GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 477 AIRFOIL (goe477-il) Reynolds number: 500,000 Max Cl/Cd: 111.26 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe477-il-500000.txt Download as CSV file: xf-goe477-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 477 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1874 0.08293 0.08045 -0.0860 0.9197 0.0293
-9.250 -0.1783 0.07886 0.07633 -0.0878 0.9115 0.0299
-9.000 -0.4180 0.02625 0.02247 -0.1119 0.8762 0.0200
-8.750 -0.3985 0.02516 0.02129 -0.1115 0.8731 0.0206
-8.500 -0.3722 0.02536 0.02151 -0.1113 0.8704 0.0214
-8.250 -0.3553 0.02343 0.01927 -0.1107 0.8674 0.0222
-8.000 -0.3395 0.02098 0.01636 -0.1099 0.8645 0.0232
-7.750 -0.3193 0.01943 0.01446 -0.1092 0.8618 0.0239
-7.500 -0.3004 0.01754 0.01231 -0.1083 0.8590 0.0251
-7.250 -0.2750 0.01719 0.01192 -0.1080 0.8564 0.0261
-7.000 -0.2499 0.01666 0.01124 -0.1076 0.8540 0.0274
-6.750 -0.2241 0.01620 0.01060 -0.1073 0.8518 0.0290
-6.500 -0.1999 0.01535 0.00961 -0.1068 0.8496 0.0307
-6.250 -0.1732 0.01528 0.00955 -0.1066 0.8475 0.0323
-6.000 -0.1470 0.01493 0.00909 -0.1063 0.8453 0.0343
-5.750 -0.1213 0.01432 0.00833 -0.1059 0.8430 0.0363
-5.500 -0.0944 0.01426 0.00831 -0.1058 0.8407 0.0385
-5.250 -0.0672 0.01420 0.00819 -0.1056 0.8384 0.0410
-5.000 -0.0396 0.01414 0.00801 -0.1054 0.8364 0.0432
-4.750 -0.0142 0.01347 0.00729 -0.1051 0.8340 0.0463
-4.500 0.0124 0.01340 0.00723 -0.1048 0.8306 0.0492
-4.250 0.0392 0.01324 0.00699 -0.1044 0.8267 0.0518
-4.000 0.0652 0.01263 0.00629 -0.1040 0.8233 0.0549
-3.750 0.0921 0.01236 0.00600 -0.1038 0.8204 0.0580
-3.500 0.1189 0.01218 0.00578 -0.1035 0.8176 0.0608
-3.250 0.1457 0.01201 0.00559 -0.1032 0.8139 0.0635
-3.000 0.1727 0.01183 0.00535 -0.1029 0.8098 0.0651
-2.750 0.1983 0.01116 0.00464 -0.1024 0.8058 0.0689
-2.500 0.2244 0.01091 0.00438 -0.1019 0.8007 0.0714
-2.250 0.2507 0.01065 0.00410 -0.1013 0.7944 0.0741
-2.000 0.2781 0.01046 0.00384 -0.1010 0.7898 0.0766
-1.750 0.3044 0.01028 0.00365 -0.1005 0.7850 0.0781
-1.500 0.3304 0.00993 0.00331 -0.1000 0.7803 0.0824
-1.250 0.3576 0.00973 0.00310 -0.0998 0.7761 0.0867
-1.000 0.3845 0.00958 0.00294 -0.0994 0.7717 0.0910
-0.750 0.4109 0.00936 0.00277 -0.0990 0.7662 0.0999
-0.500 0.4377 0.00910 0.00261 -0.0986 0.7615 0.1310
-0.250 0.4633 0.00873 0.00255 -0.0982 0.7568 0.2290
0.000 0.4877 0.00830 0.00251 -0.0976 0.7504 0.3502
0.250 0.5069 0.00742 0.00246 -0.0960 0.7449 0.6408
0.500 0.5825 0.00663 0.00247 -0.1058 0.7376 0.9904
0.750 0.6239 0.00658 0.00235 -0.1086 0.7300 1.0000
1.000 0.6482 0.00656 0.00231 -0.1078 0.7205 1.0000
1.250 0.6725 0.00655 0.00225 -0.1069 0.7095 1.0000
1.500 0.6965 0.00654 0.00219 -0.1059 0.6949 1.0000
1.750 0.7199 0.00657 0.00213 -0.1048 0.6745 1.0000
2.000 0.7421 0.00667 0.00209 -0.1035 0.6474 1.0000
2.250 0.7624 0.00689 0.00211 -0.1018 0.6130 1.0000
2.500 0.7810 0.00722 0.00222 -0.0999 0.5682 1.0000
2.750 0.7961 0.00774 0.00242 -0.0973 0.5042 1.0000
3.000 0.8112 0.00830 0.00268 -0.0948 0.4514 1.0000
3.250 0.8296 0.00873 0.00292 -0.0930 0.4209 1.0000
3.500 0.8495 0.00909 0.00315 -0.0915 0.3982 1.0000
3.750 0.8704 0.00940 0.00336 -0.0902 0.3775 1.0000
4.000 0.8915 0.00970 0.00357 -0.0890 0.3584 1.0000
