E230 (9.96%) (e230-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E230 (9.96%) (e230-il) Reynolds number: 1,000,000 Max Cl/Cd: 57.71 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e230-il-1000000.txt Download as CSV file: xf-e230-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E230 (9.96%)
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
------ -------- --------- --------- -------- -------- --------
-11.500 -1.0672 0.04689 0.04415 -0.0010 1.0000 0.0081
-11.250 -1.0991 0.04212 0.03912 0.0023 1.0000 0.0077
-11.000 -1.1617 0.03363 0.02981 0.0115 1.0000 0.0067
-10.750 -1.1515 0.03236 0.02847 0.0133 1.0000 0.0069
-10.500 -1.1474 0.02975 0.02557 0.0159 1.0000 0.0068
-10.250 -1.1355 0.02807 0.02374 0.0177 1.0000 0.0070
-10.000 -1.1220 0.02637 0.02187 0.0194 1.0000 0.0070
-9.750 -1.1063 0.02486 0.02021 0.0209 1.0000 0.0072
-9.500 -1.0888 0.02356 0.01877 0.0221 1.0000 0.0073
-9.250 -1.0710 0.02210 0.01717 0.0235 1.0000 0.0074
-9.000 -1.0520 0.02083 0.01576 0.0247 1.0000 0.0074
-8.750 -1.0321 0.01966 0.01447 0.0258 1.0000 0.0075
-8.500 -1.0114 0.01864 0.01336 0.0268 1.0000 0.0076
-8.250 -0.9906 0.01762 0.01225 0.0279 1.0000 0.0077
-8.000 -0.9691 0.01671 0.01126 0.0288 1.0000 0.0078
-7.750 -0.9474 0.01585 0.01032 0.0298 1.0000 0.0079
-7.500 -0.9247 0.01511 0.00951 0.0306 1.0000 0.0081
-7.250 -0.9012 0.01448 0.00882 0.0313 1.0000 0.0083
-7.000 -0.8771 0.01391 0.00820 0.0319 1.0000 0.0085
-6.750 -0.8531 0.01332 0.00755 0.0325 1.0000 0.0086
-6.500 -0.8321 0.01227 0.00639 0.0337 1.0000 0.0090
-6.250 -0.8080 0.01163 0.00569 0.0343 1.0000 0.0096
-6.000 -0.7823 0.01117 0.00520 0.0346 1.0000 0.0101
-5.750 -0.7561 0.01078 0.00477 0.0349 1.0000 0.0107
-5.500 -0.7268 0.01043 0.00438 0.0344 0.9868 0.0114
-5.250 -0.6955 0.01009 0.00399 0.0337 0.9674 0.0126
-5.000 -0.6724 0.00982 0.00369 0.0348 0.9494 0.0157
-4.750 -0.6536 0.00915 0.00324 0.0367 0.9339 0.0590
-4.500 -0.6327 0.00861 0.00292 0.0380 0.9204 0.1059
-4.250 -0.6098 0.00822 0.00268 0.0390 0.9077 0.1438
-4.000 -0.5865 0.00785 0.00245 0.0399 0.8955 0.1856
-3.750 -0.5620 0.00756 0.00226 0.0406 0.8836 0.2195
-3.500 -0.5373 0.00730 0.00209 0.0412 0.8715 0.2535
-3.250 -0.5125 0.00700 0.00192 0.0418 0.8592 0.2966
-3.000 -0.4875 0.00670 0.00177 0.0424 0.8466 0.3414
-2.750 -0.4627 0.00640 0.00163 0.0430 0.8340 0.3933
-2.500 -0.4372 0.00616 0.00151 0.0435 0.8210 0.4347
-2.250 -0.4111 0.00598 0.00140 0.0439 0.8078 0.4688
-2.000 -0.3851 0.00582 0.00130 0.0443 0.7940 0.5028
-1.750 -0.3592 0.00564 0.00121 0.0448 0.7800 0.5397
-1.500 -0.3332 0.00549 0.00113 0.0452 0.7657 0.5764
-1.250 -0.3072 0.00534 0.00106 0.0457 0.7507 0.6114
-1.000 -0.2812 0.00521 0.00101 0.0462 0.7355 0.6460
-0.750 -0.2552 0.00509 0.00096 0.0467 0.7198 0.6802
-0.500 -0.2294 0.00498 0.00092 0.0472 0.7036 0.7135
