GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 374 AIRFOIL (goe374-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.64 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe374-il-1000000.txt Download as CSV file: xf-goe374-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2788 0.08728 0.08580 -0.0183 1.0000 0.0067
-8.500 -0.2752 0.08416 0.08269 -0.0186 1.0000 0.0069
-8.250 -0.2723 0.08102 0.07957 -0.0190 1.0000 0.0069
-8.000 -0.2695 0.07810 0.07666 -0.0193 1.0000 0.0072
-7.750 -0.2678 0.07508 0.07366 -0.0197 1.0000 0.0074
-7.500 -0.2670 0.07216 0.07076 -0.0198 1.0000 0.0076
-7.250 -0.2678 0.06934 0.06796 -0.0197 1.0000 0.0078
-7.000 -0.2719 0.06682 0.06548 -0.0190 1.0000 0.0086
-6.750 -0.2704 0.06361 0.06229 -0.0206 0.9976 0.0088
-6.500 -0.2503 0.05867 0.05733 -0.0287 0.9900 0.0093
-6.250 -0.3046 0.07073 0.06930 -0.0274 0.9960 0.0090
-6.000 -0.2677 0.06587 0.06438 -0.0369 0.9901 0.0093
-5.750 -0.2329 0.06106 0.05950 -0.0447 0.9848 0.0094
-5.500 -0.2002 0.05664 0.05501 -0.0508 0.9783 0.0094
-5.250 -0.1653 0.05216 0.05044 -0.0566 0.9726 0.0094
-5.000 -0.1391 0.04693 0.04515 -0.0612 0.9644 0.0098
-4.750 -0.1064 0.04355 0.04168 -0.0655 0.9541 0.0100
-4.500 -0.0762 0.04048 0.03849 -0.0685 0.9379 0.0104
-4.250 -0.0496 0.03764 0.03550 -0.0701 0.9192 0.0109
-4.000 -0.0245 0.03494 0.03262 -0.0707 0.9003 0.0118
-3.750 0.0076 0.03215 0.02954 -0.0705 0.8822 0.0129
-3.500 0.0323 0.02929 0.02645 -0.0700 0.8643 0.0129
-3.250 0.0512 0.02545 0.02237 -0.0697 0.8461 0.0135
-2.750 0.0976 0.02277 0.01935 -0.0688 0.8058 0.0151
-2.500 0.1276 0.02197 0.01823 -0.0672 0.7826 0.0172
-2.250 0.1519 0.02010 0.01606 -0.0661 0.7531 0.0173
-0.750 0.3007 0.01346 0.00773 -0.0609 0.5932 0.0233
-0.500 0.3250 0.01116 0.00524 -0.0603 0.5775 0.0250
-0.250 0.3509 0.01087 0.00487 -0.0600 0.5568 0.0274
0.000 0.3781 0.01153 0.00537 -0.0595 0.5297 0.0311
1.250 0.5057 0.00904 0.00238 -0.0571 0.4255 0.0492
1.500 0.5319 0.00884 0.00210 -0.0564 0.4150 0.0390
1.750 0.5579 0.00867 0.00188 -0.0559 0.4045 0.0370
2.000 0.5841 0.00860 0.00175 -0.0555 0.3939 0.0363
2.250 0.6103 0.00857 0.00166 -0.0551 0.3842 0.0351
2.500 0.6370 0.00856 0.00160 -0.0548 0.3738 0.0339
2.750 0.6635 0.00856 0.00158 -0.0545 0.3643 0.0335
3.000 0.6899 0.00858 0.00155 -0.0542 0.3554 0.0346
3.250 0.7166 0.00859 0.00154 -0.0539 0.3465 0.0367
3.500 0.7432 0.00865 0.00157 -0.0537 0.3376 0.0384
3.750 0.7696 0.00874 0.00164 -0.0534 0.3275 0.0395
4.000 0.7962 0.00882 0.00170 -0.0532 0.3174 0.0411
4.250 0.8226 0.00892 0.00180 -0.0529 0.3069 0.0486
4.500 0.8729 0.00742 0.00215 -0.0588 0.2908 1.0000
4.750 0.8975 0.00766 0.00230 -0.0583 0.2711 1.0000
