GOE 612 AIRFOIL (goe612-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 612 AIRFOIL (goe612-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.65 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe612-il-1000000.txt Download as CSV file: xf-goe612-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7296 0.05617 0.05353 -0.1001 0.9966 0.0278
-14.500 -0.7567 0.04651 0.04364 -0.1108 0.9895 0.0278
-14.250 -0.7601 0.03984 0.03680 -0.1200 0.9851 0.0279
-14.000 -0.7516 0.03366 0.03040 -0.1309 0.9819 0.0281
-13.750 -0.7379 0.02982 0.02636 -0.1384 0.9769 0.0283
-13.500 -0.7173 0.02754 0.02391 -0.1428 0.9724 0.0285
-13.250 -0.6970 0.02579 0.02202 -0.1452 0.9671 0.0287
-13.000 -0.6881 0.02472 0.02082 -0.1440 0.9582 0.0289
-12.750 -0.6774 0.02386 0.01985 -0.1425 0.9508 0.0290
-12.500 -0.6638 0.02347 0.01935 -0.1407 0.9438 0.0292
-12.250 -0.6601 0.02183 0.01755 -0.1383 0.9362 0.0295
-12.000 -0.6509 0.02067 0.01628 -0.1361 0.9291 0.0297
-11.750 -0.6359 0.01981 0.01534 -0.1346 0.9233 0.0300
-11.500 -0.6198 0.01912 0.01462 -0.1330 0.9173 0.0303
-11.250 -0.6017 0.01850 0.01394 -0.1316 0.9115 0.0305
-11.000 -0.5816 0.01796 0.01332 -0.1305 0.9061 0.0308
-10.750 -0.5619 0.01742 0.01274 -0.1293 0.8999 0.0310
-10.500 -0.5410 0.01691 0.01216 -0.1283 0.8934 0.0314
-10.250 -0.5197 0.01638 0.01156 -0.1273 0.8871 0.0316
-10.000 -0.4980 0.01589 0.01100 -0.1263 0.8796 0.0319
-9.750 -0.4756 0.01543 0.01044 -0.1254 0.8726 0.0323
-9.500 -0.4526 0.01502 0.00998 -0.1245 0.8646 0.0327
-9.250 -0.4291 0.01464 0.00951 -0.1237 0.8563 0.0330
-9.000 -0.4054 0.01427 0.00908 -0.1229 0.8472 0.0333
-8.750 -0.3815 0.01394 0.00865 -0.1221 0.8373 0.0335
-8.500 -0.3602 0.01329 0.00793 -0.1210 0.8260 0.0339
-8.250 -0.3385 0.01272 0.00727 -0.1199 0.8146 0.0344
-8.000 -0.3151 0.01236 0.00684 -0.1191 0.8031 0.0349
-7.750 -0.2906 0.01206 0.00649 -0.1184 0.7917 0.0354
-7.500 -0.2659 0.01181 0.00618 -0.1177 0.7811 0.0359
-7.250 -0.2412 0.01158 0.00586 -0.1170 0.7705 0.0364
-7.000 -0.2158 0.01134 0.00557 -0.1164 0.7611 0.0370
-6.750 -0.1907 0.01115 0.00529 -0.1157 0.7520 0.0375
-6.500 -0.1645 0.01095 0.00504 -0.1153 0.7446 0.0380
-6.250 -0.1393 0.01070 0.00472 -0.1146 0.7372 0.0387
-6.000 -0.1144 0.01039 0.00437 -0.1140 0.7308 0.0398
-5.750 -0.0881 0.01018 0.00414 -0.1136 0.7245 0.0407
-5.500 -0.0620 0.01004 0.00394 -0.1131 0.7180 0.0416
-5.250 -0.0353 0.00988 0.00375 -0.1127 0.7121 0.0427
-5.000 -0.0084 0.00976 0.00358 -0.1123 0.7056 0.0436
-4.750 0.0170 0.00954 0.00331 -0.1117 0.6991 0.0454
