E230 (9.96%) (e230-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E230 (9.96%) (e230-il) Reynolds number: 200,000 Max Cl/Cd: 41.58 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e230-il-200000.txt Download as CSV file: xf-e230-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.9873 0.04543 0.03984 0.0101 1.0000 0.0284
-9.000 -0.9762 0.04096 0.03516 0.0113 1.0000 0.0272
-8.750 -0.9678 0.03690 0.03072 0.0132 1.0000 0.0264
-8.500 -0.9550 0.03346 0.02688 0.0150 1.0000 0.0257
-8.250 -0.9381 0.03051 0.02354 0.0165 1.0000 0.0253
-8.000 -0.9180 0.02802 0.02074 0.0177 1.0000 0.0252
-7.750 -0.8959 0.02593 0.01840 0.0187 1.0000 0.0253
-7.500 -0.8731 0.02413 0.01643 0.0196 1.0000 0.0259
-7.250 -0.8504 0.02257 0.01474 0.0205 1.0000 0.0267
-7.000 -0.8280 0.02125 0.01331 0.0215 1.0000 0.0275
-6.750 -0.8085 0.01968 0.01170 0.0228 1.0000 0.0295
-6.500 -0.7879 0.01859 0.01060 0.0238 1.0000 0.0326
-6.250 -0.7665 0.01760 0.00952 0.0250 1.0000 0.0356
-6.000 -0.7471 0.01637 0.00827 0.0265 1.0000 0.0418
-5.750 -0.7310 0.01460 0.00689 0.0284 1.0000 0.0967
-5.500 -0.7110 0.01357 0.00627 0.0294 1.0000 0.1686
-5.250 -0.6892 0.01289 0.00583 0.0302 1.0000 0.2238
-5.000 -0.6673 0.01230 0.00546 0.0310 1.0000 0.2765
-4.750 -0.6459 0.01175 0.00515 0.0319 1.0000 0.3307
-4.500 -0.6249 0.01127 0.00489 0.0331 1.0000 0.3850
-4.250 -0.6042 0.01084 0.00462 0.0343 1.0000 0.4309
-4.000 -0.5846 0.01046 0.00441 0.0358 1.0000 0.4742
-3.750 -0.5675 0.01013 0.00423 0.0378 1.0000 0.5169
-3.500 -0.5523 0.00983 0.00409 0.0402 1.0000 0.5573
-3.250 -0.5378 0.00958 0.00399 0.0427 1.0000 0.5982
-3.000 -0.5232 0.00937 0.00392 0.0452 1.0000 0.6396
-2.750 -0.4920 0.00918 0.00391 0.0444 0.9942 0.6882
-2.500 -0.4494 0.00905 0.00392 0.0415 0.9856 0.7376
-2.250 -0.4057 0.00897 0.00395 0.0386 0.9775 0.7800
-2.000 -0.3597 0.00896 0.00402 0.0353 0.9702 0.8166
-1.750 -0.3146 0.00902 0.00411 0.0323 0.9612 0.8465
-1.500 -0.2722 0.00914 0.00422 0.0300 0.9501 0.8712
-1.250 -0.2300 0.00933 0.00439 0.0278 0.9380 0.8892
-1.000 -0.1924 0.00953 0.00455 0.0266 0.9235 0.9041
-0.750 -0.1583 0.00975 0.00472 0.0262 0.9075 0.9174
-0.500 -0.1202 0.00997 0.00489 0.0250 0.8916 0.9270
-0.250 -0.0825 0.01016 0.00502 0.0237 0.8750 0.9359
0.000 -0.0480 0.01031 0.00511 0.0230 0.8573 0.9467
0.250 -0.0101 0.01044 0.00518 0.0214 0.8379 0.9564
0.500 0.0299 0.01050 0.00519 0.0194 0.8179 0.9645
0.750 0.0677 0.01053 0.00516 0.0177 0.7972 0.9741