5.000 0.9225 0.00787 0.00245 -0.0577 0.2563 1.0000
5.250 0.9469 0.00814 0.00263 -0.0572 0.2345 1.0000
5.500 0.9710 0.00844 0.00283 -0.0566 0.2141 1.0000
5.750 0.9947 0.00880 0.00306 -0.0559 0.1893 1.0000
6.000 1.0170 0.00931 0.00339 -0.0551 0.1523 1.0000
6.250 1.0394 0.00982 0.00373 -0.0542 0.1256 1.0000
6.500 1.0626 0.01023 0.00405 -0.0535 0.1089 1.0000
6.750 1.0847 0.01076 0.00441 -0.0527 0.0815 1.0000
7.000 1.0998 0.01217 0.00542 -0.0508 0.0147 1.0000
7.250 1.1233 0.01254 0.00587 -0.0501 0.0130 1.0000
7.500 1.1461 0.01300 0.00640 -0.0493 0.0116 1.0000
7.750 1.1678 0.01360 0.00709 -0.0482 0.0102 1.0000
8.000 1.1875 0.01443 0.00807 -0.0469 0.0092 1.0000
8.250 1.2105 0.01480 0.00848 -0.0462 0.0086 1.0000
8.500 1.2319 0.01535 0.00910 -0.0452 0.0079 1.0000
8.750 1.2523 0.01601 0.00983 -0.0441 0.0074 1.0000
9.000 1.2716 0.01673 0.01063 -0.0429 0.0070 1.0000
9.250 1.2893 0.01760 0.01159 -0.0414 0.0067 1.0000
9.500 1.3037 0.01871 0.01281 -0.0396 0.0062 1.0000
9.750 1.3036 0.02103 0.01531 -0.0357 0.0058 1.0000
10.000 1.3192 0.02184 0.01621 -0.0341 0.0057 1.0000
10.250 1.3337 0.02270 0.01714 -0.0323 0.0055 1.0000
10.500 1.3457 0.02367 0.01821 -0.0302 0.0052 1.0000
10.750 1.3529 0.02474 0.01937 -0.0273 0.0050 1.0000
11.000 1.3583 0.02577 0.02048 -0.0243 0.0048 1.0000
11.250 1.3589 0.02725 0.02205 -0.0210 0.0047 1.0000
11.500 1.3644 0.02843 0.02333 -0.0187 0.0045 1.0000
11.750 1.3659 0.03005 0.02504 -0.0165 0.0044 1.0000
12.000 1.3654 0.03202 0.02713 -0.0144 0.0043 1.0000
12.250 1.3663 0.03402 0.02923 -0.0130 0.0043 1.0000
12.500 1.3631 0.03667 0.03199 -0.0117 0.0042 1.0000
12.750 1.3615 0.03931 0.03474 -0.0110 0.0041 1.0000
13.000 1.3617 0.04188 0.03742 -0.0109 0.0041 1.0000
13.250 1.3574 0.04522 0.04089 -0.0109 0.0040 1.0000
13.500 1.3532 0.04875 0.04454 -0.0113 0.0040 1.0000
13.750 1.3488 0.05245 0.04834 -0.0123 0.0039 1.0000
14.000 1.3426 0.05649 0.05251 -0.0133 0.0039 1.0000
14.250 1.3386 0.06038 0.05648 -0.0150 0.0038 1.0000
14.500 1.3277 0.06529 0.06156 -0.0160 0.0039 1.0000
14.750 1.3200 0.06991 0.06626 -0.0181 0.0038 1.0000
15.000 1.3080 0.07522 0.07169 -0.0200 0.0037 1.0000
15.250 1.2986 0.08056 0.07718 -0.0223 0.0037 1.0000
15.500 1.2821 0.08688 0.08362 -0.0247 0.0036 1.0000
15.750 1.2704 0.09291 0.08977 -0.0276 0.0036 1.0000
16.000 1.2586 0.09917 0.09615 -0.0307 0.0036 1.0000
16.250 1.2505 0.10509 0.10220 -0.0341 0.0037 1.0000
16.500 1.2380 0.11198 0.10922 -0.0377 0.0037 1.0000
16.750 1.2210 0.11965 0.11700 -0.0417 0.0036 1.0000
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Polar data table (+)
Polar graphs
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