GOE 612 AIRFOIL (goe612-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 612 AIRFOIL (goe612-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-goe612-il-500000.txt Download as CSV file: xf-goe612-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 612 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5071 0.04666 0.04355 -0.1194 0.9798 0.0376
-11.750 -0.5244 0.03704 0.03344 -0.1360 0.9708 0.0376
-11.500 -0.5249 0.03360 0.02966 -0.1382 0.9625 0.0378
-11.250 -0.5145 0.03100 0.02676 -0.1394 0.9560 0.0380
-11.000 -0.5084 0.02934 0.02484 -0.1379 0.9470 0.0382
-10.750 -0.4958 0.02784 0.02308 -0.1370 0.9402 0.0384
-10.500 -0.4905 0.02560 0.02065 -0.1348 0.9311 0.0387
-10.250 -0.4739 0.02415 0.01909 -0.1337 0.9250 0.0390
-10.000 -0.4578 0.02317 0.01804 -0.1321 0.9175 0.0394
-9.750 -0.4393 0.02226 0.01704 -0.1309 0.9104 0.0398
-9.500 -0.4195 0.02151 0.01619 -0.1297 0.9038 0.0403
-9.250 -0.4000 0.02078 0.01538 -0.1285 0.8955 0.0408
-9.000 -0.3781 0.02001 0.01449 -0.1275 0.8891 0.0414
-8.750 -0.3583 0.01925 0.01363 -0.1262 0.8799 0.0418
-8.500 -0.3356 0.01848 0.01270 -0.1254 0.8730 0.0423
-8.250 -0.3141 0.01781 0.01193 -0.1242 0.8634 0.0427
-8.000 -0.2901 0.01721 0.01118 -0.1235 0.8557 0.0432
-7.750 -0.2671 0.01672 0.01059 -0.1225 0.8455 0.0436
-7.500 -0.2448 0.01572 0.00949 -0.1216 0.8370 0.0443
-7.250 -0.2220 0.01510 0.00885 -0.1208 0.8268 0.0450
-7.000 -0.1975 0.01465 0.00835 -0.1201 0.8184 0.0457
-6.750 -0.1731 0.01427 0.00791 -0.1194 0.8090 0.0466
-6.500 -0.1480 0.01392 0.00748 -0.1187 0.8009 0.0477
-6.250 -0.1231 0.01358 0.00706 -0.1180 0.7920 0.0486
-6.000 -0.0976 0.01329 0.00666 -0.1174 0.7845 0.0494
-5.750 -0.0744 0.01274 0.00608 -0.1166 0.7764 0.0506
-5.500 -0.0493 0.01240 0.00569 -0.1160 0.7698 0.0520
-5.250 -0.0240 0.01213 0.00540 -0.1154 0.7632 0.0536
-5.000 0.0019 0.01190 0.00510 -0.1148 0.7564 0.0552
-4.750 0.0275 0.01161 0.00474 -0.1143 0.7506 0.0574
-4.500 0.0528 0.01134 0.00448 -0.1137 0.7443 0.0604
-4.250 0.0790 0.01116 0.00424 -0.1132 0.7379 0.0637
-4.000 0.1048 0.01091 0.00398 -0.1127 0.7316 0.0693
-3.750 0.1304 0.01067 0.00379 -0.1121 0.7250 0.0781
-3.500 0.1566 0.01048 0.00363 -0.1116 0.7192 0.0946
-3.250 0.1834 0.01034 0.00352 -0.1113 0.7138 0.1130
-3.000 0.2095 0.01019 0.00341 -0.1108 0.7080 0.1277
-2.750 0.2361 0.01007 0.00330 -0.1105 0.7025 0.1416
-2.500 0.2633 0.00999 0.00322 -0.1102 0.6974 0.1566
-2.250 0.2892 0.00984 0.00315 -0.1097 0.6919 0.1756
-2.000 0.3153 0.00969 0.00309 -0.1092 0.6862 0.2028
-1.750 0.3420 0.00961 0.00304 -0.1089 0.6805 0.2345
-1.500 0.3681 0.00951 0.00303 -0.1084 0.6750 0.2647
-1.250 0.3943 0.00942 0.00303 -0.1080 0.6696 0.2923
-1.000 0.4213 0.00939 0.00302 -0.1076 0.6647 0.3184
-0.750 0.4481 0.00937 0.00304 -0.1073 0.6598 0.3416
-0.500 0.4743 0.00932 0.00306 -0.1068 0.6545 0.3636
-0.250 0.5009 0.00930 0.00307 -0.1064 0.6495 0.3826
0.000 0.5281 0.00932 0.00307 -0.1061 0.6447 0.3996
0.250 0.5542 0.00928 0.00309 -0.1056 0.6394 0.4162
0.500 0.5801 0.00925 0.00310 -0.1050 0.6334 0.4335
0.750 0.6065 0.00926 0.00310 -0.1046 0.6278 0.4521
1.000 0.6320 0.00922 0.00313 -0.1040 0.6222 0.4726
1.250 0.6571 0.00916 0.00316 -0.1033 0.6159 0.4978
1.500 0.6819 0.00911 0.00317 -0.1026 0.6096 0.5342
1.750 0.7043 0.00892 0.00322 -0.1014 0.6025 0.5951
2.000 0.7963 0.00824 0.00342 -0.1148 0.5923 0.9804
2.250 0.8404 0.00834 0.00350 -0.1183 0.5824 1.0000
2.500 0.8624 0.00845 0.00352 -0.1170 0.5733 1.0000
2.750 0.8845 0.00853 0.00358 -0.1157 0.5623 1.0000
