GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 417 AIRFOIL (goe417-il) Reynolds number: 500,000 Max Cl/Cd: 102.9 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe417-il-500000-n5.txt Download as CSV file: xf-goe417-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2871 0.11995 0.11766 -0.0275 1.0000 0.0083
-10.000 -0.2851 0.11761 0.11535 -0.0270 1.0000 0.0083
-9.750 -0.2845 0.11540 0.11317 -0.0262 1.0000 0.0083
-9.500 -0.2737 0.11215 0.10993 -0.0292 0.9988 0.0084
-9.250 -0.2616 0.10858 0.10636 -0.0306 0.9973 0.0088
-9.000 -0.2470 0.10522 0.10301 -0.0337 0.9948 0.0089
-8.750 -0.2326 0.10194 0.09973 -0.0367 0.9918 0.0092
-8.500 -0.2170 0.09854 0.09633 -0.0401 0.9888 0.0094
-8.250 -0.2005 0.09505 0.09285 -0.0438 0.9862 0.0096
-8.000 -0.1862 0.09185 0.08965 -0.0468 0.9816 0.0100
-7.750 -0.1691 0.08834 0.08614 -0.0508 0.9781 0.0105
-7.250 -0.1353 0.08020 0.07799 -0.0599 0.9677 0.0079
-7.000 -0.1129 0.07637 0.07414 -0.0655 0.9629 0.0078
-6.750 -0.0914 0.07240 0.07017 -0.0711 0.9560 0.0080
-6.500 -0.0659 0.06834 0.06608 -0.0775 0.9509 0.0080
-6.250 -0.0455 0.06519 0.06291 -0.0817 0.9419 0.0088
-6.000 -0.0222 0.06288 0.06057 -0.0853 0.9342 0.0099
-5.750 0.0002 0.05927 0.05692 -0.0900 0.9241 0.0096
-5.500 0.0214 0.05580 0.05340 -0.0939 0.9126 0.0095
-5.250 0.0447 0.05245 0.04997 -0.0978 0.9015 0.0096
-5.000 0.0701 0.04902 0.04646 -0.1019 0.8916 0.0100
-4.750 0.0972 0.04538 0.04272 -0.1060 0.8806 0.0104
-4.500 0.1287 0.04072 0.03792 -0.1112 0.8695 0.0116
-4.250 0.1538 0.03897 0.03607 -0.1128 0.8569 0.0121
-4.000 0.1821 0.03635 0.03331 -0.1152 0.8443 0.0127
-3.750 0.2125 0.03323 0.03001 -0.1179 0.8321 0.0136
-3.500 0.2482 0.02851 0.02500 -0.1215 0.8225 0.0156
-3.250 0.2740 0.02737 0.02376 -0.1221 0.8123 0.0162
-3.000 0.3027 0.02525 0.02146 -0.1232 0.8014 0.0172
-2.750 0.3390 0.01954 0.01517 -0.1248 0.7918 0.0202
-2.500 0.3642 0.01867 0.01416 -0.1249 0.7782 0.0208
-2.250 0.3901 0.01786 0.01319 -0.1248 0.7641 0.0215
-2.000 0.4165 0.01691 0.01205 -0.1247 0.7485 0.0229
-1.750 0.4437 0.01533 0.01012 -0.1243 0.7302 0.0241
-1.500 0.4699 0.01414 0.00857 -0.1238 0.7072 0.0248
-1.250 0.4955 0.01342 0.00752 -0.1231 0.6808 0.0254
-1.000 0.5210 0.01368 0.00752 -0.1223 0.6557 0.0265
-0.750 0.5464 0.01261 0.00613 -0.1218 0.6351 0.0267
-0.250 0.5973 0.01124 0.00433 -0.1208 0.5994 0.0277
0.000 0.6228 0.01094 0.00390 -0.1203 0.5799 0.0281
0.250 0.6477 0.01078 0.00358 -0.1197 0.5556 0.0286
0.500 0.6726 0.01066 0.00331 -0.1191 0.5300 0.0290
0.750 0.6975 0.01061 0.00314 -0.1185 0.5041 0.0298
1.000 0.7223 0.01059 0.00300 -0.1179 0.4798 0.0306
1.250 0.7470 0.01056 0.00284 -0.1172 0.4548 0.0305
1.500 0.7714 0.01060 0.00273 -0.1165 0.4272 0.0304
1.750 0.7960 0.01065 0.00267 -0.1159 0.4036 0.0304
