GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 373 AIRFOIL (goe373-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.65 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe373-il-1000000-n5.txt Download as CSV file: xf-goe373-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 373 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3439 0.11060 0.10895 -0.0178 1.0000 0.0055
-9.750 -0.3427 0.10635 0.10472 -0.0190 1.0000 0.0059
-9.500 -0.3389 0.10314 0.10152 -0.0199 1.0000 0.0062
-9.250 -0.3330 0.10069 0.09908 -0.0206 1.0000 0.0063
-9.000 -0.3277 0.09821 0.09662 -0.0211 1.0000 0.0064
-8.750 -0.3212 0.09621 0.09463 -0.0215 1.0000 0.0066
-8.500 -0.3175 0.09375 0.09219 -0.0218 1.0000 0.0068
-8.250 -0.3082 0.09074 0.08919 -0.0238 0.9991 0.0071
-8.000 -0.2984 0.08720 0.08565 -0.0266 0.9904 0.0075
-7.750 -0.2900 0.08188 0.08034 -0.0317 0.9776 0.0082
-7.500 -0.2643 0.07858 0.07703 -0.0376 0.9660 0.0084
-7.250 -0.2207 0.07411 0.07251 -0.0485 0.9516 0.0087
-7.000 -0.1705 0.06856 0.06682 -0.0621 0.9164 0.0095
-6.750 -0.1561 0.06356 0.06155 -0.0680 0.8563 0.0105
-6.500 -0.1424 0.06208 0.05991 -0.0689 0.8210 0.0107
-6.000 -0.1109 0.05730 0.05492 -0.0731 0.7790 0.0112
-5.750 -0.0922 0.05461 0.05214 -0.0757 0.7630 0.0116
-5.500 -0.0678 0.04872 0.04610 -0.0821 0.7510 0.0131
-5.250 -0.0472 0.04677 0.04406 -0.0836 0.7367 0.0132
-5.000 -0.0249 0.04476 0.04195 -0.0852 0.7213 0.0134
-4.750 -0.0015 0.04268 0.03975 -0.0870 0.7057 0.0137
-4.500 0.0236 0.04022 0.03717 -0.0890 0.6915 0.0140
-4.250 0.0499 0.03764 0.03447 -0.0909 0.6791 0.0146
-4.000 0.0826 0.03322 0.02981 -0.0940 0.6681 0.0161
-3.750 0.1064 0.03176 0.02824 -0.0946 0.6527 0.0163
-3.500 0.1310 0.03047 0.02683 -0.0952 0.6342 0.0168
-3.250 0.1573 0.02856 0.02472 -0.0959 0.6123 0.0171
-3.000 0.1844 0.02646 0.02241 -0.0965 0.5897 0.0173
-2.750 0.2116 0.02472 0.02045 -0.0968 0.5706 0.0182
-2.500 0.2392 0.02265 0.01816 -0.0970 0.5559 0.0183
-2.250 0.2710 0.02050 0.01563 -0.0965 0.5444 0.0192
-2.000 0.2977 0.01910 0.01401 -0.0964 0.5338 0.0192
-1.750 0.3227 0.01720 0.01194 -0.0966 0.5241 0.0195
-1.500 0.3484 0.01660 0.01128 -0.0967 0.5149 0.0199
-1.250 0.3745 0.01602 0.01059 -0.0966 0.5059 0.0204
-1.000 0.4015 0.01515 0.00958 -0.0964 0.4975 0.0208
-0.750 0.4293 0.01360 0.00772 -0.0958 0.4883 0.0200
-0.500 0.4560 0.01300 0.00698 -0.0956 0.4766 0.0203
-0.250 0.4829 0.01245 0.00628 -0.0953 0.4642 0.0207
0.000 0.5099 0.01193 0.00563 -0.0950 0.4537 0.0211
0.250 0.5368 0.01151 0.00508 -0.0947 0.4438 0.0214
0.500 0.5638 0.01112 0.00458 -0.0944 0.4327 0.0215
0.750 0.5906 0.01079 0.00414 -0.0941 0.4192 0.0215
1.000 0.6172 0.01062 0.00384 -0.0938 0.4023 0.0220
1.250 0.6434 0.01040 0.00350 -0.0934 0.3841 0.0219
1.500 0.6696 0.01019 0.00319 -0.0930 0.3671 0.0216
2.000 0.7224 0.00984 0.00273 -0.0923 0.3456 0.0212
2.250 0.7488 0.00972 0.00257 -0.0920 0.3378 0.0213
2.500 0.7753 0.00961 0.00245 -0.0917 0.3306 0.0214
2.750 0.8016 0.00958 0.00238 -0.0914 0.3231 0.0219
