E230 (9.96%) (e230-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E230 (9.96%) (e230-il) Reynolds number: 500,000 Max Cl/Cd: 50.38 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e230-il-500000.txt Download as CSV file: xf-e230-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -1.0547 0.03144 0.02622 0.0169 1.0000 0.0121
-9.250 -1.0382 0.02979 0.02436 0.0183 1.0000 0.0120
-9.000 -1.0207 0.02799 0.02236 0.0195 1.0000 0.0119
-8.750 -1.0020 0.02614 0.02031 0.0207 1.0000 0.0119
-8.500 -0.9834 0.02385 0.01783 0.0218 1.0000 0.0120
-8.250 -0.9650 0.02163 0.01547 0.0230 1.0000 0.0123
-8.000 -0.9451 0.02014 0.01389 0.0241 1.0000 0.0126
-7.750 -0.9243 0.01893 0.01258 0.0252 1.0000 0.0126
-7.500 -0.9038 0.01776 0.01133 0.0263 1.0000 0.0128
-7.250 -0.8828 0.01675 0.01025 0.0274 1.0000 0.0131
-7.000 -0.8611 0.01588 0.00931 0.0284 1.0000 0.0134
-6.750 -0.8386 0.01509 0.00846 0.0293 1.0000 0.0139
-6.500 -0.8155 0.01437 0.00768 0.0301 1.0000 0.0146
-6.250 -0.7916 0.01375 0.00698 0.0308 1.0000 0.0154
-6.000 -0.7671 0.01319 0.00635 0.0313 1.0000 0.0160
-5.750 -0.7433 0.01251 0.00561 0.0320 1.0000 0.0179
-5.500 -0.7179 0.01205 0.00512 0.0325 1.0000 0.0212
-5.250 -0.6966 0.01103 0.00440 0.0335 1.0000 0.0627
-5.000 -0.6740 0.01027 0.00395 0.0341 1.0000 0.1189
-4.750 -0.6501 0.00975 0.00364 0.0345 1.0000 0.1624
-4.500 -0.6271 0.00929 0.00338 0.0352 1.0000 0.2048
-4.250 -0.5942 0.00882 0.00313 0.0337 0.9870 0.2571
-4.000 -0.5598 0.00841 0.00292 0.0320 0.9745 0.3102
-3.750 -0.5310 0.00804 0.00276 0.0316 0.9601 0.3635
-3.500 -0.5089 0.00777 0.00265 0.0329 0.9443 0.4099
-3.250 -0.4885 0.00753 0.00253 0.0347 0.9291 0.4539
-3.000 -0.4674 0.00732 0.00242 0.0363 0.9150 0.4913
-2.750 -0.4455 0.00711 0.00231 0.0377 0.9017 0.5282
-2.500 -0.4229 0.00691 0.00219 0.0390 0.8885 0.5655
-2.250 -0.3998 0.00671 0.00208 0.0402 0.8752 0.6046
-2.000 -0.3765 0.00651 0.00199 0.0414 0.8619 0.6430
-1.750 -0.3526 0.00634 0.00191 0.0425 0.8485 0.6800
-1.500 -0.3286 0.00618 0.00183 0.0435 0.8349 0.7151
-1.250 -0.3040 0.00604 0.00177 0.0445 0.8209 0.7499
-0.750 -0.2533 0.00582 0.00170 0.0462 0.7922 0.8150
-0.500 -0.2265 0.00576 0.00168 0.0468 0.7772 0.8447
-0.250 -0.1982 0.00574 0.00168 0.0470 0.7617 0.8718
0.000 -0.1666 0.00576 0.00172 0.0466 0.7455 0.8936
0.250 -0.1330 0.00584 0.00177 0.0456 0.7285 0.9114
0.500 -0.0975 0.00596 0.00184 0.0443 0.7105 0.9245
0.750 -0.0621 0.00609 0.00192 0.0429 0.6910 0.9350
1.000 -0.0300 0.00624 0.00200 0.0423 0.6705 0.9452
1.250 0.0089 0.00643 0.00211 0.0401 0.6482 0.9500
1.500 0.0401 0.00661 0.00222 0.0396 0.6251 0.9585
1.750 0.0800 0.00679 0.00232 0.0372 0.6003 0.9615
2.000 0.1175 0.00698 0.00242 0.0352 0.5732 0.9661
2.500 0.1900 0.00735 0.00262 0.0318 0.5153 0.9753
2.750 0.2274 0.00754 0.00272 0.0297 0.4835 0.9796
3.000 0.2617 0.00776 0.00284 0.0283 0.4491 0.9845
3.250 0.3011 0.00796 0.00291 0.0257 0.4056 0.9871
3.500 0.3387 0.00821 0.00299 0.0234 0.3577 0.9904
3.750 0.3747 0.00851 0.00311 0.0214 0.3086 0.9940
4.000 0.4120 0.00882 0.00320 0.0190 0.2521 0.9965
4.250 0.4494 0.00914 0.00333 0.0166 0.2022 0.9993
4.500 0.4776 0.00948 0.00351 0.0161 0.1589 1.0000
5.250 0.5491 0.01110 0.00446 0.0172 0.0303 1.0000
5.500 0.5730 0.01157 0.00492 0.0178 0.0227 1.0000
5.750 0.5965 0.01209 0.00549 0.0185 0.0203 1.0000
6.000 0.6200 0.01253 0.00600 0.0192 0.0192 1.0000
6.250 0.6429 0.01304 0.00657 0.0200 0.0183 1.0000
6.500 0.6654 0.01363 0.00724 0.0208 0.0175 1.0000
6.750 0.6872 0.01433 0.00799 0.0217 0.0168 1.0000
7.000 0.7080 0.01516 0.00889 0.0227 0.0164 1.0000
7.250 0.7275 0.01622 0.01002 0.0239 0.0159 1.0000
7.500 0.7447 0.01781 0.01172 0.0253 0.0154 1.0000
7.750 0.7653 0.01857 0.01258 0.0265 0.0151 1.0000
8.000 0.7843 0.01974 0.01388 0.0278 0.0150 1.0000
8.250 0.8029 0.02097 0.01523 0.0291 0.0149 1.0000
8.500 0.8208 0.02233 0.01675 0.0305 0.0147 1.0000
8.750 0.8373 0.02393 0.01853 0.0320 0.0147 1.0000
9.000 0.8521 0.02580 0.02061 0.0337 0.0146 1.0000
9.250 0.8642 0.02802 0.02310 0.0355 0.0146 1.0000
9.500 0.8720 0.03077 0.02614 0.0376 0.0148 1.0000
9.750 0.8730 0.03545 0.03106 0.0397 0.0155 1.0000
10.000 0.8866 0.03618 0.03195 0.0414 0.0158 1.0000
11.750 0.6302 0.10286 0.10050 0.0180 0.0286 1.0000
12.000 0.6297 0.10693 0.10456 0.0165 0.0283 1.0000
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Polar data table (+)
Polar graphs
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