1.000 0.1079 0.01051 0.00509 0.0153 0.7737 0.9829
1.250 0.1504 0.01039 0.00490 0.0124 0.7488 0.9902
1.500 0.1925 0.01024 0.00468 0.0096 0.7219 0.9978
1.750 0.2199 0.01015 0.00452 0.0095 0.6956 1.0000
2.000 0.2411 0.01011 0.00441 0.0106 0.6689 1.0000
2.250 0.2628 0.01010 0.00433 0.0117 0.6417 1.0000
2.500 0.2850 0.01013 0.00427 0.0127 0.6132 1.0000
2.750 0.3076 0.01018 0.00425 0.0137 0.5834 1.0000
3.000 0.3306 0.01026 0.00425 0.0146 0.5524 1.0000
3.250 0.3539 0.01037 0.00428 0.0154 0.5199 1.0000
3.500 0.3773 0.01052 0.00433 0.0161 0.4854 1.0000
3.750 0.4011 0.01069 0.00443 0.0168 0.4471 1.0000
4.000 0.4249 0.01091 0.00455 0.0174 0.4083 1.0000
4.250 0.4488 0.01118 0.00469 0.0180 0.3639 1.0000
4.500 0.4725 0.01153 0.00489 0.0185 0.3127 1.0000
4.750 0.4961 0.01196 0.00512 0.0190 0.2603 1.0000
5.000 0.5193 0.01249 0.00542 0.0194 0.2061 1.0000
5.250 0.5424 0.01306 0.00580 0.0198 0.1563 1.0000
5.500 0.5649 0.01382 0.00633 0.0203 0.1035 1.0000
5.750 0.5854 0.01539 0.00755 0.0211 0.0494 1.0000
6.000 0.6064 0.01648 0.00867 0.0222 0.0416 1.0000
6.250 0.6271 0.01740 0.00959 0.0231 0.0372 1.0000
6.500 0.6466 0.01861 0.01084 0.0244 0.0343 1.0000
6.750 0.6670 0.01967 0.01201 0.0256 0.0328 1.0000
7.000 0.6872 0.02087 0.01330 0.0269 0.0316 1.0000
7.250 0.7073 0.02221 0.01474 0.0283 0.0307 1.0000
7.500 0.7272 0.02371 0.01637 0.0296 0.0300 1.0000
7.750 0.7466 0.02547 0.01831 0.0309 0.0297 1.0000
8.000 0.7648 0.02755 0.02065 0.0324 0.0296 1.0000
8.250 0.7808 0.03014 0.02361 0.0340 0.0300 1.0000
8.500 0.7946 0.03261 0.02641 0.0356 0.0298 1.0000
8.750 0.8076 0.03484 0.02886 0.0371 0.0292 1.0000
9.000 0.8167 0.03754 0.03185 0.0388 0.0289 1.0000
9.250 0.8024 0.04378 0.03893 0.0420 0.0311 1.0000
9.500 0.7911 0.04856 0.04407 0.0440 0.0327 1.0000
9.750 0.7784 0.05276 0.04849 0.0457 0.0337 1.0000
10.000 0.7633 0.05695 0.05279 0.0471 0.0347 1.0000
10.250 0.6696 0.04673 0.04291 0.0500 0.0335 1.0000
10.500 0.6433 0.05212 0.04842 0.0477 0.0338 1.0000
10.750 0.6154 0.05917 0.05556 0.0437 0.0341 1.0000
11.000 0.5917 0.06710 0.06352 0.0400 0.0350 1.0000
11.250 0.5806 0.11319 0.10942 0.0128 0.0648 1.0000
11.500 0.5806 0.11727 0.11348 0.0111 0.0619 1.0000
11.750 0.5897 0.11956 0.11578 0.0116 0.0593 1.0000
12.000 0.5975 0.12252 0.11874 0.0119 0.0584 1.0000
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Polar data table (+)
Polar graphs
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