GOE 504 AIRFOIL (goe504-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 504 AIRFOIL (goe504-il) Reynolds number: 500,000 Max Cl/Cd: 85.1 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe504-il-500000-n5.txt Download as CSV file: xf-goe504-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.5164 0.09583 0.09308 -0.0809 0.9961 0.0126
-16.000 -0.5587 0.08344 0.08048 -0.0889 0.9934 0.0126
-15.750 -0.5719 0.07656 0.07350 -0.0942 0.9910 0.0127
-15.500 -0.5980 0.06817 0.06492 -0.1005 0.9879 0.0126
-15.250 -0.6008 0.06299 0.05967 -0.1055 0.9852 0.0129
-15.000 -0.6091 0.05738 0.05395 -0.1104 0.9814 0.0130
-14.750 -0.6138 0.05218 0.04864 -0.1153 0.9767 0.0131
-14.500 -0.6129 0.04719 0.04352 -0.1208 0.9732 0.0132
-14.250 -0.6085 0.04314 0.03937 -0.1252 0.9673 0.0134
-14.000 -0.5995 0.03894 0.03503 -0.1309 0.9625 0.0136
-13.750 -0.5844 0.03542 0.03137 -0.1366 0.9577 0.0138
-13.500 -0.5646 0.03282 0.02864 -0.1414 0.9512 0.0143
-13.250 -0.5419 0.03009 0.02573 -0.1470 0.9458 0.0147
-13.000 -0.5262 0.02790 0.02335 -0.1500 0.9353 0.0151
-12.750 -0.5086 0.02610 0.02134 -0.1522 0.9244 0.0157
-12.500 -0.4912 0.02486 0.01999 -0.1533 0.9114 0.0159
-12.250 -0.4743 0.02408 0.01912 -0.1534 0.8969 0.0162
-12.000 -0.4609 0.02337 0.01829 -0.1524 0.8811 0.0165
-11.750 -0.4499 0.02272 0.01750 -0.1507 0.8651 0.0168
-11.500 -0.4391 0.02220 0.01686 -0.1486 0.8496 0.0172
-11.250 -0.4315 0.02158 0.01608 -0.1459 0.8348 0.0175
-10.750 -0.4142 0.02059 0.01479 -0.1402 0.8087 0.0186
-10.500 -0.4012 0.02009 0.01412 -0.1380 0.7977 0.0191
-10.250 -0.3866 0.01967 0.01359 -0.1360 0.7877 0.0196
-10.000 -0.3716 0.01922 0.01306 -0.1342 0.7778 0.0199
-9.750 -0.3548 0.01886 0.01262 -0.1325 0.7687 0.0203
-9.500 -0.3372 0.01850 0.01218 -0.1310 0.7600 0.0208
-9.250 -0.3193 0.01810 0.01169 -0.1295 0.7521 0.0213
-9.000 -0.3005 0.01775 0.01124 -0.1281 0.7440 0.0220
-8.750 -0.2815 0.01736 0.01074 -0.1267 0.7367 0.0226
-8.500 -0.2613 0.01705 0.01031 -0.1254 0.7292 0.0232
-8.250 -0.2407 0.01676 0.00991 -0.1242 0.7227 0.0237
-8.000 -0.2234 0.01616 0.00927 -0.1226 0.7155 0.0243
-7.500 -0.1831 0.01543 0.00845 -0.1201 0.7024 0.0255
-7.250 -0.1620 0.01513 0.00807 -0.1190 0.6960 0.0263
-7.000 -0.1407 0.01482 0.00769 -0.1179 0.6899 0.0269
-6.750 -0.1193 0.01450 0.00731 -0.1168 0.6833 0.0274
-6.500 -0.0971 0.01429 0.00701 -0.1158 0.6772 0.0281
-6.250 -0.0741 0.01405 0.00671 -0.1149 0.6713 0.0285
