GOE 14K AIRFOIL (goe14k-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 14K AIRFOIL (goe14k-il) Reynolds number: 100,000 Max Cl/Cd: 38.77 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe14k-il-100000-n5.txt Download as CSV file: xf-goe14k-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 14K 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5407 0.09740 0.09265 -0.0508 0.9907 0.0282
-10.000 -0.5508 0.09035 0.08564 -0.0554 0.9881 0.0280
-9.750 -0.5704 0.08070 0.07601 -0.0628 0.9844 0.0278
-9.500 -0.5923 0.07320 0.06841 -0.0676 0.9798 0.0272
-9.250 -0.6236 0.06797 0.06304 -0.0661 0.9747 0.0271
-9.000 -0.6489 0.06455 0.05945 -0.0622 0.9697 0.0268
-8.750 -0.6706 0.06053 0.05521 -0.0580 0.9651 0.0268
-8.500 -0.6875 0.05659 0.05095 -0.0536 0.9598 0.0269
-8.250 -0.6986 0.05208 0.04597 -0.0497 0.9562 0.0273
-8.000 -0.7121 0.04913 0.04266 -0.0436 0.9517 0.0276
-7.750 -0.7167 0.04609 0.03911 -0.0388 0.9481 0.0283
-7.500 -0.7143 0.04315 0.03570 -0.0352 0.9453 0.0295
-7.250 -0.7035 0.04129 0.03363 -0.0330 0.9430 0.0309
-7.000 -0.7005 0.04007 0.03220 -0.0287 0.9395 0.0320
-6.750 -0.6919 0.03855 0.03039 -0.0254 0.9369 0.0331
-6.500 -0.6792 0.03706 0.02858 -0.0227 0.9346 0.0353
-6.250 -0.6619 0.03552 0.02663 -0.0208 0.9326 0.0381
-6.000 -0.6399 0.03406 0.02466 -0.0195 0.9310 0.0414
-5.750 -0.6192 0.03281 0.02329 -0.0185 0.9294 0.0447
-5.500 -0.6095 0.03224 0.02262 -0.0152 0.9265 0.0483
-5.250 -0.5921 0.03137 0.02146 -0.0131 0.9242 0.0533
-4.750 -0.5491 0.02988 0.01967 -0.0111 0.9199 0.0655
-4.500 -0.5257 0.02914 0.01888 -0.0105 0.9183 0.0713
-4.250 -0.5007 0.02870 0.01829 -0.0102 0.9169 0.0789
-4.000 -0.4746 0.02812 0.01770 -0.0102 0.9156 0.0859
-3.750 -0.4636 0.02778 0.01725 -0.0070 0.9118 0.0918
-3.500 -0.4461 0.02734 0.01682 -0.0052 0.9091 0.0982
-3.250 -0.4238 0.02703 0.01642 -0.0043 0.9066 0.1065
-3.000 -0.3990 0.02666 0.01604 -0.0039 0.9045 0.1143
-2.750 -0.3718 0.02636 0.01574 -0.0040 0.9028 0.1269
-2.500 -0.3417 0.02603 0.01550 -0.0048 0.9013 0.1557
-2.250 -0.3243 0.02569 0.01536 -0.0031 0.8977 0.2026
-2.000 -0.3000 0.02535 0.01532 -0.0030 0.8947 0.2761
-1.750 -0.0402 0.02514 0.01747 -0.0539 0.9114 0.8982
-1.500 -0.0168 0.02591 0.01810 -0.0529 0.9086 0.9607
-1.250 0.0934 0.02712 0.01903 -0.0708 0.9155 1.0000
-1.000 0.1004 0.02722 0.01904 -0.0671 0.9097 1.0000
-0.750 0.1223 0.02730 0.01901 -0.0664 0.9062 1.0000
-0.500 0.1484 0.02738 0.01898 -0.0665 0.9037 1.0000
-0.250 0.1770 0.02747 0.01898 -0.0671 0.9017 1.0000
0.000 0.1888 0.02766 0.01911 -0.0643 0.8967 1.0000
0.250 0.2080 0.02781 0.01920 -0.0630 0.8926 1.0000
0.500 0.2332 0.02794 0.01928 -0.0629 0.8897 1.0000
0.750 0.2619 0.02805 0.01935 -0.0635 0.8874 1.0000
1.000 0.2776 0.02828 0.01956 -0.0615 0.8828 1.0000
1.250 0.2950 0.02849 0.01976 -0.0599 0.8779 1.0000
