GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 495 AIRFOIL (goe495-il) Reynolds number: 200,000 Max Cl/Cd: 93.86 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe495-il-200000-n5.txt Download as CSV file: xf-goe495-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3335 0.10101 0.09751 -0.0350 1.0000 0.0161
-8.500 -0.3343 0.09848 0.09502 -0.0338 1.0000 0.0157
-8.250 -0.3374 0.09635 0.09294 -0.0323 1.0000 0.0155
-8.000 -0.3377 0.09367 0.09031 -0.0323 0.9990 0.0153
-7.750 -0.3227 0.08932 0.08597 -0.0371 0.9946 0.0151
-7.500 -0.3082 0.08523 0.08189 -0.0417 0.9890 0.0149
-7.250 -0.2937 0.08056 0.07722 -0.0474 0.9816 0.0151
-7.000 -0.2729 0.07490 0.07156 -0.0554 0.9748 0.0156
-6.500 -0.2266 0.06258 0.05921 -0.0733 0.9601 0.0163
-6.250 -0.1934 0.05468 0.05124 -0.0860 0.9548 0.0163
-6.000 -0.1423 0.03535 0.03147 -0.1132 0.9458 0.0165
-5.750 -0.0975 0.02694 0.02232 -0.1254 0.9423 0.0178
-5.500 -0.0613 0.02500 0.02009 -0.1290 0.9398 0.0197
-5.250 -0.0297 0.02159 0.01603 -0.1317 0.9337 0.0218
-5.000 0.0045 0.01918 0.01298 -0.1338 0.9296 0.0242
-4.750 0.0390 0.01747 0.01091 -0.1359 0.9264 0.0272
-4.500 0.0689 0.01653 0.00980 -0.1365 0.9208 0.0300
-4.250 0.1003 0.01575 0.00878 -0.1373 0.9154 0.0340
-4.000 0.1342 0.01498 0.00776 -0.1385 0.9115 0.0365
-3.750 0.1625 0.01402 0.00671 -0.1388 0.9049 0.0406
-3.500 0.1936 0.01347 0.00606 -0.1395 0.8998 0.0438
-3.250 0.2256 0.01293 0.00540 -0.1403 0.8954 0.0460
-3.000 0.2537 0.01260 0.00495 -0.1402 0.8886 0.0484
-2.750 0.2851 0.01211 0.00440 -0.1409 0.8838 0.0520
-2.500 0.3139 0.01181 0.00404 -0.1410 0.8774 0.0554
-2.250 0.3436 0.01154 0.00368 -0.1413 0.8715 0.0617
-2.000 0.3732 0.01121 0.00343 -0.1416 0.8658 0.0862
-1.750 0.4014 0.01098 0.00330 -0.1417 0.8590 0.1277
-1.500 0.4311 0.01082 0.00315 -0.1419 0.8535 0.1577
-1.250 0.4583 0.01069 0.00310 -0.1418 0.8461 0.1903
-1.000 0.4877 0.01053 0.00301 -0.1420 0.8405 0.2295
-0.750 0.5143 0.01035 0.00307 -0.1418 0.8327 0.2992
-0.500 0.5428 0.01019 0.00305 -0.1419 0.8266 0.3629
-0.250 0.5693 0.01011 0.00308 -0.1416 0.8187 0.4118
0.000 0.5974 0.00999 0.00307 -0.1415 0.8122 0.4662
0.250 0.6233 0.00987 0.00314 -0.1410 0.8039 0.5327
0.750 0.6758 0.00905 0.00310 -0.1396 0.7881 1.0000
1.000 0.7034 0.00913 0.00311 -0.1394 0.7794 1.0000
1.250 0.7305 0.00921 0.00312 -0.1390 0.7690 1.0000
1.500 0.7569 0.00929 0.00315 -0.1385 0.7560 1.0000
1.750 0.7832 0.00938 0.00318 -0.1380 0.7427 1.0000
2.000 0.8095 0.00947 0.00324 -0.1375 0.7294 1.0000
2.250 0.8357 0.00957 0.00331 -0.1369 0.7151 1.0000
2.500 0.8618 0.00969 0.00339 -0.1364 0.7001 1.0000
2.750 0.8880 0.00981 0.00349 -0.1359 0.6862 1.0000
3.000 0.9139 0.00996 0.00362 -0.1353 0.6708 1.0000
