GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 621 AIRFOIL (goe621-il) Reynolds number: 500,000 Max Cl/Cd: 84.16 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe621-il-500000-n5.txt Download as CSV file: xf-goe621-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6637 0.05709 0.05361 -0.1016 0.9827 0.0285
-14.000 -0.6857 0.04812 0.04441 -0.1115 0.9769 0.0285
-13.750 -0.6891 0.04090 0.03697 -0.1217 0.9721 0.0287
-13.500 -0.6805 0.03483 0.03066 -0.1322 0.9667 0.0288
-13.250 -0.6689 0.03067 0.02626 -0.1399 0.9588 0.0290
-13.000 -0.6611 0.02847 0.02387 -0.1418 0.9499 0.0292
-12.750 -0.6542 0.02695 0.02219 -0.1414 0.9415 0.0294
-12.500 -0.6528 0.02594 0.02104 -0.1387 0.9317 0.0296
-12.250 -0.6419 0.02493 0.01988 -0.1373 0.9249 0.0297
-12.000 -0.6323 0.02407 0.01890 -0.1353 0.9167 0.0299
-11.750 -0.6196 0.02310 0.01781 -0.1338 0.9100 0.0302
-11.500 -0.6063 0.02222 0.01685 -0.1321 0.9030 0.0304
-11.250 -0.5905 0.02144 0.01600 -0.1307 0.8958 0.0306
-11.000 -0.5728 0.02074 0.01523 -0.1295 0.8893 0.0308
-10.750 -0.5546 0.02010 0.01452 -0.1283 0.8812 0.0311
-10.500 -0.5348 0.01948 0.01381 -0.1272 0.8742 0.0313
-10.250 -0.5150 0.01890 0.01316 -0.1261 0.8659 0.0316
-10.000 -0.4939 0.01835 0.01252 -0.1251 0.8582 0.0319
-9.750 -0.4728 0.01782 0.01190 -0.1242 0.8494 0.0322
-9.500 -0.4508 0.01731 0.01129 -0.1232 0.8404 0.0325
-9.250 -0.4287 0.01683 0.01073 -0.1223 0.8302 0.0329
-9.000 -0.4062 0.01637 0.01016 -0.1214 0.8202 0.0332
-8.750 -0.3834 0.01593 0.00962 -0.1206 0.8093 0.0336
-8.500 -0.3601 0.01553 0.00912 -0.1198 0.7994 0.0339
-8.250 -0.3363 0.01519 0.00866 -0.1190 0.7893 0.0343
-8.000 -0.3131 0.01476 0.00817 -0.1182 0.7796 0.0348
-7.750 -0.2899 0.01438 0.00770 -0.1174 0.7703 0.0353
-7.500 -0.2656 0.01405 0.00732 -0.1167 0.7610 0.0358
-7.250 -0.2413 0.01377 0.00696 -0.1160 0.7526 0.0363
-7.000 -0.2163 0.01348 0.00661 -0.1154 0.7449 0.0369
-6.750 -0.1913 0.01322 0.00628 -0.1148 0.7379 0.0374
-6.500 -0.1659 0.01297 0.00597 -0.1142 0.7318 0.0381
-6.250 -0.1404 0.01273 0.00567 -0.1137 0.7254 0.0387
-6.000 -0.1147 0.01254 0.00539 -0.1132 0.7193 0.0393
-5.750 -0.0894 0.01225 0.00508 -0.1126 0.7138 0.0403
-5.500 -0.0635 0.01203 0.00483 -0.1122 0.7083 0.0413
-5.250 -0.0373 0.01185 0.00460 -0.1117 0.7033 0.0424
-5.000 -0.0109 0.01169 0.00439 -0.1113 0.6987 0.0439
-4.750 0.0156 0.01151 0.00419 -0.1109 0.6940 0.0454
