GOE 398 AIRFOIL (goe398-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 398 AIRFOIL (goe398-il) Reynolds number: 500,000 Max Cl/Cd: 96.55 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe398-il-500000.txt Download as CSV file: xf-goe398-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 398 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3327 0.10736 0.10502 -0.0469 1.0000 0.0359
-11.250 -0.3288 0.10592 0.10361 -0.0451 1.0000 0.0362
-11.000 -0.5535 0.04393 0.04122 -0.0972 0.9855 0.0289
-10.750 -0.5772 0.03409 0.03061 -0.1042 0.9718 0.0293
-10.500 -0.5704 0.03009 0.02614 -0.1050 0.9629 0.0300
-10.250 -0.5508 0.02701 0.02257 -0.1065 0.9584 0.0307
-10.000 -0.5308 0.02475 0.01991 -0.1069 0.9517 0.0314
-9.750 -0.5024 0.02322 0.01833 -0.1080 0.9463 0.0321
-9.500 -0.4676 0.02253 0.01763 -0.1099 0.9428 0.0329
-9.250 -0.4413 0.02170 0.01668 -0.1101 0.9345 0.0338
-9.000 -0.4115 0.02048 0.01522 -0.1111 0.9281 0.0347
-8.750 -0.3862 0.01952 0.01402 -0.1109 0.9189 0.0354
-8.500 -0.3588 0.01817 0.01246 -0.1113 0.9110 0.0362
-8.250 -0.3343 0.01747 0.01174 -0.1108 0.9009 0.0371
-8.000 -0.3055 0.01693 0.01111 -0.1111 0.8926 0.0381
-7.750 -0.2829 0.01638 0.01046 -0.1100 0.8816 0.0389
-7.500 -0.2575 0.01583 0.00976 -0.1094 0.8720 0.0398
-7.250 -0.2336 0.01535 0.00913 -0.1085 0.8617 0.0405
-7.000 -0.2105 0.01460 0.00828 -0.1075 0.8522 0.0415
-6.750 -0.1864 0.01412 0.00777 -0.1067 0.8427 0.0426
-6.500 -0.1625 0.01377 0.00737 -0.1058 0.8335 0.0436
-6.250 -0.1378 0.01340 0.00692 -0.1050 0.8249 0.0447
-6.000 -0.1137 0.01307 0.00651 -0.1040 0.8163 0.0458
-5.750 -0.0894 0.01272 0.00605 -0.1031 0.8073 0.0469
-5.500 -0.0667 0.01225 0.00558 -0.1020 0.7986 0.0485
-5.250 -0.0421 0.01200 0.00530 -0.1011 0.7901 0.0501
-5.000 -0.0173 0.01176 0.00499 -0.1003 0.7827 0.0518
-4.750 0.0069 0.01148 0.00466 -0.0993 0.7748 0.0535
-4.500 0.0313 0.01118 0.00433 -0.0985 0.7679 0.0561
-4.250 0.0559 0.01099 0.00413 -0.0976 0.7598 0.0591
-4.000 0.0807 0.01074 0.00384 -0.0968 0.7531 0.0629
-3.750 0.1058 0.01057 0.00366 -0.0960 0.7461 0.0679
-3.500 0.1302 0.01032 0.00343 -0.0951 0.7387 0.0753
-3.250 0.1552 0.01013 0.00323 -0.0944 0.7319 0.0856
-3.000 0.1797 0.00992 0.00307 -0.0935 0.7243 0.0989
-2.750 0.2049 0.00976 0.00291 -0.0928 0.7176 0.1155
-2.500 0.2294 0.00956 0.00283 -0.0920 0.7107 0.1424
-2.250 0.2544 0.00942 0.00277 -0.0912 0.7034 0.1753
-2.000 0.2798 0.00933 0.00271 -0.0906 0.6964 0.2007
-1.750 0.3048 0.00922 0.00265 -0.0898 0.6886 0.2221
-1.250 0.3541 0.00897 0.00254 -0.0882 0.6738 0.2787
-1.000 0.3765 0.00870 0.00251 -0.0871 0.6661 0.3641
-0.750 0.3976 0.00839 0.00253 -0.0856 0.6581 0.4686
-0.500 0.4182 0.00815 0.00253 -0.0840 0.6497 0.5611
-0.250 0.4376 0.00789 0.00255 -0.0820 0.6414 0.6529
0.000 0.4541 0.00747 0.00259 -0.0792 0.6324 0.7948
0.250 0.5860 0.00752 0.00283 -0.1013 0.6162 0.9587
0.500 0.6275 0.00773 0.00296 -0.1039 0.6025 0.9855
0.750 0.6766 0.00789 0.00300 -0.1084 0.5869 0.9954
1.000 0.7183 0.00798 0.00298 -0.1114 0.5700 1.0000
1.250 0.7383 0.00808 0.00299 -0.1097 0.5538 1.0000
1.500 0.7582 0.00820 0.00301 -0.1080 0.5365 1.0000
1.750 0.7781 0.00835 0.00306 -0.1063 0.5192 1.0000
2.000 0.7978 0.00852 0.00312 -0.1046 0.5022 1.0000