-4.500 0.0439 0.00937 0.00314 -0.1113 0.6938 0.0472
-4.250 0.0711 0.00925 0.00299 -0.1110 0.6886 0.0491
-4.000 0.0973 0.00908 0.00280 -0.1105 0.6830 0.0524
-3.750 0.1242 0.00897 0.00266 -0.1102 0.6779 0.0561
-3.500 0.1511 0.00877 0.00250 -0.1098 0.6733 0.0634
-3.250 0.1773 0.00857 0.00238 -0.1094 0.6682 0.0806
-3.000 0.2035 0.00846 0.00231 -0.1090 0.6626 0.0996
-2.750 0.2310 0.00834 0.00224 -0.1087 0.6581 0.1108
-2.500 0.2584 0.00826 0.00217 -0.1085 0.6531 0.1197
-2.250 0.2851 0.00820 0.00210 -0.1081 0.6478 0.1290
-2.000 0.3119 0.00812 0.00205 -0.1077 0.6425 0.1420
-1.750 0.3390 0.00800 0.00199 -0.1074 0.6373 0.1592
-1.500 0.3655 0.00788 0.00195 -0.1070 0.6325 0.1854
-1.250 0.3917 0.00780 0.00193 -0.1066 0.6278 0.2143
-1.000 0.4186 0.00769 0.00192 -0.1063 0.6238 0.2438
-0.750 0.4456 0.00760 0.00191 -0.1060 0.6190 0.2709
-0.500 0.4721 0.00756 0.00191 -0.1056 0.6136 0.2947
-0.250 0.4984 0.00755 0.00193 -0.1051 0.6083 0.3176
0.250 0.5525 0.00748 0.00196 -0.1045 0.5980 0.3574
0.500 0.5784 0.00750 0.00198 -0.1040 0.5920 0.3735
0.750 0.6054 0.00747 0.00200 -0.1037 0.5860 0.3884
1.000 0.6316 0.00748 0.00202 -0.1032 0.5789 0.4034
1.250 0.6575 0.00750 0.00205 -0.1027 0.5723 0.4191
1.500 0.6838 0.00750 0.00209 -0.1022 0.5646 0.4361
1.750 0.7085 0.00754 0.00213 -0.1015 0.5555 0.4557
2.000 0.7337 0.00753 0.00218 -0.1009 0.5454 0.4810
2.250 0.7576 0.00754 0.00224 -0.1000 0.5342 0.5134
2.500 0.7797 0.00754 0.00231 -0.0987 0.5203 0.5609
2.750 0.7942 0.00725 0.00243 -0.0960 0.5036 0.7277
3.000 0.9014 0.00741 0.00288 -0.1135 0.4538 0.9989
3.250 0.9221 0.00787 0.00311 -0.1122 0.4115 1.0000
3.500 0.9369 0.00828 0.00333 -0.1096 0.3802 1.0000
3.750 0.9530 0.00863 0.00354 -0.1073 0.3573 1.0000
4.000 0.9713 0.00889 0.00372 -0.1054 0.3431 1.0000
4.250 0.9900 0.00914 0.00389 -0.1036 0.3323 1.0000
4.500 1.0090 0.00936 0.00406 -0.1018 0.3231 1.0000
4.750 1.0283 0.00958 0.00423 -0.1001 0.3159 1.0000
5.000 1.0481 0.00976 0.00439 -0.0985 0.3099 1.0000
5.250 1.0640 0.00999 0.00458 -0.0961 0.3037 1.0000
5.500 1.0814 0.01017 0.00474 -0.0940 0.2989 1.0000
5.750 1.0998 0.01034 0.00490 -0.0921 0.2944 1.0000
6.000 1.1171 0.01057 0.00510 -0.0901 0.2893 1.0000
6.250 1.1340 0.01083 0.00534 -0.0881 0.2839 1.0000
6.500 1.1547 0.01100 0.00551 -0.0867 0.2803 1.0000
6.750 1.1742 0.01122 0.00573 -0.0852 0.2758 1.0000
7.000 1.1922 0.01151 0.00599 -0.0836 0.2707 1.0000
7.250 1.2111 0.01178 0.00625 -0.0820 0.2661 1.0000
7.500 1.2319 0.01200 0.00648 -0.0809 0.2618 1.0000