-6.000 -0.0541 0.01364 0.00624 -0.1135 0.6647 0.0292
-5.750 -0.0333 0.01329 0.00583 -0.1123 0.6589 0.0298
-5.500 -0.0109 0.01300 0.00550 -0.1113 0.6527 0.0305
-5.250 0.0116 0.01277 0.00521 -0.1104 0.6466 0.0312
-5.000 0.0348 0.01256 0.00495 -0.1095 0.6407 0.0320
-4.750 0.0581 0.01237 0.00471 -0.1087 0.6342 0.0327
-4.500 0.0814 0.01223 0.00449 -0.1078 0.6282 0.0333
-4.250 0.1055 0.01207 0.00428 -0.1071 0.6220 0.0338
-4.000 0.1291 0.01196 0.00410 -0.1062 0.6155 0.0344
-3.750 0.1529 0.01182 0.00391 -0.1055 0.6096 0.0353
-3.500 0.1766 0.01168 0.00372 -0.1047 0.6032 0.0370
-3.000 0.2241 0.01149 0.00345 -0.1031 0.5908 0.0407
-2.750 0.2472 0.01138 0.00332 -0.1022 0.5845 0.0470
-2.500 0.2688 0.01113 0.00319 -0.1011 0.5786 0.0898
-2.000 0.3098 0.01055 0.00299 -0.0985 0.5663 0.2119
-1.750 0.3336 0.01050 0.00297 -0.0978 0.5603 0.2290
-1.500 0.3569 0.01048 0.00296 -0.0969 0.5540 0.2452
-1.250 0.3799 0.01049 0.00296 -0.0960 0.5484 0.2594
-1.000 0.4037 0.01047 0.00296 -0.0953 0.5426 0.2729
-0.750 0.4264 0.01047 0.00296 -0.0943 0.5367 0.2846
-0.250 0.4725 0.01051 0.00297 -0.0925 0.5254 0.3021
0.000 0.4944 0.01053 0.00299 -0.0914 0.5198 0.3135
0.250 0.5163 0.01055 0.00301 -0.0903 0.5143 0.3262
0.500 0.5373 0.01052 0.00304 -0.0890 0.5089 0.3457
0.750 0.5563 0.01051 0.00307 -0.0873 0.5035 0.3683
1.000 0.5767 0.01048 0.00311 -0.0859 0.4987 0.3933
1.250 0.5970 0.01046 0.00316 -0.0845 0.4931 0.4182
1.500 0.6158 0.01047 0.00322 -0.0828 0.4879 0.4493
1.750 0.6349 0.01043 0.00331 -0.0812 0.4830 0.4937
2.000 0.6533 0.01037 0.00341 -0.0795 0.4775 0.5514
2.250 0.6684 0.01029 0.00354 -0.0770 0.4722 0.6260
2.500 0.6821 0.01016 0.00369 -0.0742 0.4675 0.7180
2.750 0.6969 0.00999 0.00387 -0.0715 0.4616 0.8263
3.000 0.7827 0.01022 0.00427 -0.0843 0.4535 0.9370
3.250 0.8466 0.01048 0.00450 -0.0924 0.4452 0.9626
3.500 0.8847 0.01074 0.00470 -0.0950 0.4390 0.9793
3.750 0.9187 0.01093 0.00487 -0.0967 0.4326 0.9904
4.000 0.9496 0.01119 0.00509 -0.0978 0.4262 0.9996
4.250 0.9653 0.01137 0.00523 -0.0956 0.4210 1.0000
4.500 0.9803 0.01152 0.00537 -0.0933 0.4154 1.0000
4.750 0.9933 0.01173 0.00554 -0.0907 0.4091 1.0000
5.000 1.0093 0.01192 0.00572 -0.0887 0.4041 1.0000
5.250 1.0256 0.01213 0.00591 -0.0867 0.3984 1.0000
5.500 1.0405 0.01239 0.00614 -0.0846 0.3930 1.0000
5.750 1.0577 0.01262 0.00637 -0.0829 0.3879 1.0000
6.000 1.0746 0.01287 0.00662 -0.0811 0.3823 1.0000
