GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 408 AIRFOIL (goe408-il) Reynolds number: 200,000 Max Cl/Cd: 75.3 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe408-il-200000-n5.txt Download as CSV file: xf-goe408-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 408 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3873 0.09126 0.08788 -0.0205 1.0000 0.0166
-7.500 -0.3948 0.08866 0.08535 -0.0198 1.0000 0.0165
-7.250 -0.4027 0.08606 0.08280 -0.0189 1.0000 0.0165
-7.000 -0.4051 0.08280 0.07959 -0.0193 1.0000 0.0164
-6.750 -0.4062 0.07949 0.07631 -0.0199 1.0000 0.0164
-6.500 -0.4029 0.07573 0.07257 -0.0215 0.9994 0.0164
-6.250 -0.3764 0.06977 0.06654 -0.0296 0.9945 0.0165
-6.000 -0.3488 0.06227 0.05890 -0.0386 0.9884 0.0177
-5.750 -0.3230 0.05543 0.05189 -0.0450 0.9817 0.0184
-5.500 -0.2963 0.05224 0.04860 -0.0482 0.9763 0.0190
-5.000 -0.2477 0.04514 0.04121 -0.0524 0.9605 0.0214
-4.750 -0.2284 0.03800 0.03362 -0.0533 0.9487 0.0240
-4.500 -0.2065 0.03574 0.03119 -0.0532 0.9381 0.0253
-4.000 -0.1590 0.02880 0.02352 -0.0524 0.9186 0.0317
-3.750 -0.1317 0.02803 0.02266 -0.0527 0.9076 0.0338
-3.500 -0.1058 0.02422 0.01819 -0.0518 0.8986 0.0392
-3.250 -0.0724 0.02361 0.01754 -0.0533 0.8894 0.0411
-3.000 -0.0408 0.02224 0.01585 -0.0540 0.8791 0.0449
-2.750 -0.0054 0.02036 0.01344 -0.0549 0.8700 0.0471
-2.500 0.0306 0.01862 0.01140 -0.0568 0.8592 0.0491
-2.250 0.0703 0.01759 0.01019 -0.0594 0.8470 0.0507
-2.000 0.1142 0.01643 0.00875 -0.0627 0.8337 0.0516
-1.750 0.1606 0.01548 0.00755 -0.0667 0.8193 0.0527
-1.500 0.2064 0.01473 0.00657 -0.0706 0.8038 0.0538
-1.250 0.2468 0.01418 0.00582 -0.0732 0.7871 0.0550
-1.000 0.2828 0.01385 0.00532 -0.0749 0.7702 0.0571
-0.750 0.3151 0.01353 0.00486 -0.0758 0.7547 0.0583
-0.500 0.3448 0.01323 0.00445 -0.0761 0.7401 0.0588
-0.250 0.3727 0.01298 0.00412 -0.0760 0.7259 0.0593
0.000 0.3988 0.01262 0.00372 -0.0756 0.7126 0.0606
0.250 0.4238 0.01241 0.00347 -0.0749 0.6995 0.0621
0.500 0.4485 0.01228 0.00331 -0.0742 0.6870 0.0636
0.750 0.4730 0.01221 0.00319 -0.0733 0.6749 0.0655
1.000 0.4968 0.01216 0.00310 -0.0724 0.6621 0.0674
1.250 0.5204 0.01214 0.00304 -0.0714 0.6492 0.0713
1.500 0.5439 0.01211 0.00301 -0.0703 0.6366 0.0763
1.750 0.5674 0.01212 0.00300 -0.0693 0.6237 0.0803
2.000 0.5909 0.01213 0.00301 -0.0682 0.6109 0.0905
2.250 0.6142 0.01214 0.00304 -0.0672 0.5977 0.1152
2.750 0.8175 0.01133 0.00379 -0.1019 0.5274 1.0000
3.000 0.8387 0.01155 0.00391 -0.1004 0.5055 1.0000
3.250 0.8600 0.01177 0.00403 -0.0990 0.4861 1.0000
3.500 0.8822 0.01198 0.00419 -0.0977 0.4714 1.0000
3.750 0.9044 0.01219 0.00438 -0.0965 0.4572 1.0000
4.000 0.9264 0.01242 0.00457 -0.0953 0.4433 1.0000
4.250 0.9484 0.01266 0.00478 -0.0940 0.4302 1.0000
4.500 0.9704 0.01290 0.00501 -0.0928 0.4173 1.0000
4.750 0.9917 0.01317 0.00527 -0.0914 0.4021 1.0000