-4.500 0.0418 0.01132 0.00399 -0.1105 0.6883 0.0474
-4.250 0.0680 0.01119 0.00380 -0.1100 0.6826 0.0496
-4.000 0.0945 0.01103 0.00362 -0.1096 0.6769 0.0522
-3.750 0.1209 0.01087 0.00346 -0.1092 0.6711 0.0559
-3.500 0.1472 0.01074 0.00330 -0.1087 0.6655 0.0609
-3.250 0.1736 0.01059 0.00317 -0.1083 0.6605 0.0696
-3.000 0.2000 0.01042 0.00308 -0.1080 0.6551 0.0850
-2.750 0.2265 0.01032 0.00300 -0.1076 0.6497 0.0982
-2.500 0.2531 0.01026 0.00291 -0.1071 0.6444 0.1078
-2.250 0.2799 0.01015 0.00284 -0.1068 0.6394 0.1171
-2.000 0.3066 0.01007 0.00277 -0.1064 0.6337 0.1256
-1.750 0.3326 0.01003 0.00270 -0.1059 0.6274 0.1361
-1.500 0.3591 0.00992 0.00265 -0.1055 0.6211 0.1514
-1.250 0.3849 0.00980 0.00261 -0.1051 0.6145 0.1763
-0.750 0.4369 0.00958 0.00259 -0.1042 0.6042 0.2429
-0.500 0.4629 0.00952 0.00259 -0.1037 0.5978 0.2703
-0.250 0.4887 0.00951 0.00259 -0.1031 0.5919 0.2919
0.250 0.5413 0.00946 0.00263 -0.1023 0.5797 0.3276
0.500 0.5668 0.00948 0.00265 -0.1017 0.5731 0.3422
0.750 0.5927 0.00948 0.00268 -0.1012 0.5650 0.3557
1.000 0.6174 0.00953 0.00271 -0.1004 0.5562 0.3692
1.250 0.6429 0.00955 0.00275 -0.0998 0.5468 0.3840
1.500 0.6671 0.00959 0.00281 -0.0990 0.5373 0.4011
1.750 0.6908 0.00964 0.00287 -0.0981 0.5249 0.4203
2.000 0.7136 0.00971 0.00294 -0.0970 0.5096 0.4406
2.250 0.7347 0.00981 0.00303 -0.0956 0.4914 0.4643
2.500 0.7543 0.00995 0.00314 -0.0939 0.4710 0.4891
3.000 0.7876 0.01031 0.00347 -0.0895 0.4204 0.5605
3.250 0.7975 0.01021 0.00369 -0.0860 0.3984 0.6980
3.750 0.9098 0.01081 0.00454 -0.0987 0.3494 1.0000
4.000 0.9263 0.01109 0.00474 -0.0965 0.3381 1.0000
4.250 0.9411 0.01136 0.00494 -0.0939 0.3277 1.0000
4.750 0.9688 0.01189 0.00535 -0.0885 0.3092 1.0000
5.000 0.9830 0.01220 0.00559 -0.0859 0.3010 1.0000
5.250 1.0006 0.01243 0.00580 -0.0840 0.2957 1.0000
5.500 1.0188 0.01267 0.00602 -0.0822 0.2908 1.0000
5.750 1.0360 0.01295 0.00628 -0.0803 0.2859 1.0000
6.000 1.0530 0.01326 0.00656 -0.0785 0.2814 1.0000
6.250 1.0725 0.01350 0.00680 -0.0770 0.2774 1.0000
6.500 1.0910 0.01379 0.00708 -0.0755 0.2728 1.0000
6.750 1.1081 0.01414 0.00741 -0.0738 0.2675 1.0000
7.000 1.1257 0.01449 0.00774 -0.0722 0.2631 1.0000
7.250 1.1447 0.01479 0.00805 -0.0708 0.2581 1.0000
7.500 1.1623 0.01517 0.00842 -0.0693 0.2531 1.0000
7.750 1.1786 0.01560 0.00883 -0.0676 0.2485 1.0000
8.000 1.1974 0.01596 0.00920 -0.0663 0.2444 1.0000
8.250 1.2152 0.01636 0.00961 -0.0649 0.2395 1.0000