3.000 0.8282 0.00958 0.00236 -0.0911 0.3154 0.0225
3.250 0.8545 0.00967 0.00241 -0.0908 0.3057 0.0229
3.500 0.8802 0.00968 0.00238 -0.0904 0.2913 0.0234
3.750 0.9060 0.00973 0.00239 -0.0900 0.2757 0.0240
4.000 0.9309 0.00994 0.00249 -0.0896 0.2489 0.0248
4.250 0.9546 0.01032 0.00267 -0.0890 0.2052 0.0255
4.500 0.9771 0.01084 0.00296 -0.0882 0.1613 0.0255
4.750 1.0017 0.01111 0.00316 -0.0877 0.1435 0.0255
5.000 1.0263 0.01140 0.00337 -0.0871 0.1250 0.0258
5.250 1.0489 0.01192 0.00368 -0.0864 0.0895 0.0263
5.500 1.0680 0.01287 0.00432 -0.0851 0.0314 0.0271
5.750 1.0915 0.01330 0.00470 -0.0844 0.0142 0.0278
6.000 1.1162 0.01355 0.00499 -0.0838 0.0118 0.0293
6.250 1.1410 0.01378 0.00524 -0.0834 0.0111 0.0321
6.500 1.1655 0.01405 0.00555 -0.0828 0.0101 0.0332
6.750 1.1895 0.01435 0.00589 -0.0822 0.0091 0.0380
7.000 1.2149 0.01348 0.00662 -0.0825 0.0081 1.0000
7.250 1.2387 0.01381 0.00696 -0.0819 0.0078 1.0000
7.500 1.2620 0.01418 0.00737 -0.0812 0.0073 1.0000
7.750 1.2849 0.01458 0.00779 -0.0804 0.0069 1.0000
8.000 1.3075 0.01499 0.00823 -0.0797 0.0064 1.0000
8.250 1.3297 0.01542 0.00867 -0.0789 0.0059 1.0000
8.500 1.3500 0.01604 0.00935 -0.0777 0.0055 1.0000
8.750 1.3714 0.01651 0.00986 -0.0768 0.0053 1.0000
9.000 1.3919 0.01704 0.01045 -0.0758 0.0051 1.0000
9.250 1.4119 0.01759 0.01105 -0.0747 0.0049 1.0000
9.500 1.4310 0.01819 0.01172 -0.0734 0.0046 1.0000
9.750 1.4495 0.01880 0.01237 -0.0721 0.0044 1.0000
10.000 1.4674 0.01942 0.01304 -0.0708 0.0042 1.0000
10.250 1.4845 0.02005 0.01372 -0.0693 0.0041 1.0000
10.500 1.4998 0.02077 0.01450 -0.0676 0.0039 1.0000
10.750 1.5125 0.02155 0.01535 -0.0655 0.0038 1.0000
11.000 1.5163 0.02264 0.01653 -0.0620 0.0036 1.0000
11.250 1.5242 0.02349 0.01746 -0.0592 0.0035 1.0000
11.500 1.5317 0.02441 0.01846 -0.0566 0.0034 1.0000
11.750 1.5369 0.02552 0.01966 -0.0539 0.0034 1.0000
12.000 1.5434 0.02663 0.02084 -0.0517 0.0033 1.0000
12.250 1.5469 0.02802 0.02234 -0.0494 0.0032 1.0000
12.500 1.5474 0.02976 0.02419 -0.0473 0.0031 1.0000
12.750 1.5485 0.03163 0.02615 -0.0456 0.0031 1.0000
13.000 1.5484 0.03377 0.02840 -0.0442 0.0030 1.0000
13.250 1.5483 0.03610 0.03083 -0.0432 0.0029 1.0000
13.500 1.5457 0.03886 0.03370 -0.0425 0.0029 1.0000
13.750 1.5428 0.04184 0.03679 -0.0421 0.0028 1.0000
14.000 1.5383 0.04517 0.04024 -0.0420 0.0028 1.0000
14.250 1.5317 0.04897 0.04416 -0.0424 0.0028 1.0000
14.500 1.5242 0.05311 0.04842 -0.0431 0.0027 1.0000
14.750 1.5212 0.05681 0.05222 -0.0439 0.0027 1.0000
15.000 1.5146 0.06116 0.05669 -0.0451 0.0026 1.0000
15.250 1.5045 0.06617 0.06181 -0.0466 0.0026 1.0000
15.500 1.4995 0.07056 0.06631 -0.0481 0.0026 1.0000
15.750 1.4876 0.07616 0.07202 -0.0500 0.0026 1.0000
16.000 1.4764 0.08181 0.07779 -0.0522 0.0026 1.0000
16.250 1.4675 0.08726 0.08334 -0.0544 0.0025 1.0000
16.500 1.4573 0.09309 0.08929 -0.0568 0.0025 1.0000
16.750 1.4464 0.09914 0.09545 -0.0595 0.0025 1.0000
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