4.250 0.9125 0.01001 0.00379 -0.0877 0.3402 1.0000
4.500 0.9335 0.01032 0.00402 -0.0864 0.3236 1.0000
4.750 0.9547 0.01063 0.00425 -0.0852 0.3088 1.0000
5.000 0.9762 0.01092 0.00448 -0.0841 0.2961 1.0000
5.250 0.9975 0.01121 0.00472 -0.0829 0.2842 1.0000
5.500 1.0184 0.01152 0.00499 -0.0817 0.2735 1.0000
5.750 1.0388 0.01185 0.00526 -0.0804 0.2641 1.0000
6.000 1.0608 0.01210 0.00550 -0.0794 0.2561 1.0000
6.250 1.0807 0.01245 0.00581 -0.0781 0.2490 1.0000
6.500 1.1028 0.01267 0.00606 -0.0771 0.2422 1.0000
6.750 1.1224 0.01301 0.00636 -0.0757 0.2349 1.0000
7.000 1.1439 0.01325 0.00663 -0.0747 0.2278 1.0000
7.500 1.1826 0.01382 0.00721 -0.0718 0.2116 1.0000
7.750 1.2000 0.01416 0.00752 -0.0700 0.2018 1.0000
8.000 1.2176 0.01451 0.00783 -0.0684 0.1857 1.0000
8.250 1.2254 0.01543 0.00839 -0.0653 0.1286 1.0000
8.500 1.2155 0.01759 0.01001 -0.0598 0.0440 1.0000
8.750 1.2271 0.01847 0.01089 -0.0575 0.0357 1.0000
9.000 1.2418 0.01914 0.01163 -0.0557 0.0327 1.0000
9.250 1.2532 0.02005 0.01257 -0.0535 0.0297 1.0000
9.500 1.2647 0.02095 0.01355 -0.0515 0.0276 1.0000
9.750 1.2777 0.02176 0.01443 -0.0497 0.0262 1.0000
10.000 1.2887 0.02271 0.01544 -0.0478 0.0249 1.0000
10.250 1.2967 0.02389 0.01669 -0.0456 0.0236 1.0000
10.500 1.2960 0.02570 0.01861 -0.0427 0.0225 1.0000
10.750 1.3071 0.02671 0.01969 -0.0411 0.0217 1.0000
11.000 1.3164 0.02788 0.02094 -0.0395 0.0208 1.0000
11.250 1.3234 0.02925 0.02240 -0.0377 0.0201 1.0000
11.500 1.3286 0.03079 0.02401 -0.0359 0.0195 1.0000
11.750 1.3334 0.03239 0.02567 -0.0343 0.0188 1.0000
12.000 1.3346 0.03434 0.02769 -0.0325 0.0184 1.0000
12.250 1.3318 0.03669 0.03013 -0.0306 0.0180 1.0000
12.500 1.3204 0.03995 0.03348 -0.0284 0.0174 1.0000
12.750 1.3246 0.04187 0.03550 -0.0273 0.0172 1.0000
13.000 1.3305 0.04371 0.03745 -0.0264 0.0167 1.0000
13.250 1.3345 0.04579 0.03962 -0.0256 0.0162 1.0000
13.500 1.3363 0.04816 0.04209 -0.0249 0.0158 1.0000
13.750 1.3373 0.05073 0.04474 -0.0242 0.0154 1.0000
14.000 1.3392 0.05329 0.04738 -0.0239 0.0150 1.0000
14.250 1.3399 0.05606 0.05023 -0.0236 0.0147 1.0000
14.500 1.3398 0.05900 0.05323 -0.0234 0.0144 1.0000
14.750 1.3400 0.06196 0.05626 -0.0233 0.0142 1.0000
15.000 1.3407 0.06488 0.05925 -0.0232 0.0140 1.0000
15.250 1.3432 0.06735 0.06175 -0.0215 0.0135 1.0000
15.500 1.3420 0.07081 0.06537 -0.0223 0.0133 1.0000
15.750 1.3438 0.07384 0.06852 -0.0224 0.0132 1.0000
16.000 1.3433 0.07731 0.07213 -0.0230 0.0130 1.0000
16.250 1.3423 0.08091 0.07587 -0.0236 0.0128 1.0000
16.500 1.3403 0.08474 0.07985 -0.0245 0.0125 1.0000
16.750 1.3381 0.08868 0.08392 -0.0256 0.0123 1.0000
17.000 1.3351 0.09283 0.08820 -0.0270 0.0121 1.0000
17.250 1.3316 0.09715 0.09263 -0.0287 0.0118 1.0000
17.500 1.3269 0.10168 0.09731 -0.0302 0.0117 1.0000
17.750 1.3229 0.10620 0.10194 -0.0322 0.0115 1.0000
18.000 1.3172 0.11110 0.10699 -0.0342 0.0114 1.0000
18.250 1.3134 0.11571 0.11169 -0.0365 0.0113 1.0000
18.500 1.3071 0.12084 0.11694 -0.0391 0.0111 1.0000
18.750 1.2998 0.12624 0.12247 -0.0419 0.0111 1.0000
19.000 1.2916 0.13192 0.12829 -0.0450 0.0110 1.0000
19.250 1.2793 0.13863 0.13518 -0.0488 0.0110 1.0000
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