1.2678 0.04272 0.03613 -0.0386 0.0101 1.0000
12.500 1.2748 0.04455 0.03800 -0.0380 0.0097 1.0000
12.750 1.2809 0.04648 0.03998 -0.0374 0.0092 1.0000
13.000 1.2857 0.04858 0.04212 -0.0369 0.0087 1.0000
13.250 1.2890 0.05087 0.04447 -0.0363 0.0083 1.0000
13.500 1.2932 0.05309 0.04674 -0.0359 0.0081 1.0000
13.750 1.2989 0.05519 0.04889 -0.0355 0.0078 1.0000
14.000 1.3025 0.05754 0.05130 -0.0352 0.0075 1.0000
14.250 1.3053 0.06002 0.05383 -0.0349 0.0074 1.0000
14.500 1.3081 0.06251 0.05638 -0.0347 0.0071 1.0000
14.750 1.3095 0.06519 0.05913 -0.0345 0.0069 1.0000
15.000 1.3111 0.06788 0.06187 -0.0343 0.0068 1.0000
15.250 1.3116 0.07073 0.06477 -0.0343 0.0065 1.0000
15.500 1.3111 0.07375 0.06786 -0.0342 0.0064 1.0000
15.750 1.3089 0.07699 0.07117 -0.0343 0.0063 1.0000
16.000 1.3074 0.08016 0.07441 -0.0343 0.0060 1.0000
16.250 1.3061 0.08336 0.07768 -0.0345 0.0060 1.0000
16.500 1.3045 0.08665 0.08103 -0.0347 0.0058 1.0000
16.750 1.3021 0.09006 0.08452 -0.0350 0.0058 1.0000
17.000 1.2990 0.09357 0.08811 -0.0354 0.0056 1.0000
17.250 1.2962 0.09708 0.09169 -0.0358 0.0055 1.0000
17.500 1.2940 0.10051 0.09518 -0.0363 0.0053 1.0000
17.750 1.2905 0.10419 0.09893 -0.0369 0.0053 1.0000
18.000 1.2877 0.10780 0.10261 -0.0375 0.0051 1.0000
18.250 1.2842 0.11152 0.10639 -0.0383 0.0050 1.0000
18.500 1.2802 0.11532 0.11026 -0.0391 0.0049 1.0000
18.750 1.2752 0.11928 0.11429 -0.0400 0.0049 1.0000
19.000 1.2735 0.12279 0.11786 -0.0409 0.0048 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 504 AIRFOIL (goe504-il)