GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Reynolds number: 500,000 Max Cl/Cd: 98.33 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe325-il-500000-n5.txt Download as CSV file: xf-goe325-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 325 (PFALZ 54) 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3468 0.10055 0.09836 -0.0215 1.0000 0.0075
-8.750 -0.3437 0.09674 0.09457 -0.0232 1.0000 0.0077
-8.500 -0.3421 0.09291 0.09076 -0.0248 1.0000 0.0078
-8.000 -0.3345 0.08563 0.08354 -0.0292 0.9951 0.0085
-7.750 -0.3193 0.08271 0.08061 -0.0329 0.9891 0.0088
-7.500 -0.3029 0.07873 0.07663 -0.0382 0.9830 0.0090
-7.250 -0.2846 0.07390 0.07179 -0.0451 0.9769 0.0093
-7.000 -0.2669 0.06894 0.06680 -0.0518 0.9699 0.0096
-6.750 -0.2464 0.06312 0.06094 -0.0596 0.9631 0.0101
-6.500 -0.2245 0.05277 0.05045 -0.0719 0.9540 0.0113
-6.250 -0.2023 0.05058 0.04821 -0.0742 0.9459 0.0117
-6.000 -0.1794 0.04791 0.04544 -0.0767 0.9371 0.0123
-5.750 -0.1550 0.04353 0.04092 -0.0805 0.9260 0.0131
-5.500 -0.1244 0.03138 0.02821 -0.0886 0.9172 0.0157
-5.250 -0.1004 0.03082 0.02759 -0.0884 0.9043 0.0163
-5.000 -0.0755 0.02916 0.02577 -0.0887 0.8889 0.0172
-4.750 -0.0478 0.01857 0.01409 -0.0910 0.8767 0.0216
-4.500 -0.0223 0.01814 0.01354 -0.0907 0.8559 0.0223
-4.250 0.0032 0.01770 0.01290 -0.0902 0.8272 0.0229
-4.000 0.0286 0.01725 0.01220 -0.0898 0.7917 0.0238
-3.750 0.0544 0.01668 0.01131 -0.0894 0.7537 0.0250
-3.500 0.0809 0.01558 0.00981 -0.0892 0.7200 0.0260
-3.250 0.1079 0.01466 0.00853 -0.0890 0.6880 0.0269
-3.000 0.1349 0.01417 0.00775 -0.0888 0.6523 0.0280
-2.750 0.1617 0.01371 0.00697 -0.0886 0.6084 0.0286
-2.250 0.2160 0.01301 0.00575 -0.0884 0.5499 0.0293
-2.000 0.2437 0.01270 0.00527 -0.0883 0.5351 0.0296
-1.750 0.2714 0.01239 0.00482 -0.0883 0.5228 0.0297
-1.500 0.2991 0.01190 0.00419 -0.0883 0.5117 0.0300
-1.250 0.3268 0.01131 0.00349 -0.0883 0.5016 0.0310
-1.000 0.3547 0.01100 0.00310 -0.0883 0.4930 0.0313
-0.750 0.3826 0.01077 0.00279 -0.0883 0.4839 0.0317
-0.500 0.4107 0.01056 0.00253 -0.0883 0.4746 0.0322
-0.250 0.4387 0.01042 0.00233 -0.0883 0.4648 0.0330
0.000 0.4667 0.01033 0.00218 -0.0883 0.4543 0.0342
0.250 0.4948 0.01026 0.00208 -0.0884 0.4444 0.0357
0.500 0.5228 0.01024 0.00200 -0.0884 0.4337 0.0372
0.750 0.5506 0.01025 0.00195 -0.0884 0.4213 0.0387
1.000 0.5784 0.01028 0.00191 -0.0884 0.4076 0.0403
1.500 0.6337 0.01037 0.00193 -0.0884 0.3809 0.0528
1.750 0.6614 0.01037 0.00200 -0.0884 0.3697 0.0987
2.250 0.7099 0.00867 0.00228 -0.0874 0.3514 1.0000
2.500 0.7374 0.00882 0.00235 -0.0874 0.3430 1.0000
2.750 0.7647 0.00901 0.00246 -0.0873 0.3350 1.0000
