E471 (6.25%) (e471-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E471 (6.25%) (e471-il) Reynolds number: 200,000 Max Cl/Cd: 101.11 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e471-il-200000-n5.txt Download as CSV file: xf-e471-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E471 (6.25%)
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2357 0.08557 0.08233 -0.0435 0.9861 0.0197
-7.750 -0.2252 0.08157 0.07833 -0.0462 0.9838 0.0206
-7.500 -0.3246 0.09361 0.09030 -0.0375 0.9907 0.0184
-7.250 -0.3114 0.09022 0.08687 -0.0402 0.9870 0.0191
-7.000 -0.2966 0.08678 0.08343 -0.0440 0.9834 0.0197
-6.750 -0.2848 0.08341 0.08007 -0.0472 0.9776 0.0204
-6.500 -0.2659 0.07938 0.07604 -0.0525 0.9726 0.0213
-6.250 -0.2431 0.07501 0.07166 -0.0593 0.9687 0.0225
-6.000 -0.2259 0.07104 0.06769 -0.0646 0.9615 0.0237
-5.000 -0.0768 0.05011 0.04633 -0.1065 0.9447 0.0381
-4.500 -0.0175 0.03720 0.03309 -0.1178 0.9359 0.0230
-4.250 0.0401 0.02773 0.02281 -0.1290 0.9349 0.0191
-4.000 0.0854 0.02317 0.01752 -0.1342 0.9338 0.0181
-3.750 0.1254 0.02043 0.01423 -0.1376 0.9327 0.0182
-3.500 0.1636 0.01845 0.01182 -0.1403 0.9316 0.0188
-3.250 0.1937 0.01734 0.01044 -0.1411 0.9277 0.0203
-3.000 0.2249 0.01659 0.00950 -0.1420 0.9242 0.0229
-2.750 0.2595 0.01547 0.00818 -0.1434 0.9220 0.0228
-2.500 0.2947 0.01455 0.00712 -0.1449 0.9203 0.0227
-2.250 0.3308 0.01379 0.00627 -0.1467 0.9189 0.0226
-2.000 0.3629 0.01328 0.00564 -0.1476 0.9155 0.0227
-1.750 0.3933 0.01291 0.00517 -0.1482 0.9111 0.0231
-1.500 0.4275 0.01257 0.00472 -0.1494 0.9083 0.0239
-1.250 0.4626 0.01227 0.00433 -0.1509 0.9060 0.0258
-1.000 0.4949 0.01193 0.00408 -0.1518 0.9022 0.0539
-0.750 0.5261 0.01142 0.00401 -0.1529 0.8973 0.1937
-0.500 0.5610 0.01056 0.00411 -0.1550 0.8941 0.4921
-0.250 0.5785 0.00958 0.00414 -0.1520 0.8892 0.8649
0.000 0.6062 0.00943 0.00396 -0.1516 0.8822 1.0000
0.250 0.6414 0.00934 0.00377 -0.1530 0.8780 1.0000
0.500 0.6693 0.00937 0.00374 -0.1529 0.8694 1.0000
0.750 0.7028 0.00931 0.00361 -0.1539 0.8632 1.0000
1.000 0.7319 0.00932 0.00359 -0.1540 0.8540 1.0000
1.250 0.7617 0.00932 0.00355 -0.1542 0.8445 1.0000
1.500 0.7925 0.00931 0.00350 -0.1547 0.8348 1.0000
1.750 0.8228 0.00931 0.00348 -0.1549 0.8241 1.0000
2.000 0.8511 0.00936 0.00354 -0.1548 0.8111 1.0000
2.500 0.9065 0.00948 0.00364 -0.1543 0.7810 1.0000
2.750 0.9335 0.00957 0.00372 -0.1540 0.7632 1.0000
3.000 0.9607 0.00967 0.00380 -0.1536 0.7425 1.0000
3.250 0.9868 0.00982 0.00395 -0.1530 0.7167 1.0000
3.500 1.0121 0.01001 0.00408 -0.1522 0.6846 1.0000
3.750 1.0362 0.01029 0.00424 -0.1511 0.6431 1.0000
4.000 1.0580 0.01071 0.00445 -0.1497 0.5890 1.0000
4.250 1.0770 0.01134 0.00477 -0.1478 0.5229 1.0000
4.500 1.0917 0.01229 0.00526 -0.1453 0.4354 1.0000
4.750 1.1013 0.01376 0.00597 -0.1422 0.3092 1.0000
5.000 1.1155 0.01506 0.00676 -0.1401 0.2118 1.0000
5.250 1.1347 0.01595 0.00740 -0.1388 0.1594 1.0000
5.500 1.1540 0.01687 0.00809 -0.1375 0.1122 1.0000
5.750 1.1712 0.01805 0.00893 -0.1360 0.0576 1.0000
6.000 1.1876 0.01940 0.00997 -0.1342 0.0166 1.0000
6.250 1.2076 0.02032 0.01093 -0.1328 0.0112 1.0000
6.500 1.2277 0.02122 0.01195 -0.1314 0.0096 1.0000
6.750 1.2468 0.02225 0.01313 -0.1299 0.0086 1.0000
7.000 1.2640 0.02353 0.01469 -0.1280 0.0080 1.0000
7.250 1.2793 0.02498 0.01632 -0.1259 0.0077 1.0000
7.500 1.2949 0.02641 0.01791 -0.1239 0.0076 1.0000
7.750 1.3101 0.02801 0.01969 -0.1218 0.0075 1.0000
8.000 1.3259 0.02978 0.02163 -0.1199 0.0073 1.0000
8.250 1.3431 0.03144 0.02348 -0.1183 0.0069 1.0000
8.500 1.3601 0.03310 0.02536 -0.1167 0.0063 1.0000
8.750 1.3763 0.03503 0.02752 -0.1150 0.0057 1.0000
9.000 1.3914 0.03751 0.03030 -0.1131 0.0056 1.0000
9.250 1.4038 0.04028 0.03342 -0.1110 0.0054 1.0000
9.500 1.4120 0.04323 0.03680 -0.1083 0.0053 1.0000
9.750 1.4148 0.04638 0.04033 -0.1050 0.0052 1.0000
10.000 1.4125 0.04968 0.04400 -0.1013 0.0052 1.0000
10.250 1.4059 0.05318 0.04786 -0.0975 0.0052 1.0000
10.500 1.3955 0.05694 0.05197 -0.0938 0.0052 1.0000
10.750 1.3820 0.06105 0.05642 -0.0906 0.0052 1.0000
11.000 1.3661 0.06553 0.06122 -0.0881 0.0052 1.0000
11.250 1.3479 0.07054 0.06652 -0.0866 0.0052 1.0000
11.500 1.3287 0.07602 0.07226 -0.0860 0.0052 1.0000
11.750 1.3087 0.08207 0.07856 -0.0868 0.0053 1.0000
12.000 1.2880 0.08883 0.08554 -0.0888 0.0053 1.0000
12.250 1.2667 0.09656 0.09348 -0.0924 0.0054 1.0000
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Polar data table (+)
Polar graphs
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