1.500 0.3211 0.02863 0.01989 -0.0599 0.8747 1.0000
1.750 0.3518 0.02871 0.01998 -0.0608 0.8723 1.0000
2.000 0.3643 0.02893 0.02021 -0.0581 0.8650 1.0000
2.250 0.3933 0.02890 0.02021 -0.0585 0.8600 1.0000
2.500 0.4307 0.02872 0.02008 -0.0605 0.8568 1.0000
2.750 0.4415 0.02894 0.02034 -0.0574 0.8477 1.0000
3.000 0.4746 0.02880 0.02026 -0.0585 0.8435 1.0000
3.250 0.4941 0.02885 0.02039 -0.0570 0.8357 1.0000
3.500 0.5232 0.02870 0.02032 -0.0572 0.8297 1.0000
3.750 0.5607 0.02839 0.02012 -0.0589 0.8264 1.0000
4.000 0.5738 0.02848 0.02031 -0.0561 0.8152 1.0000
4.250 0.6023 0.02794 0.01988 -0.0557 0.8044 1.0000
4.500 0.6365 0.02678 0.01884 -0.0556 0.7893 1.0000
4.750 0.6635 0.02578 0.01796 -0.0543 0.7718 1.0000
5.000 0.6893 0.02461 0.01690 -0.0523 0.7502 1.0000
5.250 0.6912 0.02488 0.01725 -0.0472 0.7227 1.0000
5.500 0.7005 0.02511 0.01760 -0.0437 0.6975 1.0000
5.750 0.7277 0.02434 0.01693 -0.0424 0.6618 1.0000
6.000 0.8254 0.02129 0.01268 -0.0517 0.4361 1.0000
6.250 0.8321 0.02225 0.01322 -0.0478 0.3574 1.0000
6.500 0.8380 0.02328 0.01383 -0.0440 0.2746 1.0000
6.750 0.8461 0.02431 0.01450 -0.0408 0.2127 1.0000
7.000 0.8563 0.02530 0.01522 -0.0380 0.1682 1.0000
7.250 0.8681 0.02618 0.01594 -0.0355 0.1382 1.0000
7.500 0.8804 0.02701 0.01667 -0.0330 0.1166 1.0000
7.750 0.8928 0.02783 0.01745 -0.0306 0.1009 1.0000
8.000 0.9049 0.02867 0.01827 -0.0282 0.0871 1.0000
8.250 0.9163 0.02961 0.01922 -0.0257 0.0764 1.0000
8.500 0.9277 0.03058 0.02021 -0.0232 0.0657 1.0000
8.750 0.9379 0.03167 0.02130 -0.0206 0.0574 1.0000
9.000 0.9508 0.03265 0.02241 -0.0183 0.0495 1.0000
9.250 0.9615 0.03379 0.02354 -0.0160 0.0449 1.0000
9.500 0.9759 0.03492 0.02488 -0.0139 0.0405 1.0000
9.750 0.9893 0.03605 0.02611 -0.0119 0.0363 1.0000
10.000 1.0015 0.03737 0.02750 -0.0098 0.0337 1.0000
10.250 1.0173 0.03903 0.02926 -0.0083 0.0314 1.0000
10.500 1.0359 0.04068 0.03117 -0.0070 0.0295 1.0000
10.750 1.0492 0.04214 0.03283 -0.0051 0.0273 1.0000
11.000 1.0615 0.04373 0.03460 -0.0032 0.0261 1.0000
11.250 1.0705 0.04539 0.03645 -0.0010 0.0250 1.0000
11.500 1.0785 0.04742 0.03865 0.0013 0.0241 1.0000
11.750 1.0841 0.05008 0.04151 0.0036 0.0233 1.0000
12.000 1.0848 0.05284 0.04458 0.0066 0.0227 1.0000
12.250 1.0802 0.05561 0.04771 0.0100 0.0221 1.0000
12.500 1.0733 0.05811 0.05053 0.0134 0.0214 1.0000
12.750 1.0626 0.06123 0.05396 0.0168 0.0209 1.0000
13.000 1.0499 0.06445 0.05746 0.0198 0.0205 1.0000
13.250 1.0343 0.06816 0.06144 0.0226 0.0207 1.0000
13.500 1.0167 0.07214 0.06568 0.0248 0.0208 1.0000
13.750 0.9946 0.07679 0.07058 0.0264 0.0207 1.0000
14.000 0.9721 0.08174 0.07577 0.0271 0.0205 1.0000
14.250 0.9472 0.08760 0.08185 0.0267 0.0206 1.0000
14.500 0.9185 0.09482 0.08928 0.0246 0.0207 1.0000
14.750 0.8879 0.10363 0.09827 0.0207 0.0212 1.0000
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