6.250 1.0895 0.01320 0.00692 -0.0791 0.3769 1.0000
6.500 1.1073 0.01347 0.00719 -0.0777 0.3715 1.0000
6.750 1.1232 0.01381 0.00752 -0.0759 0.3649 1.0000
7.000 1.1385 0.01419 0.00789 -0.0742 0.3592 1.0000
7.250 1.1550 0.01455 0.00825 -0.0726 0.3521 1.0000
7.500 1.1678 0.01507 0.00872 -0.0706 0.3433 1.0000
7.750 1.1834 0.01551 0.00916 -0.0690 0.3358 1.0000
8.000 1.1966 0.01607 0.00969 -0.0672 0.3283 1.0000
8.250 1.2110 0.01660 0.01022 -0.0656 0.3198 1.0000
8.500 1.2227 0.01729 0.01087 -0.0637 0.3097 1.0000
8.750 1.2340 0.01803 0.01158 -0.0618 0.3009 1.0000
9.000 1.2468 0.01873 0.01227 -0.0602 0.2911 1.0000
9.250 1.2569 0.01960 0.01311 -0.0584 0.2808 1.0000
9.500 1.2662 0.02056 0.01403 -0.0566 0.2707 1.0000
9.750 1.2771 0.02148 0.01494 -0.0551 0.2606 1.0000
10.000 1.2857 0.02256 0.01600 -0.0534 0.2504 1.0000
10.250 1.2914 0.02388 0.01726 -0.0515 0.2371 1.0000
10.500 1.2965 0.02529 0.01863 -0.0497 0.2244 1.0000
10.750 1.2985 0.02698 0.02025 -0.0478 0.2085 1.0000
11.000 1.2982 0.02890 0.02210 -0.0458 0.1903 1.0000
11.250 1.2902 0.03149 0.02456 -0.0435 0.1656 1.0000
11.500 1.2640 0.03565 0.02846 -0.0402 0.1230 1.0000
11.750 1.2343 0.04043 0.03302 -0.0372 0.0814 1.0000
12.000 1.2148 0.04459 0.03707 -0.0352 0.0487 1.0000
12.250 1.1974 0.04879 0.04123 -0.0337 0.0193 1.0000
12.500 1.1998 0.05116 0.04364 -0.0331 0.0163 1.0000
12.750 1.2028 0.05351 0.04606 -0.0326 0.0148 1.0000
13.000 1.2057 0.05592 0.04854 -0.0321 0.0138 1.0000
13.250 1.2097 0.05826 0.05095 -0.0318 0.0130 1.0000
13.500 1.2128 0.06073 0.05349 -0.0315 0.0124 1.0000
13.750 1.2157 0.06323 0.05607 -0.0313 0.0121 1.0000
14.000 1.2159 0.06607 0.05900 -0.0310 0.0115 1.0000
14.250 1.2157 0.06902 0.06203 -0.0309 0.0111 1.0000
14.500 1.2132 0.07229 0.06538 -0.0308 0.0107 1.0000
14.750 1.2142 0.07517 0.06834 -0.0308 0.0104 1.0000
15.000 1.2141 0.07819 0.07145 -0.0309 0.0103 1.0000
15.250 1.2126 0.08144 0.07479 -0.0310 0.0099 1.0000
15.500 1.2112 0.08471 0.07814 -0.0312 0.0098 1.0000
15.750 1.2090 0.08813 0.08164 -0.0314 0.0095 1.0000
16.000 1.2063 0.09166 0.08525 -0.0318 0.0090 1.0000
16.250 1.2031 0.09524 0.08892 -0.0322 0.0089 1.0000
16.500 1.1983 0.09911 0.09286 -0.0327 0.0086 1.0000
16.750 1.1928 0.10313 0.09697 -0.0333 0.0085 1.0000
17.000 1.1856 0.10743 0.10136 -0.0340 0.0083 1.0000
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Polar data table (+)
Polar graphs
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