GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 621 AIRFOIL (goe621-il) Reynolds number: 500,000 Max Cl/Cd: 105.51 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe621-il-500000.txt Download as CSV file: xf-goe621-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 621 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5154 0.03832 0.03488 -0.1342 0.9719 0.0376
-11.500 -0.5184 0.03413 0.03032 -0.1380 0.9639 0.0379
-11.250 -0.5117 0.03118 0.02705 -0.1392 0.9566 0.0381
-11.000 -0.5059 0.02928 0.02489 -0.1380 0.9479 0.0383
-10.750 -0.4944 0.02771 0.02305 -0.1370 0.9406 0.0385
-10.500 -0.4853 0.02666 0.02178 -0.1347 0.9318 0.0387
-10.250 -0.4738 0.02471 0.01961 -0.1332 0.9249 0.0390
-10.000 -0.4600 0.02324 0.01803 -0.1315 0.9172 0.0394
-9.750 -0.4416 0.02216 0.01688 -0.1303 0.9103 0.0397
-9.500 -0.4220 0.02131 0.01595 -0.1292 0.9037 0.0402
-9.250 -0.4025 0.02058 0.01514 -0.1279 0.8954 0.0406
-9.000 -0.3802 0.01990 0.01436 -0.1270 0.8891 0.0412
-8.750 -0.3601 0.01921 0.01358 -0.1257 0.8799 0.0418
-8.500 -0.3372 0.01845 0.01269 -0.1249 0.8729 0.0423
-8.250 -0.3158 0.01779 0.01193 -0.1238 0.8633 0.0428
-8.000 -0.2920 0.01715 0.01115 -0.1230 0.8557 0.0433
-7.750 -0.2691 0.01662 0.01052 -0.1220 0.8454 0.0437
-7.500 -0.2443 0.01618 0.00993 -0.1213 0.8371 0.0441
-7.250 -0.2232 0.01518 0.00890 -0.1203 0.8267 0.0449
-7.000 -0.1992 0.01464 0.00831 -0.1195 0.8183 0.0457
-6.750 -0.1750 0.01423 0.00786 -0.1188 0.8089 0.0465
-6.500 -0.1499 0.01388 0.00744 -0.1181 0.8008 0.0476
-6.250 -0.1251 0.01356 0.00704 -0.1175 0.7920 0.0486
-6.000 -0.0996 0.01326 0.00664 -0.1169 0.7844 0.0496
-5.750 -0.0752 0.01285 0.00617 -0.1161 0.7764 0.0505
-5.500 -0.0509 0.01241 0.00569 -0.1154 0.7698 0.0520
-5.250 -0.0256 0.01213 0.00539 -0.1148 0.7631 0.0535
-5.000 0.0001 0.01189 0.00510 -0.1143 0.7565 0.0553
-4.750 0.0264 0.01168 0.00479 -0.1138 0.7506 0.0572
-4.500 0.0512 0.01134 0.00448 -0.1132 0.7443 0.0603
-4.250 0.0775 0.01116 0.00425 -0.1127 0.7379 0.0638
-4.000 0.1033 0.01092 0.00398 -0.1122 0.7316 0.0693
-3.750 0.1290 0.01068 0.00379 -0.1116 0.7250 0.0779
-3.500 0.1553 0.01049 0.00363 -0.1112 0.7192 0.0944
-3.250 0.1821 0.01035 0.00352 -0.1108 0.7139 0.1129
-3.000 0.2083 0.01020 0.00342 -0.1104 0.7080 0.1275
-2.750 0.2349 0.01007 0.00331 -0.1100 0.7024 0.1414
-2.500 0.2622 0.01000 0.00322 -0.1098 0.6973 0.1565
-2.250 0.2882 0.00985 0.00316 -0.1093 0.6921 0.1755
-2.000 0.3143 0.00970 0.00309 -0.1088 0.6863 0.2020
-1.750 0.3410 0.00961 0.00304 -0.1085 0.6806 0.2342
-1.500 0.3672 0.00951 0.00304 -0.1080 0.6750 0.2645
-1.250 0.3935 0.00943 0.00303 -0.1076 0.6696 0.2917
-1.000 0.4205 0.00939 0.00303 -0.1073 0.6648 0.3182
-0.750 0.4475 0.00939 0.00304 -0.1069 0.6599 0.3417
-0.500 0.4737 0.00933 0.00306 -0.1065 0.6545 0.3631
-0.250 0.5003 0.00930 0.00307 -0.1061 0.6495 0.3823
0.000 0.5275 0.00932 0.00307 -0.1058 0.6447 0.3994
0.250 0.5537 0.00930 0.00309 -0.1053 0.6394 0.4162
0.500 0.5797 0.00926 0.00310 -0.1048 0.6335 0.4336
0.750 0.6060 0.00926 0.00310 -0.1043 0.6277 0.4522
1.000 0.6318 0.00923 0.00313 -0.1037 0.6221 0.4726
1.250 0.6570 0.00917 0.00316 -0.1031 0.6159 0.4969
1.500 0.6819 0.00912 0.00317 -0.1024 0.6097 0.5319
1.750 0.7046 0.00894 0.00322 -0.1012 0.6027 0.5917
2.000 0.7882 0.00827 0.00345 -0.1128 0.5926 0.9761
2.250 0.8447 0.00837 0.00352 -0.1189 0.5821 1.0000
2.500 0.8666 0.00848 0.00354 -0.1176 0.5729 1.0000
2.750 0.8885 0.00856 0.00360 -0.1163 0.5619 1.0000
