GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 374 AIRFOIL (goe374-il) Reynolds number: 500,000 Max Cl/Cd: 97.07 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe374-il-500000-n5.txt Download as CSV file: xf-goe374-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 374 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3157 0.09211 0.09000 -0.0203 1.0000 0.0065
-7.500 -0.3165 0.08984 0.08777 -0.0199 1.0000 0.0065
-7.250 -0.3197 0.08767 0.08565 -0.0193 1.0000 0.0065
-7.000 -0.3036 0.08374 0.08174 -0.0239 0.9949 0.0065
-6.750 -0.2894 0.07939 0.07740 -0.0264 0.9883 0.0069
-6.500 -0.2675 0.07595 0.07394 -0.0315 0.9799 0.0076
-6.250 -0.2411 0.07173 0.06970 -0.0382 0.9712 0.0080
-5.750 -0.1651 0.06257 0.06041 -0.0569 0.9497 0.0096
-4.250 -0.0080 0.03811 0.03511 -0.0775 0.8522 0.0064
-4.000 0.0176 0.03465 0.03143 -0.0785 0.8360 0.0065
-3.750 0.0430 0.03120 0.02774 -0.0791 0.8200 0.0066
-3.500 0.0663 0.02989 0.02628 -0.0792 0.8020 0.0073
-3.250 0.0915 0.02785 0.02401 -0.0791 0.7825 0.0081
-3.000 0.1177 0.02509 0.02095 -0.0787 0.7608 0.0085
-2.750 0.1435 0.02226 0.01773 -0.0779 0.7351 0.0087
-2.500 0.1691 0.01916 0.01414 -0.0766 0.7058 0.0092
-2.250 0.1939 0.01685 0.01136 -0.0754 0.6770 0.0101
-2.000 0.2186 0.01678 0.01111 -0.0749 0.6513 0.0115
-1.750 0.2447 0.01468 0.00854 -0.0737 0.6334 0.0133
-1.500 0.2707 0.01333 0.00685 -0.0729 0.6172 0.0153
-1.250 0.2965 0.01339 0.00682 -0.0726 0.6009 0.0168
-1.000 0.3227 0.01270 0.00590 -0.0720 0.5851 0.0188
-0.750 0.3495 0.01249 0.00542 -0.0714 0.5680 0.0215
-0.500 0.3751 0.01178 0.00454 -0.0709 0.5497 0.0231
-0.250 0.4009 0.01140 0.00408 -0.0705 0.5283 0.0242
0.000 0.4265 0.01119 0.00374 -0.0700 0.5047 0.0260
0.250 0.4522 0.01096 0.00336 -0.0695 0.4830 0.0274
0.500 0.4776 0.01081 0.00306 -0.0690 0.4622 0.0284
0.750 0.5033 0.01075 0.00288 -0.0685 0.4435 0.0293
1.000 0.5291 0.01074 0.00276 -0.0681 0.4280 0.0298
1.500 0.5801 0.01034 0.00229 -0.0672 0.4077 0.0319
1.750 0.6062 0.01032 0.00222 -0.0668 0.3978 0.0313
2.000 0.6322 0.01035 0.00219 -0.0665 0.3864 0.0309
2.250 0.6581 0.01038 0.00218 -0.0661 0.3747 0.0305
2.500 0.6844 0.01038 0.00217 -0.0658 0.3661 0.0303
2.750 0.7105 0.01041 0.00218 -0.0655 0.3579 0.0301
3.000 0.7366 0.01044 0.00218 -0.0652 0.3472 0.0300
3.250 0.7627 0.01049 0.00221 -0.0648 0.3364 0.0301
3.500 0.7887 0.01057 0.00224 -0.0645 0.3263 0.0303
3.750 0.8146 0.01067 0.00229 -0.0642 0.3162 0.0310
4.000 0.8406 0.01077 0.00237 -0.0639 0.3061 0.0326