7.750 1.2507 0.01230 0.00676 -0.0794 0.2567 1.0000
8.000 1.2681 0.01268 0.00710 -0.0778 0.2511 1.0000
8.250 1.2889 0.01292 0.00737 -0.0768 0.2475 1.0000
8.500 1.3082 0.01323 0.00768 -0.0755 0.2427 1.0000
8.750 1.3258 0.01364 0.00806 -0.0740 0.2372 1.0000
9.000 1.3447 0.01399 0.00842 -0.0728 0.2326 1.0000
9.250 1.3636 0.01436 0.00879 -0.0716 0.2274 1.0000
9.500 1.3802 0.01484 0.00924 -0.0701 0.2214 1.0000
9.750 1.3982 0.01527 0.00968 -0.0688 0.2156 1.0000
10.000 1.4145 0.01580 0.01018 -0.0674 0.2082 1.0000
10.250 1.4304 0.01636 0.01072 -0.0660 0.2011 1.0000
10.500 1.4464 0.01693 0.01128 -0.0646 0.1946 1.0000
10.750 1.4604 0.01763 0.01194 -0.0630 0.1864 1.0000
11.000 1.4736 0.01838 0.01266 -0.0615 0.1779 1.0000
11.250 1.4877 0.01911 0.01338 -0.0600 0.1711 1.0000
11.500 1.5009 0.01991 0.01417 -0.0586 0.1648 1.0000
11.750 1.5138 0.02076 0.01500 -0.0571 0.1589 1.0000
12.000 1.5275 0.02157 0.01582 -0.0558 0.1539 1.0000
12.250 1.5380 0.02260 0.01683 -0.0543 0.1483 1.0000
12.500 1.5519 0.02345 0.01770 -0.0531 0.1446 1.0000
12.750 1.5641 0.02441 0.01868 -0.0519 0.1405 1.0000
13.000 1.5737 0.02559 0.01984 -0.0505 0.1358 1.0000
13.250 1.5862 0.02659 0.02087 -0.0494 0.1324 1.0000
13.500 1.5984 0.02764 0.02195 -0.0484 0.1294 1.0000
13.750 1.6081 0.02888 0.02319 -0.0472 0.1256 1.0000
14.000 1.6171 0.03021 0.02454 -0.0461 0.1227 1.0000
14.250 1.6287 0.03138 0.02575 -0.0451 0.1207 1.0000
14.500 1.6405 0.03253 0.02694 -0.0443 0.1178 1.0000
14.750 1.6497 0.03392 0.02836 -0.0434 0.1149 1.0000
15.000 1.6574 0.03544 0.02990 -0.0424 0.1122 1.0000
15.250 1.6649 0.03703 0.03151 -0.0415 0.1093 1.0000
15.500 1.6761 0.03829 0.03283 -0.0408 0.1073 1.0000
15.750 1.6844 0.03985 0.03442 -0.0400 0.1047 1.0000
16.000 1.6897 0.04169 0.03628 -0.0392 0.1013 1.0000
16.250 1.6954 0.04351 0.03813 -0.0384 0.0979 1.0000
16.500 1.7019 0.04528 0.03993 -0.0378 0.0935 1.0000
16.750 1.7037 0.04753 0.04218 -0.0370 0.0889 1.0000
17.000 1.7060 0.04977 0.04444 -0.0364 0.0824 1.0000
17.250 1.6997 0.05291 0.04753 -0.0356 0.0724 1.0000
17.500 1.6784 0.05772 0.05223 -0.0347 0.0565 1.0000
17.750 1.6527 0.06325 0.05771 -0.0342 0.0431 1.0000
18.000 1.6264 0.06908 0.06354 -0.0340 0.0325 1.0000
18.250 1.6039 0.07473 0.06922 -0.0342 0.0250 1.0000
18.500 1.5859 0.07998 0.07454 -0.0346 0.0212 1.0000
18.750 1.5725 0.08479 0.07942 -0.0352 0.0195 1.0000
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Polar data table (+)
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