GOE 512 AIRFOIL (goe512-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 512 AIRFOIL (goe512-il) Reynolds number: 100,000 Max Cl/Cd: 48.81 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe512-il-100000.txt Download as CSV file: xf-goe512-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 512 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3135 0.09865 0.09503 -0.0358 0.9792 0.1265
-7.500 -0.3885 0.10215 0.09832 -0.0155 1.0000 0.1188
-7.250 -0.4018 0.10022 0.09645 -0.0161 0.9975 0.1222
-7.000 -0.4134 0.09516 0.09131 -0.0301 0.9829 0.1276
-6.750 -0.2321 0.07926 0.07560 -0.0435 0.9487 0.1487
-6.500 -0.2469 0.07594 0.07225 -0.0464 0.9366 0.1557
-6.250 -0.3351 0.08235 0.07841 -0.0393 0.9566 0.1466
-6.000 -0.3286 0.07839 0.07421 -0.0465 0.9420 0.1586
-5.750 -0.3077 0.07531 0.07127 -0.0435 0.9336 0.1628
-5.500 -0.2932 0.07163 0.06741 -0.0475 0.9228 0.1755
-5.250 -0.2686 0.06846 0.06425 -0.0476 0.9147 0.1814
-5.000 -0.2948 0.04790 0.04209 -0.0509 0.9020 0.0962
-4.750 -0.2695 0.04298 0.03662 -0.0515 0.8965 0.0949
-4.500 -0.2581 0.03982 0.03293 -0.0489 0.8853 0.0952
-4.250 -0.2234 0.03632 0.02868 -0.0497 0.8807 0.0962
-4.000 -0.2069 0.03455 0.02643 -0.0474 0.8692 0.0990
-3.750 -0.1628 0.03252 0.02427 -0.0500 0.8651 0.1041
-3.500 -0.1414 0.03153 0.02300 -0.0484 0.8532 0.1092
-3.250 -0.0932 0.02966 0.02093 -0.0514 0.8495 0.1162
-3.000 -0.0702 0.02898 0.02013 -0.0501 0.8375 0.1231
-2.750 -0.0195 0.02740 0.01852 -0.0534 0.8338 0.1348
-2.500 0.0046 0.02671 0.01780 -0.0523 0.8219 0.1458
-2.250 0.0555 0.02528 0.01648 -0.0556 0.8182 0.1690
-2.000 0.0804 0.02484 0.01623 -0.0544 0.8064 0.1955
-1.750 0.1241 0.02453 0.01597 -0.0557 0.8019 0.2604
-1.500 0.1441 0.02439 0.01573 -0.0536 0.7894 0.3018
-1.250 0.1988 0.02314 0.01440 -0.0578 0.7856 0.3450
-1.000 0.2320 0.02234 0.01371 -0.0584 0.7736 0.3698
-0.750 0.3032 0.02088 0.01233 -0.0661 0.7688 0.4095
-0.500 0.3479 0.02018 0.01175 -0.0690 0.7558 0.4391
-0.250 0.4008 0.01939 0.01102 -0.0734 0.7430 0.4701
0.000 0.4468 0.01863 0.01031 -0.0763 0.7285 0.5004
0.250 0.6925 0.01748 0.00993 -0.1180 0.6992 0.9889
0.500 0.7504 0.01745 0.00963 -0.1240 0.6784 1.0000
0.750 0.7750 0.01763 0.00959 -0.1231 0.6616 1.0000
1.000 0.7989 0.01785 0.00960 -0.1221 0.6458 1.0000
1.250 0.8222 0.01809 0.00964 -0.1211 0.6309 1.0000
1.500 0.8466 0.01833 0.00968 -0.1202 0.6173 1.0000
1.750 0.8660 0.01861 0.00984 -0.1185 0.6034 1.0000
2.000 0.8842 0.01893 0.01007 -0.1166 0.5905 1.0000
2.250 0.9045 0.01922 0.01025 -0.1150 0.5785 1.0000