3.000 0.7922 0.00915 0.00256 -0.0873 0.3283 1.0000
3.250 0.8194 0.00933 0.00268 -0.0872 0.3223 1.0000
3.500 0.8468 0.00948 0.00281 -0.0872 0.3173 1.0000
3.750 0.8742 0.00964 0.00294 -0.0871 0.3122 1.0000
4.000 0.9012 0.00982 0.00310 -0.0871 0.3074 1.0000
4.250 0.9284 0.00998 0.00326 -0.0870 0.3032 1.0000
4.500 0.9556 0.01015 0.00342 -0.0869 0.2986 1.0000
4.750 0.9825 0.01034 0.00360 -0.0869 0.2940 1.0000
5.000 1.0093 0.01053 0.00380 -0.0868 0.2889 1.0000
5.250 1.0361 0.01072 0.00398 -0.0867 0.2801 1.0000
5.500 1.0627 0.01093 0.00417 -0.0866 0.2719 1.0000
5.750 1.0891 0.01115 0.00438 -0.0864 0.2640 1.0000
6.000 1.1156 0.01135 0.00460 -0.0863 0.2561 1.0000
6.250 1.1416 0.01161 0.00483 -0.0861 0.2451 1.0000
6.500 1.1672 0.01190 0.00508 -0.0859 0.2277 1.0000
6.750 1.1913 0.01237 0.00541 -0.0856 0.1986 1.0000
7.000 1.2026 0.01454 0.00675 -0.0837 0.0687 1.0000
7.250 1.2212 0.01570 0.00767 -0.0826 0.0224 1.0000
7.500 1.2440 0.01628 0.00826 -0.0819 0.0154 1.0000
7.750 1.2667 0.01684 0.00888 -0.0812 0.0129 1.0000
8.000 1.2886 0.01749 0.00963 -0.0804 0.0109 1.0000
8.250 1.3111 0.01800 0.01022 -0.0797 0.0102 1.0000
8.500 1.3327 0.01859 0.01090 -0.0789 0.0095 1.0000
8.750 1.3534 0.01924 0.01162 -0.0780 0.0087 1.0000
9.000 1.3726 0.02000 0.01245 -0.0769 0.0080 1.0000
9.250 1.3890 0.02097 0.01353 -0.0754 0.0073 1.0000
9.500 1.4069 0.02174 0.01440 -0.0742 0.0070 1.0000
9.750 1.4229 0.02260 0.01537 -0.0726 0.0066 1.0000
10.000 1.4370 0.02355 0.01641 -0.0709 0.0063 1.0000
10.250 1.4489 0.02456 0.01751 -0.0688 0.0060 1.0000
10.500 1.4566 0.02560 0.01865 -0.0661 0.0058 1.0000
10.750 1.4630 0.02678 0.01991 -0.0634 0.0056 1.0000
11.000 1.4679 0.02811 0.02134 -0.0609 0.0055 1.0000
11.250 1.4697 0.02976 0.02308 -0.0583 0.0053 1.0000
11.500 1.4654 0.03202 0.02547 -0.0556 0.0051 1.0000
11.750 1.4672 0.03399 0.02757 -0.0539 0.0049 1.0000
12.000 1.4681 0.03620 0.02992 -0.0525 0.0048 1.0000
12.250 1.4686 0.03868 0.03253 -0.0516 0.0047 1.0000
12.500 1.4665 0.04169 0.03567 -0.0511 0.0045 1.0000
12.750 1.4627 0.04516 0.03928 -0.0511 0.0045 1.0000
13.000 1.4579 0.04900 0.04326 -0.0515 0.0044 1.0000
13.250 1.4523 0.05312 0.04751 -0.0523 0.0043 1.0000
13.500 1.4467 0.05741 0.05193 -0.0532 0.0042 1.0000
13.750 1.4400 0.06189 0.05653 -0.0543 0.0042 1.0000
14.000 1.4330 0.06638 0.06114 -0.0553 0.0041 1.0000
14.250 1.4252 0.07096 0.06584 -0.0563 0.0040 1.0000
14.500 1.4179 0.07549 0.07048 -0.0574 0.0040 1.0000
14.750 1.4104 0.08007 0.07517 -0.0585 0.0039 1.0000
15.000 1.4033 0.08469 0.07989 -0.0596 0.0039 1.0000
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Polar data table (+)
Polar graphs
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