2.000 0.8209 0.01071 0.00263 -0.1154 0.3842 0.0305
2.250 0.8456 0.01082 0.00264 -0.1148 0.3651 0.0310
2.750 0.8958 0.01102 0.00271 -0.1138 0.3371 0.0325
3.000 0.9214 0.01112 0.00277 -0.1133 0.3289 0.0336
3.250 0.9469 0.01124 0.00285 -0.1129 0.3208 0.0346
3.500 0.9725 0.01135 0.00295 -0.1125 0.3134 0.0354
3.750 0.9978 0.01149 0.00305 -0.1120 0.3059 0.0383
4.000 1.0233 0.01162 0.00319 -0.1116 0.2992 0.0418
4.250 1.0485 0.01177 0.00334 -0.1111 0.2918 0.0451
4.500 1.0723 0.01130 0.00372 -0.1108 0.2859 0.5623
5.000 1.1267 0.01096 0.00411 -0.1108 0.2718 1.0000
5.250 1.1514 0.01119 0.00430 -0.1103 0.2618 1.0000
5.500 1.1757 0.01143 0.00453 -0.1097 0.2496 1.0000
5.750 1.1998 0.01170 0.00476 -0.1091 0.2375 1.0000
6.000 1.2233 0.01202 0.00501 -0.1084 0.2214 1.0000
6.250 1.2442 0.01257 0.00537 -0.1074 0.1887 1.0000
6.500 1.2651 0.01312 0.00579 -0.1064 0.1641 1.0000
7.000 1.3079 0.01411 0.00662 -0.1045 0.1332 1.0000
7.250 1.3291 0.01460 0.00706 -0.1035 0.1195 1.0000
7.500 1.3498 0.01512 0.00753 -0.1025 0.1051 1.0000
7.750 1.3632 0.01632 0.00840 -0.1004 0.0514 1.0000
8.000 1.3763 0.01753 0.00944 -0.0982 0.0174 1.0000
8.250 1.3951 0.01816 0.01010 -0.0968 0.0128 1.0000
8.500 1.4145 0.01869 0.01072 -0.0955 0.0113 1.0000
8.750 1.4327 0.01929 0.01141 -0.0941 0.0099 1.0000
9.000 1.4485 0.02006 0.01227 -0.0923 0.0085 1.0000
9.250 1.4628 0.02080 0.01311 -0.0902 0.0079 1.0000
9.500 1.4767 0.02149 0.01389 -0.0880 0.0074 1.0000
9.750 1.4891 0.02224 0.01473 -0.0857 0.0068 1.0000
10.000 1.5003 0.02308 0.01566 -0.0833 0.0064 1.0000
10.250 1.5104 0.02399 0.01665 -0.0809 0.0060 1.0000
10.500 1.5167 0.02517 0.01793 -0.0781 0.0056 1.0000
10.750 1.5227 0.02639 0.01926 -0.0753 0.0053 1.0000
11.000 1.5310 0.02747 0.02045 -0.0731 0.0050 1.0000
11.250 1.5355 0.02887 0.02197 -0.0705 0.0048 1.0000
11.500 1.5395 0.03036 0.02358 -0.0681 0.0046 1.0000
11.750 1.5424 0.03200 0.02533 -0.0659 0.0044 1.0000
12.000 1.5431 0.03391 0.02737 -0.0637 0.0043 1.0000
12.250 1.5434 0.03597 0.02954 -0.0618 0.0042 1.0000
12.500 1.5422 0.03831 0.03200 -0.0601 0.0041 1.0000
12.750 1.5406 0.04082 0.03463 -0.0588 0.0040 1.0000
13.000 1.5369 0.04373 0.03768 -0.0578 0.0039 1.0000
13.250 1.5314 0.04704 0.04111 -0.0571 0.0038 1.0000
13.500 1.5231 0.05094 0.04514 -0.0568 0.0037 1.0000
13.750 1.5127 0.05541 0.04976 -0.0571 0.0036 1.0000
14.000 1.5014 0.06026 0.05476 -0.0578 0.0036 1.0000
14.250 1.4919 0.06515 0.05979 -0.0589 0.0035 1.0000
14.500 1.4832 0.07009 0.06488 -0.0601 0.0035 1.0000
14.750 1.4757 0.07504 0.06997 -0.0616 0.0035 1.0000
15.000 1.4669 0.08032 0.07539 -0.0632 0.0034 1.0000
15.250 1.4582 0.08575 0.08096 -0.0651 0.0034 1.0000
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Polar data table (+)
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