GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 495 AIRFOIL (goe495-il) Reynolds number: 500,000 Max Cl/Cd: 132.84 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe495-il-500000.txt Download as CSV file: xf-goe495-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3507 0.09921 0.09698 -0.0338 1.0000 0.0183
-8.500 -0.3542 0.09695 0.09476 -0.0327 1.0000 0.0184
-8.250 -0.3627 0.09338 0.09124 -0.0303 1.0000 0.0190
-8.000 -0.3639 0.09232 0.09021 -0.0273 1.0000 0.0194
-7.750 -0.3472 0.08906 0.08695 -0.0308 0.9980 0.0200
-7.500 -0.3279 0.08519 0.08307 -0.0360 0.9950 0.0207
-7.250 -0.3101 0.08121 0.07910 -0.0414 0.9901 0.0214
-7.000 -0.2837 0.07601 0.07389 -0.0500 0.9856 0.0228
-6.750 -0.2473 0.06944 0.06729 -0.0645 0.9793 0.0245
-6.500 -0.2148 0.06320 0.06102 -0.0752 0.9746 0.0247
-6.250 -0.1754 0.05546 0.05321 -0.0886 0.9718 0.0247
-6.000 -0.1210 0.02387 0.02044 -0.1264 0.9621 0.0197
-5.750 -0.0866 0.02495 0.02169 -0.1276 0.9604 0.0214
-5.500 -0.0465 0.01917 0.01510 -0.1333 0.9581 0.0224
-5.250 -0.0154 0.01698 0.01248 -0.1346 0.9525 0.0237
-5.000 0.0172 0.01560 0.01073 -0.1359 0.9479 0.0250
-4.750 0.0496 0.01360 0.00852 -0.1376 0.9445 0.0278
-4.500 0.0790 0.01288 0.00769 -0.1380 0.9389 0.0299
-4.250 0.1090 0.01212 0.00676 -0.1384 0.9332 0.0319
-4.000 0.1412 0.01192 0.00643 -0.1390 0.9292 0.0335
-3.750 0.1674 0.01036 0.00472 -0.1389 0.9216 0.0368
-3.500 0.1973 0.00985 0.00414 -0.1392 0.9162 0.0392
-3.250 0.2250 0.00950 0.00374 -0.1391 0.9092 0.0418
-3.000 0.2537 0.00918 0.00333 -0.1391 0.9029 0.0437
-2.750 0.2817 0.00882 0.00290 -0.1390 0.8962 0.0454
-2.500 0.3098 0.00842 0.00245 -0.1389 0.8895 0.0500
-2.250 0.3379 0.00823 0.00221 -0.1389 0.8830 0.0545
-2.000 0.3657 0.00801 0.00197 -0.1387 0.8760 0.0636
-1.750 0.3936 0.00766 0.00185 -0.1387 0.8696 0.1335
-1.500 0.4209 0.00752 0.00179 -0.1385 0.8624 0.1726
-1.250 0.4488 0.00742 0.00174 -0.1384 0.8560 0.2069
-1.000 0.4759 0.00729 0.00172 -0.1382 0.8484 0.2487
-0.750 0.5035 0.00719 0.00171 -0.1381 0.8419 0.3013
-0.500 0.5304 0.00708 0.00174 -0.1378 0.8341 0.3552
-0.250 0.5577 0.00698 0.00176 -0.1376 0.8270 0.4165
0.000 0.5841 0.00682 0.00180 -0.1372 0.8176 0.4976
0.250 0.6096 0.00660 0.00185 -0.1366 0.8067 0.6034
0.500 0.6353 0.00582 0.00184 -0.1358 0.7967 1.0000
0.750 0.6623 0.00589 0.00182 -0.1354 0.7867 1.0000
1.000 0.6890 0.00595 0.00183 -0.1350 0.7755 1.0000
1.250 0.7159 0.00602 0.00184 -0.1346 0.7648 1.0000
1.500 0.7429 0.00610 0.00188 -0.1343 0.7548 1.0000
1.750 0.7696 0.00617 0.00191 -0.1339 0.7436 1.0000
2.000 0.7961 0.00625 0.00195 -0.1334 0.7305 1.0000
2.250 0.8225 0.00634 0.00200 -0.1330 0.7163 1.0000
2.500 0.8487 0.00645 0.00208 -0.1325 0.7012 1.0000
