GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 403 AIRFOIL (goe403-il) Reynolds number: 200,000 Max Cl/Cd: 75.81 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe403-il-200000.txt Download as CSV file: xf-goe403-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 403 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3332 0.08938 0.08607 -0.0259 1.0000 0.0352
-7.250 -0.3357 0.08716 0.08393 -0.0257 1.0000 0.0361
-7.000 -0.3394 0.08506 0.08190 -0.0259 1.0000 0.0372
-6.750 -0.3392 0.08292 0.07983 -0.0286 1.0000 0.0381
-6.500 -0.3371 0.08074 0.07771 -0.0320 1.0000 0.0386
-6.250 -0.3362 0.07855 0.07555 -0.0336 1.0000 0.0389
-6.000 -0.3380 0.07647 0.07351 -0.0337 1.0000 0.0390
-5.750 -0.3331 0.07372 0.07074 -0.0350 0.9996 0.0391
-5.500 -0.3099 0.06569 0.06269 -0.0415 0.9951 0.0402
-5.250 -0.2880 0.06212 0.05911 -0.0428 0.9905 0.0420
-5.000 -0.2525 0.05819 0.05507 -0.0490 0.9854 0.0478
-4.750 -0.1955 0.05015 0.04670 -0.0643 0.9793 0.0531
-4.500 -0.1697 0.04721 0.04377 -0.0660 0.9737 0.0558
-4.250 -0.1104 0.04096 0.03690 -0.0773 0.9696 0.0656
-4.000 -0.0877 0.03791 0.03398 -0.0782 0.9627 0.0684
-3.750 -0.0460 0.03421 0.02997 -0.0832 0.9581 0.0808
-3.500 0.0036 0.02310 0.01740 -0.0882 0.9551 0.0527
-3.250 0.0350 0.02088 0.01501 -0.0896 0.9476 0.0565
-3.000 0.0761 0.01889 0.01250 -0.0921 0.9439 0.0623
-2.750 0.1123 0.01749 0.01060 -0.0933 0.9374 0.0649
-2.500 0.1478 0.01566 0.00861 -0.0949 0.9314 0.0694
-2.250 0.1824 0.01462 0.00738 -0.0959 0.9240 0.0727
-2.000 0.2174 0.01377 0.00635 -0.0969 0.9164 0.0766
-1.750 0.2480 0.01297 0.00549 -0.0971 0.9064 0.0815
-1.500 0.2794 0.01252 0.00500 -0.0975 0.8964 0.0901
-1.250 0.3097 0.01187 0.00438 -0.0976 0.8860 0.1021
-1.000 0.3380 0.01131 0.00387 -0.0973 0.8739 0.1337
-0.750 0.3648 0.01092 0.00357 -0.0968 0.8606 0.1709
-0.500 0.3912 0.01064 0.00339 -0.0962 0.8467 0.2100
-0.250 0.4161 0.01016 0.00330 -0.0956 0.8324 0.3224
0.000 0.4562 0.00854 0.00312 -0.0977 0.8184 1.0000
0.250 0.4812 0.00864 0.00304 -0.0967 0.8012 1.0000
0.500 0.5063 0.00873 0.00298 -0.0958 0.7834 1.0000
0.750 0.5316 0.00882 0.00292 -0.0950 0.7653 1.0000
1.000 0.5566 0.00891 0.00288 -0.0941 0.7456 1.0000
1.250 0.5817 0.00901 0.00285 -0.0933 0.7251 1.0000
1.500 0.6069 0.00911 0.00285 -0.0925 0.7044 1.0000
1.750 0.6321 0.00924 0.00286 -0.0917 0.6838 1.0000
2.000 0.6575 0.00941 0.00290 -0.0910 0.6644 1.0000
2.250 0.6828 0.00959 0.00298 -0.0904 0.6456 1.0000
2.500 0.7083 0.00980 0.00312 -0.0898 0.6288 1.0000
2.750 0.7338 0.01004 0.00327 -0.0892 0.6135 1.0000
3.000 0.7587 0.01026 0.00341 -0.0885 0.5946 1.0000
3.250 0.7820 0.01049 0.00350 -0.0874 0.5668 1.0000
3.500 0.8065 0.01073 0.00369 -0.0867 0.5476 1.0000
3.750 0.8293 0.01098 0.00385 -0.0856 0.5182 1.0000
4.000 0.8514 0.01123 0.00397 -0.0843 0.4806 1.0000
4.500 0.8956 0.01190 0.00438 -0.0819 0.3916 1.0000
4.750 0.9119 0.01290 0.00476 -0.0800 0.2695 1.0000
5.000 0.9159 0.01579 0.00628 -0.0769 0.0368 1.0000
5.250 0.9387 0.01641 0.00705 -0.0758 0.0314 1.0000
5.500 0.9605 0.01714 0.00793 -0.0746 0.0288 1.0000
5.750 0.9807 0.01804 0.00902 -0.0732 0.0275 1.0000
6.000 0.9984 0.01916 0.01031 -0.0714 0.0270 1.0000
6.250 1.0143 0.02042 0.01166 -0.0694 0.0269 1.0000
6.500 1.0256 0.02233 0.01362 -0.0668 0.0260 1.0000
6.750 1.0444 0.02349 0.01488 -0.0652 0.0249 1.0000
7.000 1.0633 0.02540 0.01679 -0.0636 0.0252 1.0000
7.250 1.0895 0.02819 0.01955 -0.0630 0.0261 1.0000
7.500 1.1140 0.02861 0.02013 -0.0617 0.0278 1.0000
7.750 1.1506 0.03252 0.02428 -0.0616 0.0349 1.0000
14.500 0.8208 0.16851 0.16563 -0.0791 0.0575 1.0000
14.750 0.8164 0.17321 0.17032 -0.0823 0.0543 1.0000
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Polar data table (+)
Polar graphs
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