3.000 0.9060 0.00865 0.00364 -0.1143 0.5506 1.0000
3.250 0.9262 0.00879 0.00370 -0.1126 0.5363 1.0000
3.500 0.9454 0.00896 0.00379 -0.1108 0.5186 1.0000
3.750 0.9631 0.00918 0.00390 -0.1087 0.4964 1.0000
4.000 0.9769 0.00950 0.00406 -0.1059 0.4674 1.0000
4.250 0.9876 0.00994 0.00429 -0.1025 0.4337 1.0000
4.750 1.0095 0.01083 0.00486 -0.0960 0.3822 1.0000
5.000 1.0202 0.01120 0.00512 -0.0927 0.3669 1.0000
5.250 1.0322 0.01155 0.00539 -0.0897 0.3551 1.0000
5.500 1.0471 0.01186 0.00565 -0.0872 0.3454 1.0000
5.750 1.0608 0.01223 0.00595 -0.0847 0.3369 1.0000
6.000 1.0782 0.01252 0.00622 -0.0828 0.3295 1.0000
6.250 1.0939 0.01288 0.00654 -0.0807 0.3223 1.0000
6.500 1.1106 0.01324 0.00687 -0.0788 0.3163 1.0000
6.750 1.1292 0.01354 0.00717 -0.0772 0.3106 1.0000
7.000 1.1455 0.01394 0.00753 -0.0754 0.3049 1.0000
7.250 1.1624 0.01433 0.00791 -0.0737 0.2997 1.0000
7.500 1.1818 0.01464 0.00824 -0.0724 0.2947 1.0000
7.750 1.1990 0.01504 0.00862 -0.0708 0.2895 1.0000
8.000 1.2139 0.01557 0.00910 -0.0689 0.2843 1.0000
8.250 1.2340 0.01587 0.00946 -0.0678 0.2798 1.0000
8.500 1.2520 0.01627 0.00987 -0.0665 0.2745 1.0000
8.750 1.2671 0.01682 0.01038 -0.0648 0.2692 1.0000
9.000 1.2852 0.01725 0.01084 -0.0635 0.2643 1.0000
9.250 1.3030 0.01769 0.01131 -0.0623 0.2588 1.0000
9.500 1.3180 0.01830 0.01189 -0.0607 0.2535 1.0000
9.750 1.3346 0.01884 0.01245 -0.0594 0.2485 1.0000
10.000 1.3517 0.01936 0.01300 -0.0583 0.2429 1.0000
10.250 1.3657 0.02007 0.01369 -0.0567 0.2372 1.0000
10.500 1.3815 0.02070 0.01435 -0.0555 0.2317 1.0000
10.750 1.3970 0.02136 0.01503 -0.0543 0.2255 1.0000
11.000 1.4078 0.02231 0.01595 -0.0526 0.2193 1.0000
11.250 1.4245 0.02295 0.01664 -0.0516 0.2130 1.0000
11.500 1.4351 0.02398 0.01763 -0.0501 0.2056 1.0000
11.750 1.4490 0.02483 0.01850 -0.0490 0.1985 1.0000
12.000 1.4588 0.02596 0.01961 -0.0476 0.1915 1.0000
12.250 1.4709 0.02698 0.02065 -0.0464 0.1850 1.0000
12.500 1.4808 0.02817 0.02184 -0.0452 0.1786 1.0000
12.750 1.4902 0.02944 0.02310 -0.0439 0.1731 1.0000
13.000 1.5017 0.03057 0.02428 -0.0429 0.1684 1.0000
13.250 1.5095 0.03201 0.02571 -0.0417 0.1636 1.0000
13.500 1.5179 0.03343 0.02715 -0.0406 0.1597 1.0000
13.750 1.5293 0.03464 0.02842 -0.0397 0.1557 1.0000
14.000 1.5374 0.03613 0.02993 -0.0387 0.1518 1.0000
14.250 1.5421 0.03795 0.03174 -0.0376 0.1481 1.0000
14.500 1.5528 0.03927 0.03313 -0.0369 0.1450 1.0000
14.750 1.5622 0.04074 0.03466 -0.0361 0.1424 1.0000
15.000 1.5695 0.04239 0.03635 -0.0353 0.1393 1.0000
15.250 1.5735 0.04437 0.03835 -0.0345 0.1362 1.0000
15.500 1.5787 0.04626 0.04027 -0.0337 0.1336 1.0000
15.750 1.5888 0.04775 0.04185 -0.0332 0.1314 1.0000
16.000 1.5958 0.04954 0.04371 -0.0327 0.1285 1.0000
16.250 1.6007 0.05155 0.04576 -0.0322 0.1258 1.0000
16.500 1.6018 0.05398 0.04821 -0.0316 0.1231 1.0000
16.750 1.6065 0.05606 0.05036 -0.0312 0.1209 1.0000
17.000 1.6140 0.05793 0.05233 -0.0310 0.1180 1.0000
17.250 1.6179 0.06017 0.05463 -0.0307 0.1152 1.0000
17.500 1.6181 0.06285 0.05735 -0.0305 0.1125 1.0000
17.750 1.6159 0.06583 0.06037 -0.0303 0.1094 1.0000
18.000 1.6223 0.06790 0.06255 -0.0302 0.1062 1.0000
18.250 1.6206 0.07097 0.06566 -0.0303 0.1021 1.0000
18.500 1.6138 0.07467 0.06939 -0.0305 0.0985 1.0000
18.750 1.6162 0.07730 0.07212 -0.0307 0.0936 1.0000
19.000 1.6067 0.08146 0.07631 -0.0311 0.0887 1.0000
19.250 1.6013 0.08516 0.08008 -0.0316 0.0817 1.0000
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Polar data table (+)
Polar graphs
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