2.750 0.8741 0.00658 0.00214 -0.1318 0.6796 1.0000
3.000 0.8985 0.00677 0.00221 -0.1309 0.6501 1.0000
3.250 0.9230 0.00699 0.00232 -0.1301 0.6227 1.0000
3.500 0.9473 0.00725 0.00247 -0.1292 0.5948 1.0000
3.750 0.9715 0.00751 0.00264 -0.1284 0.5673 1.0000
4.000 0.9953 0.00782 0.00283 -0.1276 0.5354 1.0000
4.250 1.0188 0.00816 0.00305 -0.1267 0.5021 1.0000
4.500 1.0408 0.00861 0.00332 -0.1255 0.4547 1.0000
4.750 1.0613 0.00922 0.00364 -0.1242 0.3884 1.0000
5.000 1.0789 0.01016 0.00413 -0.1225 0.3022 1.0000
5.250 1.0947 0.01137 0.00477 -0.1207 0.1963 1.0000
5.500 1.1135 0.01229 0.00537 -0.1193 0.1395 1.0000
5.750 1.1300 0.01345 0.00609 -0.1175 0.0652 1.0000
6.000 1.1510 0.01414 0.00669 -0.1163 0.0478 1.0000
6.250 1.1720 0.01482 0.00736 -0.1151 0.0402 1.0000
6.500 1.1941 0.01535 0.00795 -0.1141 0.0361 1.0000
7.000 1.2338 0.01683 0.00954 -0.1113 0.0280 1.0000
7.250 1.2540 0.01748 0.01023 -0.1100 0.0252 1.0000
7.500 1.2651 0.01909 0.01191 -0.1073 0.0222 1.0000
7.750 1.2867 0.01955 0.01244 -0.1062 0.0210 1.0000
8.000 1.3066 0.02016 0.01311 -0.1049 0.0193 1.0000
8.250 1.3258 0.02080 0.01379 -0.1036 0.0179 1.0000
8.500 1.3385 0.02214 0.01518 -0.1012 0.0166 1.0000
8.750 1.3507 0.02378 0.01694 -0.0988 0.0157 1.0000
9.000 1.3674 0.02472 0.01799 -0.0970 0.0151 1.0000
9.250 1.3825 0.02586 0.01924 -0.0951 0.0145 1.0000
9.500 1.3971 0.02697 0.02044 -0.0931 0.0138 1.0000
9.750 1.4107 0.02785 0.02141 -0.0910 0.0130 1.0000
10.000 1.4230 0.02878 0.02239 -0.0889 0.0124 1.0000
10.250 1.4335 0.03115 0.02488 -0.0869 0.0117 1.0000
10.500 1.4455 0.03397 0.02796 -0.0850 0.0113 1.0000
10.750 1.4548 0.03558 0.02977 -0.0826 0.0111 1.0000
11.000 1.4621 0.03755 0.03195 -0.0801 0.0108 1.0000
11.250 1.4665 0.03988 0.03452 -0.0775 0.0106 1.0000
11.500 1.4672 0.04256 0.03746 -0.0747 0.0104 1.0000
11.750 1.4640 0.04557 0.04074 -0.0718 0.0102 1.0000
12.000 1.4568 0.04895 0.04440 -0.0691 0.0101 1.0000
12.250 1.4456 0.05280 0.04853 -0.0666 0.0100 1.0000
12.500 1.4306 0.05721 0.05324 -0.0646 0.0100 1.0000
12.750 1.4124 0.06216 0.05846 -0.0632 0.0100 1.0000
13.000 1.3913 0.06777 0.06433 -0.0628 0.0100 1.0000
13.250 1.3685 0.07397 0.07076 -0.0634 0.0101 1.0000
13.500 1.3447 0.08082 0.07785 -0.0651 0.0101 1.0000
13.750 1.3202 0.08839 0.08562 -0.0681 0.0102 1.0000
14.000 1.2959 0.09674 0.09417 -0.0723 0.0103 1.0000
14.250 1.2721 0.10589 0.10350 -0.0777 0.0104 1.0000
14.500 1.2482 0.11616 0.11393 -0.0843 0.0106 1.0000
14.750 1.2241 0.12783 0.12574 -0.0923 0.0107 1.0000
15.000 1.1974 0.14193 0.13997 -0.1019 0.0110 1.0000
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Polar data table (+)
Polar graphs
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