GOE 546 AIRFOIL (goe546-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 546 AIRFOIL (goe546-il) Reynolds number: 500,000 Max Cl/Cd: 93.53 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe546-il-500000-n5.txt Download as CSV file: xf-goe546-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 546 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.8554 0.03791 0.03512 -0.0807 1.0000 0.0108
-12.000 -0.8643 0.03302 0.02987 -0.0826 0.9981 0.0110
-11.750 -0.8465 0.02923 0.02568 -0.0863 0.9938 0.0114
-11.500 -0.8260 0.02672 0.02290 -0.0883 0.9894 0.0118
-11.250 -0.7989 0.02545 0.02152 -0.0900 0.9865 0.0123
-11.000 -0.7733 0.02437 0.02032 -0.0909 0.9825 0.0127
-10.750 -0.7470 0.02326 0.01905 -0.0919 0.9783 0.0133
-10.500 -0.7189 0.02196 0.01755 -0.0933 0.9754 0.0139
-10.250 -0.6959 0.02069 0.01606 -0.0935 0.9685 0.0146
-9.750 -0.6398 0.01919 0.01437 -0.0950 0.9587 0.0158
-9.500 -0.6086 0.01880 0.01391 -0.0961 0.9544 0.0166
-9.250 -0.5755 0.01822 0.01321 -0.0977 0.9513 0.0176
-9.000 -0.5459 0.01740 0.01219 -0.0986 0.9457 0.0186
-8.750 -0.5140 0.01674 0.01144 -0.0999 0.9412 0.0194
-8.500 -0.4794 0.01639 0.01103 -0.1017 0.9373 0.0202
-8.250 -0.4472 0.01608 0.01066 -0.1028 0.9314 0.0212
-8.000 -0.4144 0.01559 0.01005 -0.1041 0.9256 0.0224
-7.750 -0.3827 0.01509 0.00938 -0.1052 0.9201 0.0233
-7.500 -0.3546 0.01444 0.00861 -0.1056 0.9136 0.0242
-7.250 -0.3248 0.01410 0.00823 -0.1062 0.9081 0.0252
-7.000 -0.2971 0.01382 0.00789 -0.1064 0.9026 0.0261
-6.750 -0.2698 0.01347 0.00746 -0.1064 0.8969 0.0271
-6.500 -0.2418 0.01312 0.00701 -0.1065 0.8917 0.0281
-6.250 -0.2157 0.01282 0.00661 -0.1062 0.8860 0.0290
-6.000 -0.1889 0.01252 0.00622 -0.1060 0.8804 0.0295
-5.500 -0.1378 0.01155 0.00517 -0.1053 0.8703 0.0317
-5.250 -0.1114 0.01127 0.00484 -0.1051 0.8648 0.0326
-5.000 -0.0846 0.01099 0.00449 -0.1049 0.8599 0.0335
-4.750 -0.0587 0.01071 0.00418 -0.1045 0.8543 0.0344
-4.500 -0.0321 0.01048 0.00390 -0.1042 0.8489 0.0355
-4.250 -0.0053 0.01027 0.00363 -0.1039 0.8437 0.0364
-4.000 0.0209 0.01006 0.00337 -0.1035 0.8374 0.0369
-3.750 0.0472 0.00977 0.00302 -0.1032 0.8311 0.0383
-3.500 0.0733 0.00954 0.00277 -0.1027 0.8230 0.0399
-3.250 0.0998 0.00938 0.00256 -0.1024 0.8142 0.0416
-3.000 0.1261 0.00923 0.00238 -0.1020 0.8049 0.0437
-2.750 0.1529 0.00911 0.00221 -0.1016 0.7973 0.0460
-2.500 0.1794 0.00894 0.00205 -0.1013 0.7886 0.0511
-2.250 0.2061 0.00883 0.00192 -0.1009 0.7801 0.0569
-2.000 0.2326 0.00870 0.00180 -0.1006 0.7706 0.0683
-1.750 0.2589 0.00855 0.00168 -0.1002 0.7606 0.0884
-1.500 0.2846 0.00831 0.00158 -0.0998 0.7498 0.1391
-1.250 0.3095 0.00797 0.00149 -0.0993 0.7379 0.2346
-1.000 0.3349 0.00775 0.00145 -0.0989 0.7254 0.3046
-0.750 0.3603 0.00761 0.00143 -0.0984 0.7120 0.3618
-0.500 0.3852 0.00746 0.00145 -0.0978 0.6977 0.4322
-0.250 0.4097 0.00735 0.00148 -0.0971 0.6829 0.5032
0.000 0.4341 0.00726 0.00151 -0.0963 0.6684 0.5603
0.250 0.4585 0.00722 0.00154 -0.0955 0.6537 0.6062
0.500 0.4832 0.00720 0.00158 -0.0948 0.6406 0.6465
0.750 0.5077 0.00717 0.00163 -0.0940 0.6296 0.6887
1.000 0.5310 0.00705 0.00170 -0.0929 0.6191 0.7567
1.250 0.5529 0.00688 0.00179 -0.0912 0.6091 0.8647
1.500 0.6002 0.00690 0.00186 -0.0954 0.5932 0.9560
1.750 0.6395 0.00708 0.00193 -0.0980 0.5693 1.0000
2.000 0.6631 0.00723 0.00199 -0.0970 0.5507 1.0000
2.250 0.6865 0.00739 0.00206 -0.0960 0.5286 1.0000
2.500 0.7091 0.00761 0.00215 -0.0949 0.5020 1.0000
3.000 0.7548 0.00807 0.00238 -0.0929 0.4528 1.0000