2.250 0.8175 0.00870 0.00320 -0.1029 0.4867 1.0000
2.500 0.8371 0.00891 0.00331 -0.1011 0.4728 1.0000
2.750 0.8570 0.00911 0.00342 -0.0995 0.4609 1.0000
3.000 0.8782 0.00929 0.00355 -0.0981 0.4512 1.0000
3.250 0.8981 0.00951 0.00369 -0.0964 0.4422 1.0000
3.500 0.9198 0.00967 0.00383 -0.0952 0.4341 1.0000
3.750 0.9398 0.00990 0.00399 -0.0935 0.4261 1.0000
4.000 0.9616 0.01006 0.00414 -0.0923 0.4188 1.0000
4.250 0.9818 0.01028 0.00430 -0.0907 0.4111 1.0000
4.500 1.0028 0.01046 0.00447 -0.0893 0.4042 1.0000
4.750 1.0238 0.01064 0.00464 -0.0879 0.3972 1.0000
5.000 1.0432 0.01089 0.00483 -0.0863 0.3905 1.0000
5.250 1.0649 0.01103 0.00499 -0.0850 0.3838 1.0000
5.500 1.0843 0.01126 0.00519 -0.0834 0.3768 1.0000
5.750 1.1045 0.01145 0.00538 -0.0819 0.3700 1.0000
6.000 1.1242 0.01165 0.00558 -0.0803 0.3626 1.0000
6.250 1.1424 0.01189 0.00580 -0.0784 0.3551 1.0000
6.500 1.1610 0.01209 0.00599 -0.0766 0.3455 1.0000
6.750 1.1767 0.01233 0.00620 -0.0743 0.3356 1.0000
7.000 1.1898 0.01260 0.00643 -0.0714 0.3248 1.0000
7.250 1.2063 0.01282 0.00665 -0.0693 0.3148 1.0000
7.500 1.2207 0.01313 0.00692 -0.0668 0.3050 1.0000
7.750 1.2361 0.01344 0.00721 -0.0646 0.2953 1.0000
8.000 1.2518 0.01377 0.00753 -0.0625 0.2859 1.0000
8.500 1.2814 0.01456 0.00827 -0.0582 0.2665 1.0000
8.750 1.2956 0.01502 0.00869 -0.0561 0.2580 1.0000
9.000 1.3112 0.01544 0.00912 -0.0542 0.2504 1.0000
9.250 1.3253 0.01595 0.00961 -0.0522 0.2432 1.0000
9.500 1.3407 0.01642 0.01009 -0.0505 0.2357 1.0000
9.750 1.3536 0.01702 0.01068 -0.0484 0.2293 1.0000
10.000 1.3700 0.01749 0.01117 -0.0469 0.2226 1.0000
10.250 1.3826 0.01815 0.01182 -0.0450 0.2163 1.0000
10.500 1.3982 0.01869 0.01240 -0.0436 0.2112 1.0000
10.750 1.4127 0.01931 0.01305 -0.0420 0.2055 1.0000
11.000 1.4241 0.02012 0.01384 -0.0402 0.1993 1.0000
11.250 1.4398 0.02071 0.01449 -0.0390 0.1932 1.0000
11.500 1.4510 0.02158 0.01536 -0.0373 0.1869 1.0000
11.750 1.4647 0.02233 0.01615 -0.0360 0.1791 1.0000
12.000 1.4733 0.02343 0.01722 -0.0343 0.1706 1.0000
12.250 1.4852 0.02436 0.01818 -0.0330 0.1606 1.0000
12.500 1.4908 0.02575 0.01951 -0.0312 0.1452 1.0000
12.750 1.4910 0.02759 0.02124 -0.0292 0.1210 1.0000
13.000 1.4774 0.03057 0.02398 -0.0265 0.0886 1.0000
13.250 1.4681 0.03340 0.02673 -0.0244 0.0747 1.0000
13.500 1.4646 0.03587 0.02921 -0.0229 0.0689 1.0000
13.750 1.4642 0.03818 0.03156 -0.0217 0.0652 1.0000
14.000 1.4636 0.04059 0.03403 -0.0207 0.0625 1.0000
14.250 1.4594 0.04345 0.03695 -0.0198 0.0603 1.0000
14.500 1.4574 0.04618 0.03975 -0.0192 0.0583 1.0000
14.750 1.4578 0.04876 0.04242 -0.0187 0.0568 1.0000
15.000 1.4566 0.05158 0.04533 -0.0184 0.0555 1.0000
15.250 1.4518 0.05486 0.04868 -0.0182 0.0542 1.0000
15.500 1.4449 0.05850 0.05240 -0.0181 0.0530 1.0000
15.750 1.4350 0.06260 0.05658 -0.0183 0.0520 1.0000
16.000 1.4279 0.06646 0.06053 -0.0185 0.0511 1.0000
16.250 1.4269 0.06963 0.06381 -0.0188 0.0502 1.0000
16.500 1.4235 0.07318 0.06746 -0.0193 0.0494 1.0000
16.750 1.4185 0.07699 0.07136 -0.0199 0.0485 1.0000
17.000 1.4136 0.08083 0.07528 -0.0206 0.0475 1.0000
17.250 1.4067 0.08496 0.07950 -0.0214 0.0467 1.0000
17.500 1.3985 0.08932 0.08391 -0.0223 0.0460 1.0000
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