4.250 0.8665 0.01089 0.00248 -0.0636 0.2960 0.0369
4.500 0.9084 0.00947 0.00286 -0.0675 0.2831 1.0000
4.750 0.9335 0.00968 0.00302 -0.0670 0.2720 1.0000
5.000 0.9585 0.00990 0.00323 -0.0665 0.2603 1.0000
5.250 0.9833 0.01013 0.00343 -0.0661 0.2477 1.0000
5.500 1.0069 0.01051 0.00369 -0.0655 0.2227 1.0000
5.750 1.0301 0.01094 0.00399 -0.0648 0.1957 1.0000
6.000 1.0520 0.01150 0.00437 -0.0640 0.1601 1.0000
6.250 1.0736 0.01211 0.00481 -0.0631 0.1292 1.0000
6.500 1.0961 0.01260 0.00521 -0.0624 0.1112 1.0000
6.750 1.1177 0.01320 0.00568 -0.0616 0.0873 1.0000
7.000 1.1307 0.01480 0.00686 -0.0595 0.0146 1.0000
7.250 1.1532 0.01529 0.00742 -0.0587 0.0099 1.0000
7.500 1.1755 0.01577 0.00801 -0.0578 0.0085 1.0000
7.750 1.1965 0.01637 0.00872 -0.0568 0.0072 1.0000
8.000 1.2171 0.01701 0.00947 -0.0558 0.0060 1.0000
8.250 1.2375 0.01763 0.01020 -0.0547 0.0054 1.0000
8.500 1.2568 0.01835 0.01104 -0.0535 0.0049 1.0000
8.750 1.2745 0.01920 0.01198 -0.0521 0.0045 1.0000
9.000 1.2878 0.02042 0.01334 -0.0501 0.0042 1.0000
9.250 1.3028 0.02140 0.01445 -0.0483 0.0040 1.0000
9.500 1.3156 0.02248 0.01566 -0.0463 0.0038 1.0000
9.750 1.3282 0.02349 0.01678 -0.0443 0.0035 1.0000
10.000 1.3371 0.02464 0.01805 -0.0418 0.0033 1.0000
10.250 1.3447 0.02563 0.01912 -0.0391 0.0031 1.0000
10.500 1.3507 0.02670 0.02030 -0.0363 0.0029 1.0000
10.750 1.3514 0.02818 0.02188 -0.0333 0.0027 1.0000
11.000 1.3502 0.02992 0.02374 -0.0304 0.0027 1.0000
11.250 1.3451 0.03215 0.02610 -0.0278 0.0026 1.0000
11.500 1.3413 0.03452 0.02862 -0.0258 0.0025 1.0000
11.750 1.3385 0.03704 0.03128 -0.0244 0.0025 1.0000
12.000 1.3366 0.03970 0.03409 -0.0235 0.0024 1.0000
12.250 1.3333 0.04271 0.03724 -0.0230 0.0024 1.0000
12.500 1.3282 0.04614 0.04082 -0.0228 0.0024 1.0000
12.750 1.3232 0.04982 0.04466 -0.0230 0.0023 1.0000
13.000 1.3175 0.05372 0.04871 -0.0234 0.0022 1.0000
13.250 1.3119 0.05776 0.05291 -0.0241 0.0021 1.0000
13.500 1.3045 0.06215 0.05746 -0.0249 0.0021 1.0000
13.750 1.2969 0.06672 0.06219 -0.0261 0.0021 1.0000
14.000 1.2889 0.07147 0.06709 -0.0275 0.0021 1.0000
14.250 1.2798 0.07660 0.07238 -0.0293 0.0021 1.0000
14.500 1.2700 0.08204 0.07798 -0.0314 0.0021 1.0000
14.750 1.2597 0.08779 0.08388 -0.0338 0.0021 1.0000
15.000 1.2472 0.09412 0.09037 -0.0366 0.0020 1.0000
15.250 1.2362 0.10037 0.09678 -0.0396 0.0021 1.0000
15.500 1.2245 0.10703 0.10358 -0.0430 0.0020 1.0000
15.750 1.2123 0.11395 0.11064 -0.0466 0.0021 1.0000
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