GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 495 AIRFOIL (goe495-il) Reynolds number: 500,000 Max Cl/Cd: 122.74 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe495-il-500000-n5.txt Download as CSV file: xf-goe495-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 495 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3413 0.10838 0.10606 -0.0328 1.0000 0.0066
-9.500 -0.3404 0.10557 0.10327 -0.0328 1.0000 0.0064
-9.250 -0.3415 0.10256 0.10029 -0.0326 1.0000 0.0067
-9.000 -0.3305 0.09843 0.09617 -0.0359 0.9986 0.0066
-8.750 -0.3181 0.09405 0.09179 -0.0400 0.9962 0.0065
-8.500 -0.3081 0.08870 0.08644 -0.0447 0.9926 0.0073
-7.500 -0.2390 0.01909 0.01530 -0.1356 0.9515 0.0076
-7.250 -0.2100 0.01640 0.01216 -0.1379 0.9452 0.0081
-7.000 -0.1782 0.01522 0.01076 -0.1395 0.9411 0.0087
-6.750 -0.1485 0.01447 0.00984 -0.1404 0.9356 0.0094
-6.500 -0.1186 0.01367 0.00885 -0.1412 0.9294 0.0103
-6.250 -0.0878 0.01283 0.00775 -0.1421 0.9239 0.0111
-6.000 -0.0592 0.01188 0.00664 -0.1425 0.9161 0.0124
-5.750 -0.0294 0.01153 0.00620 -0.1430 0.9091 0.0137
-5.500 -0.0007 0.01117 0.00573 -0.1432 0.9000 0.0153
-5.250 0.0277 0.01080 0.00524 -0.1433 0.8910 0.0171
-5.000 0.0563 0.01061 0.00498 -0.1434 0.8827 0.0193
-4.750 0.0841 0.01038 0.00466 -0.1434 0.8747 0.0218
-4.500 0.1123 0.01026 0.00444 -0.1434 0.8678 0.0242
-4.250 0.1400 0.01022 0.00432 -0.1432 0.8605 0.0252
-4.000 0.1677 0.00957 0.00354 -0.1433 0.8541 0.0283
-3.750 0.1953 0.00936 0.00328 -0.1433 0.8473 0.0307
-3.500 0.2231 0.00916 0.00299 -0.1432 0.8411 0.0325
-3.250 0.2508 0.00898 0.00273 -0.1431 0.8349 0.0341
-3.000 0.2785 0.00879 0.00245 -0.1430 0.8287 0.0349
-2.750 0.3063 0.00862 0.00221 -0.1429 0.8228 0.0355
-2.500 0.3340 0.00850 0.00202 -0.1428 0.8167 0.0361
-2.250 0.3618 0.00835 0.00179 -0.1427 0.8110 0.0376
-2.000 0.3895 0.00821 0.00161 -0.1426 0.8047 0.0402
-1.750 0.4172 0.00810 0.00147 -0.1424 0.7989 0.0452
-1.500 0.4448 0.00793 0.00137 -0.1424 0.7927 0.0688
-1.250 0.4723 0.00778 0.00132 -0.1423 0.7862 0.1094
-1.000 0.4998 0.00770 0.00129 -0.1422 0.7801 0.1371
-0.750 0.5273 0.00763 0.00127 -0.1421 0.7731 0.1599
-0.500 0.5547 0.00759 0.00126 -0.1419 0.7663 0.1802
-0.250 0.5820 0.00751 0.00126 -0.1418 0.7585 0.2145
0.000 0.6091 0.00745 0.00128 -0.1416 0.7495 0.2518
0.250 0.6356 0.00737 0.00130 -0.1413 0.7360 0.3066
0.500 0.6619 0.00730 0.00135 -0.1409 0.7194 0.3725
0.750 0.6881 0.00725 0.00140 -0.1405 0.7036 0.4300
1.000 0.7145 0.00724 0.00146 -0.1402 0.6890 0.4766
1.250 0.7405 0.00721 0.00154 -0.1398 0.6735 0.5379
1.500 0.7661 0.00715 0.00163 -0.1393 0.6574 0.6187
1.750 0.7903 0.00655 0.00169 -0.1383 0.6423 1.0000
2.000 0.8162 0.00671 0.00177 -0.1378 0.6256 1.0000
2.250 0.8420 0.00689 0.00186 -0.1373 0.6084 1.0000
2.500 0.8678 0.00707 0.00197 -0.1368 0.5896 1.0000
2.750 0.8925 0.00732 0.00210 -0.1361 0.5645 1.0000
3.000 0.9172 0.00758 0.00226 -0.1355 0.5386 1.0000
3.250 0.9418 0.00784 0.00242 -0.1348 0.5128 1.0000
