GOE 503 AIRFOIL (goe503-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 503 AIRFOIL (goe503-il) Reynolds number: 500,000 Max Cl/Cd: 96.38 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe503-il-500000.txt Download as CSV file: xf-goe503-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 503 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 -0.4052 0.06808 0.06539 -0.1056 0.9790 0.0175
-12.750 -0.4432 0.05597 0.05312 -0.1183 0.9733 0.0174
-12.500 -0.4883 0.04280 0.03974 -0.1345 0.9619 0.0171
-12.250 -0.4879 0.03410 0.03064 -0.1442 0.9576 0.0172
-12.000 -0.4900 0.03102 0.02730 -0.1434 0.9474 0.0173
-11.750 -0.4672 0.02836 0.02434 -0.1461 0.9441 0.0175
-11.500 -0.4629 0.02587 0.02164 -0.1446 0.9345 0.0178
-11.250 -0.4403 0.02381 0.01941 -0.1458 0.9294 0.0182
-11.000 -0.4239 0.02256 0.01805 -0.1448 0.9196 0.0186
-10.750 -0.3952 0.02126 0.01661 -0.1461 0.9133 0.0190
-10.500 -0.3770 0.02030 0.01551 -0.1449 0.9015 0.0196
-10.250 -0.3543 0.01933 0.01437 -0.1446 0.8903 0.0203
-10.000 -0.3290 0.01848 0.01332 -0.1446 0.8792 0.0209
-9.750 -0.3106 0.01748 0.01218 -0.1433 0.8655 0.0218
-9.500 -0.2912 0.01680 0.01139 -0.1419 0.8510 0.0227
-9.250 -0.2703 0.01626 0.01070 -0.1407 0.8366 0.0237
-9.000 -0.2495 0.01574 0.01002 -0.1394 0.8226 0.0247
-8.750 -0.2305 0.01512 0.00926 -0.1379 0.8098 0.0261
-8.500 -0.2087 0.01469 0.00872 -0.1367 0.7986 0.0277
-8.250 -0.1871 0.01428 0.00818 -0.1355 0.7878 0.0301
-8.000 -0.1653 0.01391 0.00775 -0.1343 0.7779 0.0332
-7.750 -0.1416 0.01363 0.00739 -0.1335 0.7688 0.0382
-7.500 -0.1184 0.01343 0.00715 -0.1325 0.7600 0.0442
-7.250 -0.0930 0.01333 0.00693 -0.1320 0.7523 0.0498
-7.000 -0.0694 0.01321 0.00678 -0.1311 0.7445 0.0539
-6.750 -0.0441 0.01313 0.00655 -0.1305 0.7373 0.0572
-6.500 -0.0219 0.01286 0.00629 -0.1294 0.7299 0.0607
-6.250 0.0029 0.01280 0.00613 -0.1287 0.7227 0.0640
-6.000 0.0275 0.01270 0.00594 -0.1280 0.7161 0.0664
-5.750 0.0500 0.01241 0.00564 -0.1269 0.7092 0.0700
-5.500 0.0754 0.01234 0.00548 -0.1263 0.7028 0.0731
-5.250 0.0989 0.01224 0.00533 -0.1253 0.6958 0.0760
-5.000 0.1224 0.01203 0.00508 -0.1244 0.6891 0.0802
-4.750 0.1465 0.01194 0.00498 -0.1236 0.6826 0.0841
-4.500 0.1705 0.01189 0.00485 -0.1227 0.6756 0.0879
-4.250 0.1941 0.01167 0.00458 -0.1218 0.6692 0.0924
-4.000 0.2168 0.01153 0.00446 -0.1206 0.6621 0.0976
-3.750 0.2407 0.01144 0.00428 -0.1197 0.6555 0.1027
-3.500 0.2632 0.01125 0.00412 -0.1186 0.6487 0.1107
-3.250 0.2860 0.01115 0.00396 -0.1174 0.6416 0.1181
-3.000 0.3092 0.01106 0.00386 -0.1164 0.6351 0.1270
-2.750 0.3316 0.01096 0.00377 -0.1153 0.6280 0.1352
-2.500 0.3550 0.01095 0.00370 -0.1143 0.6215 0.1437
-2.250 0.3773 0.01087 0.00364 -0.1131 0.6146 0.1521
-2.000 0.4003 0.01087 0.00359 -0.1120 0.6080 0.1605
-1.750 0.4230 0.01083 0.00357 -0.1109 0.6018 0.1698
-1.500 0.4455 0.01083 0.00353 -0.1098 0.5951 0.1789
-1.250 0.4685 0.01085 0.00353 -0.1088 0.5892 0.1893
-1.000 0.4907 0.01083 0.00352 -0.1076 0.5830 0.1989
-0.750 0.5132 0.01085 0.00351 -0.1064 0.5771 0.2082
-0.500 0.5361 0.01088 0.00351 -0.1054 0.5718 0.2177
-0.250 0.5585 0.01090 0.00353 -0.1043 0.5661 0.2272
0.000 0.5799 0.01090 0.00354 -0.1030 0.5606 0.2379
0.250 0.6033 0.01097 0.00356 -0.1021 0.5556 0.2469
0.500 0.6237 0.01094 0.00358 -0.1006 0.5506 0.2554
0.750 0.6445 0.01097 0.00358 -0.0991 0.5454 0.2635
1.000 0.6671 0.01103 0.00361 -0.0981 0.5408 0.2735
