GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 495 AIRFOIL (goe495-il) Reynolds number: 1,000,000 Max Cl/Cd: 158.88 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe495-il-1000000.txt Download as CSV file: xf-goe495-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3539 0.10202 0.10039 -0.0303 1.0000 0.0109
-9.000 -0.3529 0.09983 0.09823 -0.0298 1.0000 0.0112
-8.750 -0.3537 0.09772 0.09614 -0.0290 1.0000 0.0119
-8.500 -0.3443 0.09392 0.09235 -0.0320 0.9992 0.0129
-8.250 -0.3281 0.08841 0.08684 -0.0393 0.9970 0.0136
-8.000 -0.3110 0.08393 0.08236 -0.0447 0.9948 0.0136
-7.750 -0.2975 0.01669 0.01343 -0.1306 0.9746 0.0104
-7.500 -0.2631 0.01533 0.01188 -0.1331 0.9732 0.0110
-7.250 -0.2290 0.01460 0.01104 -0.1349 0.9717 0.0115
-7.000 -0.1993 0.01375 0.01003 -0.1357 0.9676 0.0121
-6.750 -0.1695 0.01288 0.00898 -0.1365 0.9626 0.0128
-6.500 -0.1372 0.01219 0.00814 -0.1376 0.9586 0.0135
-6.250 -0.1093 0.01079 0.00650 -0.1381 0.9511 0.0146
-6.000 -0.0788 0.01071 0.00642 -0.1386 0.9445 0.0155
-5.750 -0.0505 0.01056 0.00622 -0.1386 0.9363 0.0166
-5.250 0.0066 0.01016 0.00564 -0.1387 0.9199 0.0183
-5.000 0.0338 0.00914 0.00448 -0.1388 0.9113 0.0203
-4.750 0.0616 0.00900 0.00429 -0.1387 0.9026 0.0217
-4.500 0.0892 0.00891 0.00415 -0.1386 0.8942 0.0234
-4.250 0.1171 0.00887 0.00403 -0.1384 0.8863 0.0245
-4.000 0.1440 0.00808 0.00311 -0.1383 0.8781 0.0265
-3.750 0.1715 0.00781 0.00278 -0.1382 0.8709 0.0285
-3.500 0.1990 0.00764 0.00257 -0.1381 0.8635 0.0305
-3.250 0.2266 0.00747 0.00232 -0.1379 0.8570 0.0319
-3.000 0.2543 0.00732 0.00212 -0.1378 0.8502 0.0330
-2.500 0.3097 0.00686 0.00152 -0.1375 0.8375 0.0368
-2.250 0.3374 0.00672 0.00133 -0.1374 0.8314 0.0398
-2.000 0.3651 0.00661 0.00119 -0.1372 0.8253 0.0427
-1.750 0.3928 0.00653 0.00107 -0.1371 0.8190 0.0461
-1.500 0.4204 0.00627 0.00097 -0.1370 0.8131 0.0990
-1.250 0.4480 0.00613 0.00094 -0.1369 0.8066 0.1411
-1.000 0.4754 0.00608 0.00092 -0.1368 0.8000 0.1677
-0.750 0.5027 0.00596 0.00090 -0.1366 0.7911 0.2038
0.000 0.5841 0.00573 0.00091 -0.1359 0.7613 0.3339
0.250 0.6111 0.00565 0.00094 -0.1357 0.7508 0.3908
0.500 0.6381 0.00560 0.00097 -0.1355 0.7407 0.4409
0.750 0.6650 0.00550 0.00103 -0.1352 0.7302 0.5123
1.000 0.6914 0.00532 0.00111 -0.1350 0.7188 0.6226
1.250 0.7168 0.00464 0.00117 -0.1343 0.7068 1.0000
1.500 0.7434 0.00475 0.00120 -0.1339 0.6902 1.0000
1.750 0.7697 0.00487 0.00125 -0.1335 0.6727 1.0000
2.000 0.7960 0.00501 0.00130 -0.1330 0.6534 1.0000
2.250 0.8213 0.00521 0.00138 -0.1324 0.6255 1.0000
2.500 0.8463 0.00545 0.00148 -0.1318 0.5941 1.0000
2.750 0.8716 0.00567 0.00159 -0.1312 0.5688 1.0000
3.000 0.8968 0.00591 0.00172 -0.1306 0.5405 1.0000
3.250 0.9219 0.00617 0.00185 -0.1300 0.5112 1.0000
3.500 0.9473 0.00641 0.00201 -0.1295 0.4854 1.0000