5.000 1.0118 0.01347 0.00552 -0.0899 0.3809 1.0000
5.250 1.0316 0.01380 0.00579 -0.0882 0.3603 1.0000
5.500 1.0516 0.01412 0.00608 -0.0866 0.3379 1.0000
5.750 1.0714 0.01446 0.00642 -0.0850 0.3185 1.0000
6.000 1.0908 0.01482 0.00676 -0.0834 0.2971 1.0000
6.250 1.1095 0.01523 0.00714 -0.0816 0.2748 1.0000
6.500 1.1271 0.01571 0.00755 -0.0797 0.2496 1.0000
6.750 1.1440 0.01624 0.00802 -0.0777 0.2259 1.0000
7.250 1.1753 0.01748 0.00911 -0.0733 0.1782 1.0000
7.500 1.1891 0.01821 0.00972 -0.0709 0.1533 1.0000
7.750 1.2044 0.01884 0.01032 -0.0687 0.1344 1.0000
8.000 1.2189 0.01952 0.01094 -0.0663 0.1145 1.0000
8.250 1.2300 0.02041 0.01166 -0.0635 0.0730 1.0000
8.500 1.2361 0.02155 0.01265 -0.0599 0.0537 1.0000
8.750 1.2453 0.02239 0.01354 -0.0566 0.0429 1.0000
9.000 1.2534 0.02329 0.01448 -0.0531 0.0329 1.0000
9.250 1.2616 0.02419 0.01541 -0.0499 0.0258 1.0000
9.500 1.2680 0.02524 0.01648 -0.0463 0.0212 1.0000
9.750 1.2758 0.02619 0.01755 -0.0431 0.0193 1.0000
10.000 1.2821 0.02724 0.01871 -0.0399 0.0174 1.0000
10.250 1.2840 0.02861 0.02016 -0.0362 0.0152 1.0000
10.500 1.2851 0.03005 0.02174 -0.0326 0.0145 1.0000
10.750 1.2885 0.03139 0.02324 -0.0295 0.0140 1.0000
11.000 1.2901 0.03294 0.02498 -0.0265 0.0133 1.0000
11.250 1.2904 0.03468 0.02687 -0.0237 0.0130 1.0000
11.500 1.2904 0.03657 0.02890 -0.0213 0.0127 1.0000
11.750 1.2892 0.03871 0.03118 -0.0191 0.0122 1.0000
12.000 1.2882 0.04098 0.03357 -0.0173 0.0117 1.0000
12.250 1.2875 0.04333 0.03605 -0.0160 0.0113 1.0000
12.500 1.2838 0.04613 0.03895 -0.0148 0.0107 1.0000
12.750 1.2752 0.04962 0.04254 -0.0139 0.0100 1.0000
13.000 1.2721 0.05269 0.04574 -0.0130 0.0100 1.0000
13.250 1.2713 0.05553 0.04875 -0.0125 0.0099 1.0000
13.500 1.2697 0.05856 0.05194 -0.0122 0.0097 1.0000
13.750 1.2661 0.06195 0.05551 -0.0119 0.0095 1.0000
14.000 1.2612 0.06559 0.05934 -0.0120 0.0091 1.0000
14.250 1.2564 0.06932 0.06324 -0.0122 0.0091 1.0000
14.500 1.2502 0.07333 0.06741 -0.0126 0.0090 1.0000
14.750 1.2432 0.07759 0.07185 -0.0134 0.0088 1.0000
15.000 1.2354 0.08211 0.07657 -0.0145 0.0087 1.0000
15.250 1.2253 0.08718 0.08183 -0.0159 0.0086 1.0000
15.500 1.2157 0.09231 0.08713 -0.0176 0.0085 1.0000
15.750 1.2046 0.09788 0.09288 -0.0195 0.0087 1.0000
16.000 1.1931 0.10374 0.09891 -0.0220 0.0086 1.0000
16.250 1.1786 0.11042 0.10577 -0.0250 0.0084 1.0000
16.500 1.1654 0.11703 0.11255 -0.0281 0.0084 1.0000
16.750 1.1494 0.12454 0.12024 -0.0319 0.0084 1.0000
17.000 1.1350 0.13201 0.12787 -0.0358 0.0085 1.0000
17.250 1.1174 0.14060 0.13663 -0.0405 0.0085 1.0000
17.500 1.0995 0.14974 0.14589 -0.0456 0.0086 1.0000
17.750 1.0818 0.15932 0.15561 -0.0510 0.0088 1.0000
18.000 1.0582 0.17159 0.16802 -0.0579 0.0089 1.0000
18.250 1.0324 0.18567 0.18217 -0.0654 0.0093 1.0000
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