3.500 0.9649 0.00823 0.00263 -0.1339 0.4723 1.0000
3.750 0.9868 0.00872 0.00289 -0.1328 0.4191 1.0000
4.000 1.0078 0.00934 0.00320 -0.1316 0.3574 1.0000
4.250 1.0290 0.00997 0.00357 -0.1306 0.3034 1.0000
4.500 1.0504 0.01060 0.00395 -0.1295 0.2486 1.0000
4.750 1.0705 0.01138 0.00443 -0.1283 0.1865 1.0000
5.000 1.0929 0.01190 0.00482 -0.1274 0.1595 1.0000
5.250 1.1163 0.01232 0.00519 -0.1267 0.1400 1.0000
5.500 1.1376 0.01293 0.00562 -0.1257 0.1030 1.0000
5.750 1.1573 0.01370 0.00618 -0.1244 0.0631 1.0000
6.000 1.1785 0.01432 0.00668 -0.1233 0.0444 1.0000
6.250 1.2010 0.01477 0.00713 -0.1225 0.0377 1.0000
6.500 1.2230 0.01526 0.00762 -0.1215 0.0322 1.0000
6.750 1.2458 0.01565 0.00806 -0.1207 0.0285 1.0000
7.000 1.2670 0.01619 0.00862 -0.1196 0.0231 1.0000
7.250 1.2889 0.01663 0.00911 -0.1186 0.0192 1.0000
7.500 1.3090 0.01725 0.00970 -0.1174 0.0140 1.0000
7.750 1.3291 0.01783 0.01031 -0.1161 0.0119 1.0000
8.000 1.3477 0.01854 0.01105 -0.1147 0.0101 1.0000
8.250 1.3659 0.01926 0.01185 -0.1131 0.0091 1.0000
8.500 1.3840 0.01994 0.01262 -0.1116 0.0084 1.0000
8.750 1.4014 0.02065 0.01339 -0.1100 0.0076 1.0000
9.000 1.4162 0.02150 0.01433 -0.1079 0.0069 1.0000
9.250 1.4281 0.02246 0.01537 -0.1054 0.0064 1.0000
9.500 1.4409 0.02330 0.01631 -0.1031 0.0061 1.0000
9.750 1.4526 0.02422 0.01734 -0.1006 0.0058 1.0000
10.000 1.4634 0.02522 0.01844 -0.0982 0.0055 1.0000
10.250 1.4736 0.02628 0.01960 -0.0958 0.0053 1.0000
10.500 1.4831 0.02742 0.02084 -0.0934 0.0051 1.0000
10.750 1.4919 0.02864 0.02217 -0.0910 0.0048 1.0000
11.000 1.4989 0.03005 0.02368 -0.0886 0.0047 1.0000
11.250 1.5020 0.03187 0.02561 -0.0860 0.0045 1.0000
11.500 1.5065 0.03364 0.02752 -0.0837 0.0043 1.0000
11.750 1.5127 0.03528 0.02934 -0.0817 0.0042 1.0000
12.000 1.5182 0.03705 0.03127 -0.0798 0.0040 1.0000
12.250 1.5227 0.03896 0.03333 -0.0780 0.0039 1.0000
12.500 1.5258 0.04109 0.03562 -0.0763 0.0037 1.0000
12.750 1.5278 0.04339 0.03808 -0.0748 0.0036 1.0000
13.000 1.5278 0.04599 0.04083 -0.0734 0.0035 1.0000
13.250 1.5269 0.04879 0.04380 -0.0722 0.0034 1.0000
13.500 1.5252 0.05176 0.04693 -0.0713 0.0034 1.0000
13.750 1.5220 0.05505 0.05038 -0.0706 0.0033 1.0000
14.000 1.5174 0.05865 0.05415 -0.0703 0.0032 1.0000
14.250 1.5115 0.06259 0.05825 -0.0703 0.0032 1.0000
14.500 1.5041 0.06696 0.06279 -0.0708 0.0032 1.0000
14.750 1.4954 0.07176 0.06777 -0.0717 0.0031 1.0000
15.000 1.4854 0.07706 0.07324 -0.0732 0.0031 1.0000
15.250 1.4738 0.08294 0.07929 -0.0752 0.0031 1.0000
15.500 1.4605 0.08945 0.08599 -0.0778 0.0030 1.0000
15.750 1.4460 0.09656 0.09328 -0.0810 0.0030 1.0000
16.000 1.4302 0.10430 0.10120 -0.0849 0.0030 1.0000
16.250 1.4122 0.11299 0.11008 -0.0895 0.0030 1.0000
16.500 1.3940 0.12222 0.11949 -0.0948 0.0030 1.0000
16.750 1.3737 0.13245 0.12991 -0.1010 0.0030 1.0000
17.000 1.3495 0.14441 0.14209 -0.1083 0.0031 1.0000
17.250 1.3277 0.15639 0.15424 -0.1158 0.0031 1.0000
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