1.250 0.6868 0.01102 0.00365 -0.0965 0.5364 0.2835
1.750 0.7278 0.01107 0.00373 -0.0936 0.5271 0.3129
2.000 0.7492 0.01110 0.00382 -0.0923 0.5227 0.3347
2.250 0.7676 0.01108 0.00390 -0.0905 0.5183 0.3650
2.500 0.7856 0.01102 0.00398 -0.0886 0.5140 0.4167
2.750 0.9118 0.01064 0.00490 -0.1102 0.5071 0.9731
3.000 0.9653 0.01093 0.00518 -0.1159 0.5018 0.9856
3.250 1.0149 0.01118 0.00537 -0.1208 0.4966 0.9925
3.500 1.0637 0.01143 0.00553 -0.1256 0.4913 0.9968
3.750 1.1063 0.01153 0.00565 -0.1291 0.4864 1.0000
4.000 1.1176 0.01161 0.00572 -0.1259 0.4821 1.0000
4.250 1.1283 0.01173 0.00580 -0.1226 0.4781 1.0000
4.500 1.1379 0.01183 0.00589 -0.1190 0.4736 1.0000
4.750 1.1460 0.01189 0.00597 -0.1151 0.4687 1.0000
5.000 1.1554 0.01200 0.00605 -0.1115 0.4637 1.0000
5.250 1.1672 0.01216 0.00618 -0.1084 0.4585 1.0000
5.500 1.1784 0.01226 0.00631 -0.1053 0.4534 1.0000
5.750 1.1904 0.01241 0.00645 -0.1023 0.4480 1.0000
6.000 1.2040 0.01263 0.00662 -0.0997 0.4431 1.0000
6.250 1.2181 0.01277 0.00680 -0.0973 0.4380 1.0000
6.500 1.2328 0.01296 0.00700 -0.0950 0.4331 1.0000
6.750 1.2466 0.01324 0.00722 -0.0926 0.4281 1.0000
7.000 1.2628 0.01342 0.00746 -0.0906 0.4234 1.0000
7.250 1.2783 0.01366 0.00771 -0.0886 0.4183 1.0000
7.500 1.2925 0.01397 0.00800 -0.0864 0.4134 1.0000
7.750 1.3090 0.01423 0.00829 -0.0846 0.4085 1.0000
8.000 1.3247 0.01452 0.00861 -0.0828 0.4031 1.0000
8.250 1.3382 0.01491 0.00896 -0.0806 0.3977 1.0000
8.500 1.3537 0.01524 0.00934 -0.0788 0.3914 1.0000
8.750 1.3656 0.01569 0.00977 -0.0765 0.3838 1.0000
9.000 1.3792 0.01613 0.01023 -0.0746 0.3766 1.0000
9.250 1.3925 0.01661 0.01072 -0.0727 0.3701 1.0000
9.500 1.4044 0.01717 0.01128 -0.0706 0.3625 1.0000
9.750 1.4162 0.01776 0.01188 -0.0686 0.3543 1.0000
10.000 1.4276 0.01842 0.01254 -0.0666 0.3469 1.0000
10.250 1.4393 0.01909 0.01323 -0.0648 0.3393 1.0000
10.500 1.4498 0.01986 0.01400 -0.0629 0.3323 1.0000
10.750 1.4609 0.02063 0.01480 -0.0611 0.3245 1.0000
11.000 1.4697 0.02156 0.01574 -0.0592 0.3163 1.0000
11.250 1.4783 0.02256 0.01674 -0.0573 0.3078 1.0000
11.500 1.4862 0.02364 0.01783 -0.0555 0.2986 1.0000
11.750 1.4899 0.02504 0.01921 -0.0534 0.2884 1.0000
12.000 1.4966 0.02631 0.02050 -0.0518 0.2782 1.0000
12.250 1.5014 0.02777 0.02196 -0.0501 0.2679 1.0000
12.500 1.5027 0.02955 0.02373 -0.0482 0.2563 1.0000
12.750 1.5016 0.03159 0.02574 -0.0463 0.2439 1.0000
13.000 1.4996 0.03377 0.02790 -0.0445 0.2306 1.0000
13.250 1.4925 0.03645 0.03053 -0.0425 0.2141 1.0000
13.500 1.4844 0.03933 0.03335 -0.0407 0.1981 1.0000
13.750 1.4761 0.04230 0.03628 -0.0390 0.1843 1.0000
14.000 1.4637 0.04576 0.03968 -0.0374 0.1680 1.0000
14.250 1.4532 0.04918 0.04306 -0.0360 0.1541 1.0000
14.500 1.4371 0.05325 0.04706 -0.0347 0.1364 1.0000
14.750 1.4157 0.05803 0.05172 -0.0334 0.1117 1.0000
15.000 1.3810 0.06441 0.05792 -0.0321 0.0775 1.0000
15.250 1.3585 0.06967 0.06312 -0.0314 0.0581 1.0000
15.500 1.3314 0.07566 0.06906 -0.0309 0.0356 1.0000
15.750 1.3147 0.08059 0.07396 -0.0307 0.0239 1.0000
16.000 1.3073 0.08446 0.07788 -0.0307 0.0213 1.0000
16.250 1.3006 0.08837 0.08186 -0.0308 0.0195 1.0000
16.500 1.2969 0.09189 0.08548 -0.0310 0.0186 1.0000
16.750 1.2926 0.09551 0.08919 -0.0312 0.0180 1.0000
17.000 1.2857 0.09955 0.09332 -0.0316 0.0172 1.0000
17.250 1.2787 0.10366 0.09752 -0.0321 0.0168 1.0000
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