8.500 1.2315 0.01684 0.01008 -0.0634 0.2345 1.0000
8.750 1.2481 0.01732 0.01056 -0.0619 0.2300 1.0000
9.000 1.2656 0.01778 0.01103 -0.0607 0.2251 1.0000
9.250 1.2815 0.01833 0.01158 -0.0592 0.2196 1.0000
9.500 1.2965 0.01894 0.01218 -0.0577 0.2147 1.0000
9.750 1.3132 0.01948 0.01274 -0.0565 0.2093 1.0000
10.000 1.3276 0.02016 0.01341 -0.0550 0.2036 1.0000
10.250 1.3421 0.02086 0.01411 -0.0536 0.1982 1.0000
10.500 1.3567 0.02157 0.01483 -0.0523 0.1919 1.0000
10.750 1.3686 0.02247 0.01570 -0.0508 0.1855 1.0000
11.000 1.3831 0.02322 0.01648 -0.0495 0.1804 1.0000
11.250 1.3948 0.02419 0.01743 -0.0481 0.1736 1.0000
11.500 1.4065 0.02516 0.01840 -0.0468 0.1671 1.0000
11.750 1.4172 0.02625 0.01947 -0.0454 0.1604 1.0000
12.000 1.4285 0.02731 0.02055 -0.0442 0.1559 1.0000
12.250 1.4402 0.02837 0.02163 -0.0431 0.1509 1.0000
12.500 1.4506 0.02956 0.02283 -0.0419 0.1467 1.0000
12.750 1.4604 0.03082 0.02410 -0.0408 0.1421 1.0000
13.000 1.4718 0.03198 0.02530 -0.0398 0.1389 1.0000
13.250 1.4814 0.03330 0.02664 -0.0388 0.1348 1.0000
13.500 1.4890 0.03481 0.02817 -0.0377 0.1313 1.0000
13.750 1.4997 0.03610 0.02950 -0.0369 0.1283 1.0000
14.000 1.5093 0.03748 0.03092 -0.0360 0.1254 1.0000
14.250 1.5173 0.03903 0.03251 -0.0351 0.1222 1.0000
14.500 1.5239 0.04074 0.03424 -0.0343 0.1193 1.0000
14.750 1.5317 0.04237 0.03592 -0.0335 0.1171 1.0000
15.000 1.5408 0.04388 0.03749 -0.0329 0.1148 1.0000
15.250 1.5474 0.04566 0.03931 -0.0322 0.1116 1.0000
15.500 1.5536 0.04749 0.04119 -0.0316 0.1094 1.0000
15.750 1.5561 0.04974 0.04348 -0.0309 0.1063 1.0000
16.000 1.5634 0.05153 0.04533 -0.0304 0.1043 1.0000
16.250 1.5690 0.05350 0.04736 -0.0300 0.1014 1.0000
16.500 1.5728 0.05569 0.04960 -0.0296 0.0986 1.0000
16.750 1.5743 0.05817 0.05212 -0.0292 0.0959 1.0000
17.000 1.5768 0.06058 0.05461 -0.0289 0.0932 1.0000
17.250 1.5798 0.06295 0.05704 -0.0287 0.0895 1.0000
17.500 1.5775 0.06597 0.06009 -0.0285 0.0853 1.0000
17.750 1.5773 0.06880 0.06298 -0.0285 0.0813 1.0000
18.000 1.5688 0.07269 0.06688 -0.0286 0.0731 1.0000
18.250 1.5570 0.07706 0.07125 -0.0289 0.0644 1.0000
18.500 1.5392 0.08230 0.07650 -0.0295 0.0553 1.0000
18.750 1.5120 0.08899 0.08319 -0.0307 0.0445 1.0000
19.000 1.4861 0.09573 0.08997 -0.0321 0.0361 1.0000
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Polar data table (+)
Polar graphs
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