3.750 0.9716 0.00674 0.00218 -0.1288 0.4464 1.0000
4.000 0.9937 0.00728 0.00243 -0.1278 0.3833 1.0000
4.250 1.0151 0.00793 0.00276 -0.1267 0.3154 1.0000
4.500 1.0350 0.00875 0.00318 -0.1254 0.2331 1.0000
4.750 1.0549 0.00958 0.00364 -0.1242 0.1624 1.0000
5.000 1.0780 0.01007 0.00398 -0.1234 0.1302 1.0000
5.250 1.0981 0.01087 0.00445 -0.1221 0.0700 1.0000
5.500 1.1197 0.01152 0.00491 -0.1211 0.0412 1.0000
5.750 1.1440 0.01186 0.00526 -0.1204 0.0369 1.0000
6.000 1.1670 0.01233 0.00573 -0.1195 0.0311 1.0000
6.250 1.1916 0.01260 0.00603 -0.1189 0.0292 1.0000
6.500 1.2154 0.01296 0.00639 -0.1182 0.0261 1.0000
6.750 1.2371 0.01354 0.00701 -0.1171 0.0220 1.0000
7.000 1.2613 0.01381 0.00729 -0.1165 0.0202 1.0000
7.250 1.2841 0.01423 0.00769 -0.1157 0.0176 1.0000
7.500 1.3053 0.01482 0.00833 -0.1145 0.0155 1.0000
7.750 1.3280 0.01522 0.00875 -0.1137 0.0143 1.0000
8.000 1.3498 0.01569 0.00925 -0.1127 0.0132 1.0000
8.250 1.3673 0.01661 0.01023 -0.1110 0.0117 1.0000
8.500 1.3870 0.01724 0.01093 -0.1096 0.0111 1.0000
8.750 1.4078 0.01774 0.01148 -0.1085 0.0105 1.0000
9.000 1.4278 0.01828 0.01206 -0.1073 0.0099 1.0000
9.250 1.4472 0.01885 0.01267 -0.1060 0.0093 1.0000
9.500 1.4638 0.01964 0.01351 -0.1042 0.0088 1.0000
9.750 1.4689 0.02144 0.01548 -0.1006 0.0081 1.0000
10.000 1.4839 0.02210 0.01621 -0.0986 0.0079 1.0000
10.250 1.4974 0.02282 0.01701 -0.0963 0.0077 1.0000
10.500 1.5090 0.02368 0.01796 -0.0938 0.0074 1.0000
10.750 1.5195 0.02465 0.01902 -0.0912 0.0072 1.0000
11.000 1.5297 0.02565 0.02011 -0.0888 0.0069 1.0000
11.250 1.5394 0.02670 0.02127 -0.0864 0.0067 1.0000
11.500 1.5482 0.02786 0.02251 -0.0840 0.0065 1.0000
11.750 1.5565 0.02906 0.02381 -0.0817 0.0063 1.0000
12.000 1.5640 0.03035 0.02518 -0.0795 0.0062 1.0000
12.250 1.5698 0.03183 0.02675 -0.0772 0.0060 1.0000
12.500 1.5703 0.03394 0.02899 -0.0747 0.0058 1.0000
12.750 1.5553 0.03807 0.03341 -0.0712 0.0055 1.0000
13.000 1.5565 0.04030 0.03578 -0.0694 0.0054 1.0000
13.250 1.5598 0.04229 0.03791 -0.0679 0.0053 1.0000
13.500 1.5621 0.04447 0.04022 -0.0666 0.0052 1.0000
13.750 1.5604 0.04725 0.04315 -0.0654 0.0052 1.0000
14.000 1.5570 0.05035 0.04642 -0.0644 0.0051 1.0000
14.250 1.5512 0.05390 0.05014 -0.0638 0.0050 1.0000
14.500 1.5439 0.05782 0.05422 -0.0635 0.0049 1.0000
14.750 1.5346 0.06224 0.05882 -0.0638 0.0049 1.0000
15.000 1.5233 0.06722 0.06397 -0.0646 0.0048 1.0000
15.250 1.5100 0.07286 0.06979 -0.0660 0.0048 1.0000
15.500 1.4953 0.07912 0.07623 -0.0682 0.0048 1.0000
15.750 1.4783 0.08624 0.08353 -0.0711 0.0048 1.0000
16.000 1.4596 0.09414 0.09162 -0.0749 0.0048 1.0000
16.250 1.4389 0.10301 0.10067 -0.0796 0.0047 1.0000
16.500 1.4167 0.11277 0.11061 -0.0852 0.0048 1.0000
16.750 1.3914 0.12400 0.12203 -0.0921 0.0048 1.0000
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