GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 494 AIRFOIL (goe494-il) Reynolds number: 200,000 Max Cl/Cd: 95.59 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe494-il-200000-n5.txt Download as CSV file: xf-goe494-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 494 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3361 0.10254 0.09907 -0.0304 1.0000 0.0225
-8.000 -0.3394 0.10090 0.09749 -0.0295 1.0000 0.0227
-7.750 -0.3459 0.09946 0.09612 -0.0279 1.0000 0.0228
-7.500 -0.3415 0.09684 0.09353 -0.0296 0.9978 0.0229
-7.250 -0.3258 0.09293 0.08962 -0.0342 0.9927 0.0229
-6.750 -0.2942 0.08309 0.07978 -0.0409 0.9842 0.0174
-6.250 -0.2398 0.07068 0.06733 -0.0611 0.9707 0.0137
-6.000 -0.2092 0.06504 0.06165 -0.0698 0.9670 0.0138
-5.750 -0.1921 0.06225 0.05887 -0.0725 0.9608 0.0151
-5.500 -0.1632 0.05954 0.05612 -0.0774 0.9571 0.0173
-5.250 -0.1218 0.05375 0.05024 -0.0883 0.9541 0.0180
-5.000 -0.0838 0.04795 0.04433 -0.0979 0.9471 0.0185
-4.750 -0.0292 0.04026 0.03639 -0.1119 0.9439 0.0204
-4.500 0.0435 0.02751 0.02270 -0.1300 0.9421 0.0237
-4.250 0.0753 0.02507 0.02008 -0.1333 0.9382 0.0262
-4.000 0.1093 0.02275 0.01736 -0.1360 0.9334 0.0301
-3.750 0.1475 0.02017 0.01408 -0.1388 0.9302 0.0330
-3.500 0.1829 0.01810 0.01162 -0.1413 0.9276 0.0364
-3.250 0.2124 0.01693 0.01016 -0.1419 0.9217 0.0377
-3.000 0.2445 0.01590 0.00886 -0.1430 0.9172 0.0388
-2.750 0.2777 0.01523 0.00798 -0.1441 0.9139 0.0414
-2.250 0.3370 0.01373 0.00614 -0.1449 0.9027 0.0407
-2.000 0.3682 0.01309 0.00539 -0.1455 0.8983 0.0402
-1.750 0.3959 0.01261 0.00485 -0.1454 0.8912 0.0397
-1.500 0.4267 0.01214 0.00431 -0.1460 0.8862 0.0394
-1.250 0.4541 0.01181 0.00395 -0.1458 0.8777 0.0392
-1.000 0.4840 0.01148 0.00357 -0.1461 0.8706 0.0392
-0.750 0.5115 0.01127 0.00330 -0.1459 0.8616 0.0394
-0.500 0.5399 0.01109 0.00306 -0.1459 0.8546 0.0399
-0.250 0.5679 0.01096 0.00288 -0.1459 0.8476 0.0406
0.000 0.5959 0.01085 0.00274 -0.1458 0.8409 0.0420
0.500 0.6518 0.01035 0.00265 -0.1459 0.8277 0.1746
0.750 0.6790 0.01004 0.00281 -0.1459 0.8208 0.3407
1.000 0.7063 0.00993 0.00291 -0.1458 0.8146 0.4100
1.250 0.7310 0.00935 0.00306 -0.1452 0.8078 0.6782
1.750 0.7853 0.00904 0.00309 -0.1443 0.7913 1.0000
2.250 0.8387 0.00922 0.00325 -0.1434 0.7677 1.0000
2.500 0.8649 0.00932 0.00333 -0.1428 0.7522 1.0000
2.750 0.8902 0.00946 0.00341 -0.1418 0.7288 1.0000
3.000 0.9149 0.00964 0.00353 -0.1408 0.7033 1.0000
3.250 0.9387 0.00982 0.00369 -0.1396 0.6711 1.0000
3.500 0.9607 0.01007 0.00381 -0.1381 0.6115 1.0000
3.750 0.9740 0.01103 0.00406 -0.1350 0.4774 1.0000
4.000 0.9791 0.01319 0.00498 -0.1313 0.2517 1.0000
4.250 0.9889 0.01529 0.00603 -0.1288 0.0650 1.0000
4.500 1.0079 0.01641 0.00701 -0.1273 0.0344 1.0000
4.750 1.0296 0.01717 0.00784 -0.1261 0.0250 1.0000
5.000 1.0497 0.01817 0.00896 -0.1246 0.0210 1.0000
5.250 1.0712 0.01892 0.00987 -0.1234 0.0175 1.0000
5.500 1.0907 0.01994 0.01099 -0.1219 0.0154 1.0000
5.750 1.1089 0.02120 0.01233 -0.1202 0.0140 1.0000
6.000 1.1251 0.02308 0.01428 -0.1181 0.0126 1.0000
6.250 1.1452 0.02474 0.01604 -0.1167 0.0112 1.0000
6.500 1.1677 0.02639 0.01783 -0.1156 0.0105 1.0000
6.750 1.1913 0.02843 0.02011 -0.1146 0.0099 1.0000
7.000 1.2152 0.03078 0.02271 -0.1135 0.0095 1.0000
7.250 1.2380 0.03346 0.02570 -0.1123 0.0092 1.0000
7.500 1.2581 0.03605 0.02862 -0.1108 0.0088 1.0000
7.750 1.2755 0.03774 0.03050 -0.1095 0.0081 1.0000
8.000 1.2892 0.04001 0.03298 -0.1080 0.0074 1.0000
8.250 1.2978 0.04436 0.03779 -0.1054 0.0071 1.0000
8.500 1.3058 0.04796 0.04183 -0.1026 0.0070 1.0000
8.750 1.3097 0.05184 0.04612 -0.0996 0.0070 1.0000
9.000 1.3093 0.05586 0.05052 -0.0964 0.0070 1.0000
9.250 1.3044 0.05990 0.05490 -0.0931 0.0070 1.0000
9.500 1.2949 0.06376 0.05905 -0.0895 0.0070 1.0000
9.750 1.2798 0.06727 0.06279 -0.0856 0.0070 1.0000
10.000 1.2630 0.07100 0.06672 -0.0824 0.0071 1.0000
10.250 1.2451 0.07519 0.07110 -0.0803 0.0071 1.0000
10.500 1.2278 0.07968 0.07579 -0.0792 0.0072 1.0000
10.750 1.2119 0.08426 0.08056 -0.0792 0.0072 1.0000
11.000 1.1967 0.08929 0.08577 -0.0801 0.0072 1.0000
11.250 1.1792 0.09534 0.09198 -0.0824 0.0073 1.0000
11.500 1.1627 0.10218 0.09899 -0.0860 0.0073 1.0000
11.750 1.1458 0.11078 0.10775 -0.0915 0.0075 1.0000
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Polar data table (+)
Polar graphs
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