2.500 0.9282 0.01947 0.01033 -0.1141 0.5675 1.0000
2.750 0.9430 0.01980 0.01064 -0.1116 0.5554 1.0000
3.000 0.9615 0.02010 0.01086 -0.1098 0.5443 1.0000
3.250 0.9848 0.02033 0.01093 -0.1088 0.5337 1.0000
3.500 0.9981 0.02066 0.01126 -0.1059 0.5217 1.0000
3.750 1.0153 0.02098 0.01152 -0.1039 0.5107 1.0000
4.000 1.0378 0.02126 0.01163 -0.1027 0.5002 1.0000
4.250 1.0518 0.02163 0.01201 -0.1001 0.4886 1.0000
4.500 1.0688 0.02204 0.01237 -0.0980 0.4778 1.0000
4.750 1.0932 0.02242 0.01256 -0.0974 0.4677 1.0000
5.000 1.1056 0.02291 0.01311 -0.0945 0.4566 1.0000
5.250 1.1242 0.02343 0.01357 -0.0928 0.4465 1.0000
5.500 1.1461 0.02392 0.01394 -0.0917 0.4367 1.0000
5.750 1.1585 0.02453 0.01460 -0.0890 0.4270 1.0000
6.000 1.1859 0.02506 0.01496 -0.0890 0.4185 1.0000
6.250 1.1933 0.02573 0.01577 -0.0854 0.4098 1.0000
6.500 1.2189 0.02630 0.01622 -0.0851 0.4027 1.0000
6.750 1.2294 0.02706 0.01711 -0.0821 0.3957 1.0000
7.000 1.2461 0.02771 0.01779 -0.0803 0.3893 1.0000
7.250 1.2734 0.02839 0.01836 -0.0804 0.3837 1.0000
7.500 1.2768 0.02917 0.01935 -0.0762 0.3777 1.0000
7.750 1.2942 0.02981 0.02003 -0.0745 0.3722 1.0000
8.000 1.3239 0.03051 0.02062 -0.0752 0.3676 1.0000
8.250 1.3230 0.03146 0.02183 -0.0703 0.3628 1.0000
8.500 1.3343 0.03220 0.02267 -0.0676 0.3578 1.0000
8.750 1.3611 0.03269 0.02309 -0.0677 0.3530 1.0000
9.000 1.3661 0.03363 0.02418 -0.0640 0.3483 1.0000
9.250 1.3687 0.03453 0.02525 -0.0600 0.3436 1.0000
9.500 1.3871 0.03508 0.02581 -0.0586 0.3390 1.0000
9.750 1.4131 0.03574 0.02644 -0.0586 0.3347 1.0000
10.000 1.4022 0.03700 0.02797 -0.0525 0.3309 1.0000
10.250 1.4038 0.03800 0.02911 -0.0485 0.3267 1.0000
10.500 1.4239 0.03862 0.02976 -0.0476 0.3227 1.0000
10.750 1.4487 0.03937 0.03051 -0.0475 0.3188 1.0000
11.000 1.4237 0.04102 0.03242 -0.0395 0.3158 1.0000
11.250 1.4087 0.04248 0.03407 -0.0333 0.3125 1.0000
11.500 1.4139 0.04353 0.03521 -0.0304 0.3089 1.0000
11.750 1.4701 0.04360 0.03519 -0.0350 0.3044 1.0000
12.000 1.4291 0.04590 0.03774 -0.0256 0.3019 1.0000
12.250 1.3795 0.04921 0.04132 -0.0169 0.2992 1.0000
12.500 1.3315 0.05335 0.04567 -0.0102 0.2960 1.0000
12.750 1.3807 0.05222 0.04452 -0.0118 0.2915 1.0000
13.000 1.4044 0.05283 0.04517 -0.0115 0.2874 1.0000
13.750 1.4301 0.05590 0.04843 -0.0065 0.2732 1.0000
14.000 0.7710 0.15772 0.15046 -0.0296 0.3046 1.0000
14.250 0.7324 0.16107 0.15380 -0.0319 0.2977 1.0000
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Polar data table (+)
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