3.000 0.9097 0.00868 0.00366 -0.1148 0.5503 1.0000
3.250 0.9296 0.00882 0.00372 -0.1131 0.5357 1.0000
3.500 0.9485 0.00899 0.00381 -0.1112 0.5179 1.0000
3.750 0.9657 0.00920 0.00393 -0.1090 0.4958 1.0000
4.000 0.9789 0.00953 0.00409 -0.1061 0.4665 1.0000
4.250 0.9890 0.00996 0.00432 -0.1026 0.4332 1.0000
4.750 1.0096 0.01085 0.00488 -0.0958 0.3821 1.0000
5.000 1.0193 0.01122 0.00514 -0.0923 0.3667 1.0000
5.250 1.0310 0.01155 0.00539 -0.0892 0.3552 1.0000
5.500 1.0452 0.01185 0.00565 -0.0866 0.3458 1.0000
5.750 1.0585 0.01222 0.00595 -0.0840 0.3371 1.0000
6.000 1.0751 0.01251 0.00622 -0.0819 0.3299 1.0000
6.250 1.0908 0.01286 0.00653 -0.0798 0.3226 1.0000
6.500 1.1062 0.01324 0.00687 -0.0777 0.3165 1.0000
6.750 1.1248 0.01352 0.00716 -0.0761 0.3109 1.0000
7.000 1.1413 0.01390 0.00750 -0.0743 0.3053 1.0000
7.250 1.1566 0.01434 0.00790 -0.0723 0.2998 1.0000
7.500 1.1762 0.01462 0.00822 -0.0710 0.2951 1.0000
7.750 1.1935 0.01500 0.00859 -0.0694 0.2899 1.0000
8.000 1.2085 0.01550 0.00905 -0.0675 0.2846 1.0000
8.250 1.2270 0.01585 0.00944 -0.0662 0.2803 1.0000
8.500 1.2453 0.01623 0.00983 -0.0649 0.2752 1.0000
8.750 1.2606 0.01674 0.01032 -0.0632 0.2698 1.0000
9.000 1.2768 0.01724 0.01082 -0.0617 0.2648 1.0000
9.250 1.2951 0.01765 0.01127 -0.0605 0.2594 1.0000
9.500 1.3104 0.01821 0.01182 -0.0589 0.2541 1.0000
9.750 1.3251 0.01883 0.01243 -0.0574 0.2489 1.0000
10.000 1.3427 0.01930 0.01295 -0.0562 0.2436 1.0000
10.250 1.3572 0.01996 0.01360 -0.0547 0.2379 1.0000
10.500 1.3710 0.02068 0.01432 -0.0533 0.2325 1.0000
10.750 1.3874 0.02127 0.01495 -0.0521 0.2265 1.0000
11.000 1.3989 0.02216 0.01581 -0.0505 0.2201 1.0000
11.250 1.4139 0.02287 0.01656 -0.0493 0.2136 1.0000
11.500 1.4255 0.02381 0.01748 -0.0479 0.2064 1.0000
11.750 1.4378 0.02473 0.01841 -0.0466 0.2000 1.0000
12.000 1.4492 0.02575 0.01943 -0.0453 0.1927 1.0000
12.250 1.4591 0.02688 0.02056 -0.0439 0.1866 1.0000
12.500 1.4706 0.02795 0.02164 -0.0427 0.1800 1.0000
12.750 1.4775 0.02937 0.02302 -0.0413 0.1743 1.0000
13.000 1.4901 0.03041 0.02412 -0.0403 0.1694 1.0000
13.250 1.4992 0.03172 0.02545 -0.0392 0.1647 1.0000
13.500 1.5047 0.03336 0.02706 -0.0379 0.1599 1.0000
13.750 1.5170 0.03448 0.02826 -0.0370 0.1567 1.0000
14.000 1.5263 0.03585 0.02967 -0.0361 0.1527 1.0000
14.250 1.5324 0.03753 0.03135 -0.0351 0.1491 1.0000
14.500 1.5389 0.03919 0.03303 -0.0341 0.1458 1.0000
14.750 1.5499 0.04050 0.03442 -0.0334 0.1429 1.0000
15.000 1.5580 0.04207 0.03603 -0.0326 0.1398 1.0000
15.250 1.5636 0.04388 0.03788 -0.0318 0.1370 1.0000
15.500 1.5658 0.04603 0.04003 -0.0310 0.1338 1.0000
15.750 1.5755 0.04753 0.04162 -0.0304 0.1317 1.0000
16.000 1.5837 0.04919 0.04336 -0.0299 0.1294 1.0000
16.250 1.5897 0.05108 0.04530 -0.0294 0.1266 1.0000
16.500 1.5929 0.05327 0.04753 -0.0289 0.1242 1.0000
16.750 1.5923 0.05586 0.05013 -0.0283 0.1210 1.0000
17.000 1.6009 0.05760 0.05198 -0.0281 0.1187 1.0000
17.250 1.6065 0.05964 0.05410 -0.0278 0.1161 1.0000
17.500 1.6077 0.06220 0.05671 -0.0276 0.1130 1.0000
17.750 1.6048 0.06523 0.05976 -0.0274 0.1100 1.0000
18.000 1.6095 0.06747 0.06210 -0.0274 0.1069 1.0000
18.250 1.6111 0.07011 0.06482 -0.0274 0.1035 1.0000
18.500 1.6054 0.07366 0.06840 -0.0276 0.0995 1.0000
18.750 1.6049 0.07662 0.07143 -0.0278 0.0952 1.0000
19.000 1.6008 0.08006 0.07493 -0.0281 0.0905 1.0000
19.250 1.5930 0.08407 0.07899 -0.0287 0.0848 1.0000
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