3.250 0.7772 0.00834 0.00253 -0.0918 0.4277 1.0000
3.500 0.8002 0.00861 0.00269 -0.0908 0.4043 1.0000
3.750 0.8215 0.00897 0.00290 -0.0896 0.3700 1.0000
4.000 0.8417 0.00943 0.00313 -0.0882 0.3240 1.0000
4.250 0.8606 0.01001 0.00343 -0.0867 0.2700 1.0000
4.500 0.8810 0.01049 0.00373 -0.0854 0.2351 1.0000
4.750 0.9025 0.01090 0.00403 -0.0842 0.2094 1.0000
5.000 0.9234 0.01134 0.00433 -0.0831 0.1796 1.0000
5.250 0.9397 0.01212 0.00478 -0.0812 0.1186 1.0000
5.500 0.9577 0.01278 0.00525 -0.0795 0.0827 1.0000
5.750 0.9766 0.01336 0.00567 -0.0780 0.0532 1.0000
6.000 0.9969 0.01382 0.00605 -0.0767 0.0426 1.0000
6.250 1.0184 0.01418 0.00641 -0.0756 0.0397 1.0000
6.500 1.0396 0.01455 0.00679 -0.0745 0.0375 1.0000
6.750 1.0605 0.01493 0.00719 -0.0733 0.0359 1.0000
7.000 1.0815 0.01528 0.00758 -0.0721 0.0354 1.0000
7.250 1.1019 0.01565 0.00800 -0.0709 0.0348 1.0000
7.500 1.1216 0.01605 0.00845 -0.0695 0.0339 1.0000
7.750 1.1399 0.01646 0.00890 -0.0679 0.0332 1.0000
8.000 1.1570 0.01690 0.00939 -0.0661 0.0325 1.0000
8.250 1.1732 0.01738 0.00991 -0.0641 0.0318 1.0000
8.500 1.1886 0.01791 0.01048 -0.0621 0.0309 1.0000
8.750 1.2029 0.01850 0.01112 -0.0600 0.0300 1.0000
9.000 1.2152 0.01922 0.01188 -0.0576 0.0290 1.0000
9.250 1.2246 0.02010 0.01282 -0.0548 0.0280 1.0000
9.500 1.2413 0.02058 0.01336 -0.0533 0.0276 1.0000
9.750 1.2562 0.02117 0.01401 -0.0515 0.0270 1.0000
10.000 1.2708 0.02178 0.01470 -0.0498 0.0263 1.0000
10.250 1.2849 0.02244 0.01542 -0.0481 0.0255 1.0000
10.500 1.2975 0.02321 0.01625 -0.0462 0.0248 1.0000
10.750 1.3105 0.02397 0.01706 -0.0445 0.0239 1.0000
11.000 1.3231 0.02478 0.01791 -0.0429 0.0231 1.0000
11.250 1.3329 0.02580 0.01898 -0.0410 0.0225 1.0000
11.500 1.3395 0.02709 0.02034 -0.0390 0.0216 1.0000
11.750 1.3537 0.02786 0.02120 -0.0377 0.0211 1.0000
12.000 1.3659 0.02880 0.02223 -0.0364 0.0204 1.0000
12.250 1.3784 0.02973 0.02323 -0.0351 0.0194 1.0000
12.500 1.3895 0.03080 0.02437 -0.0339 0.0187 1.0000
12.750 1.4016 0.03181 0.02543 -0.0328 0.0179 1.0000
13.000 1.4117 0.03300 0.02667 -0.0316 0.0172 1.0000
13.250 1.4202 0.03437 0.02811 -0.0305 0.0165 1.0000
13.500 1.4279 0.03586 0.02971 -0.0293 0.0158 1.0000
13.750 1.4364 0.03732 0.03124 -0.0284 0.0150 1.0000
14.000 1.4454 0.03876 0.03274 -0.0276 0.0142 1.0000
14.250 1.4519 0.04048 0.03452 -0.0268 0.0137 1.0000
14.500 1.4569 0.04241 0.03651 -0.0260 0.0131 1.0000
14.750 1.4600 0.04462 0.03883 -0.0254 0.0127 1.0000
15.000 1.4624 0.04697 0.04131 -0.0249 0.0122 1.0000
15.250 1.4644 0.04945 0.04389 -0.0246 0.0118 1.0000
15.500 1.4672 0.05194 0.04647 -0.0244 0.0112 1.0000
15.750 1.4679 0.05476 0.04938 -0.0245 0.0109 1.0000
16.000 1.4670 0.05785 0.05256 -0.0247 0.0105 1.0000
16.250 1.4645 0.06127 0.05608 -0.0251 0.0101 1.0000
16.500 1.4618 0.06481 0.05974 -0.0257 0.0098 1.0000
16.750 1.4580 0.06861 0.06366 -0.0265 0.0096 1.0000
17.000 1.4532 0.07265 0.06784 -0.0275 0.0094 1.0000
17.250 1.4475 0.07698 0.07230 -0.0287 0.0091 1.0000
17.500 1.4411 0.08154 0.07699 -0.0302 0.0089 1.0000
17.750 1.4336 0.08641 0.08199 -0.0320 0.0088 1.0000
18.000 1.4250 0.09159 0.08730 -0.0341 0.0085 1.0000
18.250 1.4156 0.09706 0.09290 -0.0364 0.0085 1.0000
18.500 1.4051 0.10286 0.09882 -0.0390 0.0083 1.0000
18.750 1.3935 0.10898 0.10507 -0.0420 0.0082 1.0000
19.000 1.3811 0.11539 0.11162 -0.0452 0.0081 1.0000
19.250 1.3681 0.12209 0.11845 -0.0487 0.0080 1.0000
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