-0.250 -0.2035 0.00488 0.00089 0.0478 0.6868 0.7466
0.000 -0.1777 0.00479 0.00087 0.0483 0.6694 0.7793
0.250 -0.1517 0.00473 0.00085 0.0489 0.6513 0.8104
0.500 -0.1254 0.00468 0.00086 0.0494 0.6327 0.8401
0.750 -0.0984 0.00465 0.00087 0.0498 0.6127 0.8669
1.000 -0.0702 0.00466 0.00090 0.0499 0.5921 0.8913
1.250 -0.0399 0.00471 0.00095 0.0495 0.5708 0.9126
1.500 -0.0072 0.00482 0.00103 0.0486 0.5474 0.9292
1.750 0.0281 0.00496 0.00112 0.0470 0.5223 0.9403
2.000 0.0626 0.00513 0.00122 0.0457 0.4961 0.9485
2.250 0.0925 0.00531 0.00131 0.0453 0.4711 0.9577
2.500 0.1279 0.00550 0.00143 0.0437 0.4435 0.9614
2.750 0.1627 0.00572 0.00155 0.0422 0.4137 0.9651
3.000 0.1903 0.00597 0.00168 0.0423 0.3769 0.9719
3.250 0.2274 0.00625 0.00181 0.0402 0.3343 0.9735
3.500 0.2636 0.00655 0.00196 0.0382 0.2915 0.9755
3.750 0.2985 0.00687 0.00211 0.0365 0.2471 0.9781
4.000 0.3309 0.00723 0.00229 0.0354 0.2037 0.9815
4.250 0.3622 0.00758 0.00250 0.0345 0.1662 0.9847
4.500 0.3983 0.00794 0.00269 0.0324 0.1255 0.9859
4.750 0.4335 0.00836 0.00292 0.0305 0.0855 0.9875
5.000 0.4675 0.00898 0.00328 0.0288 0.0356 0.9893
5.250 0.5013 0.00949 0.00367 0.0273 0.0163 0.9915
5.500 0.5346 0.00980 0.00401 0.0260 0.0146 0.9936
5.750 0.5687 0.01011 0.00437 0.0246 0.0137 0.9951
6.000 0.6034 0.01050 0.00479 0.0229 0.0127 0.9964
6.250 0.6371 0.01104 0.00540 0.0214 0.0119 0.9979
6.500 0.6702 0.01178 0.00625 0.0200 0.0113 0.9993
6.750 0.6994 0.01217 0.00668 0.0194 0.0110 1.0000
7.000 0.7219 0.01269 0.00726 0.0202 0.0108 1.0000
7.250 0.7440 0.01326 0.00789 0.0211 0.0106 1.0000
7.500 0.7656 0.01391 0.00860 0.0220 0.0104 1.0000
7.750 0.7868 0.01456 0.00933 0.0230 0.0102 1.0000
8.000 0.8071 0.01537 0.01022 0.0241 0.0101 1.0000
8.250 0.8272 0.01616 0.01108 0.0252 0.0099 1.0000
8.500 0.8468 0.01697 0.01197 0.0264 0.0097 1.0000
8.750 0.8658 0.01786 0.01294 0.0276 0.0095 1.0000
9.000 0.8842 0.01880 0.01397 0.0289 0.0093 1.0000
9.250 0.9021 0.01974 0.01499 0.0302 0.0090 1.0000
9.500 0.9184 0.02089 0.01623 0.0316 0.0089 1.0000
9.750 0.9333 0.02222 0.01767 0.0332 0.0088 1.0000
10.000 0.9463 0.02378 0.01937 0.0349 0.0087 1.0000
10.250 0.9550 0.02592 0.02167 0.0370 0.0085 1.0000
10.500 0.9595 0.02844 0.02441 0.0393 0.0084 1.0000
10.750 0.9593 0.03123 0.02743 0.0419 0.0083 1.0000
11.000 0.9577 0.03364 0.03005 0.0445 0.0083 1.0000
11.250 0.9548 0.03572 0.03230 0.0471 0.0083 1.0000
11.500 0.9430 0.03743 0.03414 0.0509 0.0083 1.0000
11.750 0.9327 0.03949 0.03633 0.0530 0.0084 1.0000
12.000 0.9267 0.04177 0.03874 0.0534 0.0084 1.0000
12.250 0.9169 0.04505 0.04217 0.0526 0.0084 1.0000
12.500 0.8960 0.05051 0.04781 0.0498 0.0084 1.0000
12.750 0.8946 0.05385 0.05125 0.0473 0.0085 1.0000
13.000 0.8773 0.06027 0.05784 0.0426 0.0085 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E230 (9.96%) (e230-il)