3.250 0.9395 0.01012 0.00374 -0.1347 0.6531 1.0000
3.500 0.9648 0.01031 0.00390 -0.1340 0.6352 1.0000
3.750 0.9893 0.01054 0.00408 -0.1332 0.6118 1.0000
4.000 1.0127 0.01083 0.00427 -0.1321 0.5816 1.0000
4.250 1.0351 0.01118 0.00449 -0.1309 0.5468 1.0000
4.500 1.0574 0.01157 0.00476 -0.1297 0.5123 1.0000
4.750 1.0775 0.01209 0.00510 -0.1282 0.4637 1.0000
5.000 1.0958 0.01275 0.00549 -0.1264 0.4004 1.0000
5.250 1.1117 0.01365 0.00601 -0.1244 0.3281 1.0000
5.500 1.1288 0.01454 0.00662 -0.1227 0.2658 1.0000
5.750 1.1450 0.01557 0.00732 -0.1209 0.1996 1.0000
6.000 1.1627 0.01648 0.00806 -0.1194 0.1618 1.0000
6.250 1.1814 0.01729 0.00877 -0.1180 0.1264 1.0000
6.500 1.1968 0.01843 0.00959 -0.1162 0.0782 1.0000
6.750 1.2136 0.01941 0.01044 -0.1145 0.0556 1.0000
7.000 1.2314 0.02026 0.01128 -0.1130 0.0450 1.0000
7.250 1.2493 0.02109 0.01221 -0.1114 0.0380 1.0000
7.500 1.2649 0.02211 0.01325 -0.1095 0.0318 1.0000
7.750 1.2823 0.02293 0.01421 -0.1079 0.0269 1.0000
8.000 1.2954 0.02411 0.01542 -0.1057 0.0226 1.0000
8.250 1.3102 0.02503 0.01648 -0.1036 0.0200 1.0000
8.500 1.3223 0.02610 0.01767 -0.1012 0.0179 1.0000
8.750 1.3339 0.02721 0.01886 -0.0988 0.0162 1.0000
9.000 1.3390 0.02896 0.02066 -0.0957 0.0144 1.0000
9.250 1.3510 0.03013 0.02199 -0.0935 0.0135 1.0000
9.500 1.3608 0.03163 0.02369 -0.0911 0.0127 1.0000
9.750 1.3704 0.03322 0.02543 -0.0888 0.0120 1.0000
10.000 1.3800 0.03489 0.02724 -0.0867 0.0114 1.0000
10.250 1.3892 0.03658 0.02907 -0.0846 0.0109 1.0000
10.500 1.3971 0.03831 0.03092 -0.0827 0.0103 1.0000
10.750 1.4020 0.04068 0.03343 -0.0806 0.0097 1.0000
11.000 1.4085 0.04294 0.03592 -0.0786 0.0093 1.0000
11.250 1.4142 0.04524 0.03848 -0.0767 0.0089 1.0000
11.500 1.4173 0.04798 0.04148 -0.0748 0.0086 1.0000
11.750 1.4176 0.05098 0.04475 -0.0730 0.0083 1.0000
12.000 1.4152 0.05427 0.04833 -0.0713 0.0082 1.0000
12.250 1.4100 0.05788 0.05222 -0.0698 0.0080 1.0000
12.500 1.4022 0.06184 0.05646 -0.0687 0.0079 1.0000
12.750 1.3919 0.06621 0.06109 -0.0681 0.0078 1.0000
13.000 1.3794 0.07105 0.06620 -0.0680 0.0077 1.0000
13.250 1.3647 0.07643 0.07184 -0.0686 0.0077 1.0000
13.500 1.3479 0.08246 0.07813 -0.0700 0.0077 1.0000
13.750 1.3295 0.08916 0.08508 -0.0723 0.0077 1.0000
14.000 1.3095 0.09670 0.09287 -0.0757 0.0077 1.0000
14.250 1.2881 0.10525 0.10165 -0.0802 0.0077 1.0000
14.500 1.2655 0.11497 0.11160 -0.0860 0.0078 1.0000
14.750 1.2417 0.12609 0.12293 -0.0933 0.0079 1.0000
15.000 1.2157 0.13948 0.13650 -0.1022 0.0081 1.0000
15.250 1.1845 0.15705 0.15419 -0.1134 0.0085 1.0000
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Polar data table (+)
Polar graphs
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