E230 (9.96%) (e230-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E230 (9.96%) (e230-il) Reynolds number: 100,000 Max Cl/Cd: 32.62 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e230-il-100000.txt Download as CSV file: xf-e230-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7082 0.08491 0.08067 0.0062 1.0000 0.0562
-10.500 -0.7321 0.07626 0.07197 0.0015 1.0000 0.0545
-10.250 -0.8606 0.07511 0.07039 -0.0013 1.0000 0.0561
-10.000 -0.8778 0.07035 0.06553 -0.0018 1.0000 0.0549
-9.750 -0.8988 0.06587 0.06089 -0.0008 1.0000 0.0537
-9.500 -0.9190 0.06088 0.05562 0.0009 1.0000 0.0518
-9.250 -0.9543 0.05474 0.04845 0.0050 1.0000 0.0475
-9.000 -0.9463 0.05114 0.04452 0.0066 1.0000 0.0464
-8.750 -0.9402 0.04665 0.03970 0.0081 1.0000 0.0458
-8.500 -0.9312 0.04278 0.03542 0.0099 1.0000 0.0453
-8.250 -0.9194 0.03978 0.03191 0.0118 1.0000 0.0460
-8.000 -0.9046 0.03751 0.02910 0.0137 1.0000 0.0469
-7.750 -0.8853 0.03356 0.02486 0.0146 1.0000 0.0479
-7.500 -0.8622 0.03069 0.02182 0.0153 1.0000 0.0493
-7.250 -0.8378 0.02842 0.01942 0.0160 1.0000 0.0513
-7.000 -0.8130 0.02645 0.01732 0.0167 1.0000 0.0542
-6.750 -0.7883 0.02477 0.01544 0.0177 1.0000 0.0582
-6.500 -0.7687 0.02290 0.01370 0.0190 1.0000 0.0681
-6.250 -0.7521 0.02094 0.01193 0.0209 1.0000 0.0881
-6.000 -0.7402 0.01862 0.01018 0.0234 1.0000 0.1634
-5.750 -0.7231 0.01757 0.00950 0.0248 1.0000 0.2359
-5.500 -0.7060 0.01685 0.00909 0.0265 1.0000 0.3010
-5.250 -0.6872 0.01617 0.00857 0.0281 1.0000 0.3558
-5.000 -0.6678 0.01553 0.00812 0.0297 1.0000 0.4060
-4.750 -0.6480 0.01498 0.00771 0.0313 1.0000 0.4567
-4.500 -0.6279 0.01445 0.00739 0.0331 1.0000 0.5051
-4.250 -0.6076 0.01399 0.00708 0.0349 1.0000 0.5533
-4.000 -0.5872 0.01360 0.00685 0.0367 1.0000 0.6015
-3.750 -0.5668 0.01327 0.00667 0.0387 1.0000 0.6494
-3.500 -0.5454 0.01302 0.00657 0.0406 1.0000 0.6956
-3.250 -0.5225 0.01287 0.00651 0.0423 1.0000 0.7401
-3.000 -0.4971 0.01285 0.00655 0.0437 1.0000 0.7825
-2.750 -0.4633 0.01302 0.00673 0.0436 1.0000 0.8202
-2.500 -0.4251 0.01332 0.00697 0.0427 1.0000 0.8536
-2.250 -0.3759 0.01378 0.00732 0.0397 1.0000 0.8792
-2.000 -0.3277 0.01421 0.00763 0.0367 1.0000 0.9020
-1.750 -0.2660 0.01462 0.00789 0.0309 1.0000 0.9176
-1.500 -0.2080 0.01485 0.00802 0.0254 1.0000 0.9329
-1.250 -0.1521 0.01492 0.00800 0.0199 1.0000 0.9483
-1.000 -0.0968 0.01484 0.00788 0.0142 1.0000 0.9635
-0.750 -0.0408 0.01460 0.00763 0.0081 1.0000 0.9781
-0.500 0.0165 0.01421 0.00726 0.0014 1.0000 0.9920
-0.250 0.0589 0.01385 0.00695 -0.0032 1.0000 1.0000
0.000 0.0525 0.01408 0.00722 0.0001 1.0000 1.0000
0.250 0.1068 0.01400 0.00720 -0.0065 0.9781 1.0000
0.500 0.1678 0.01383 0.00710 -0.0135 0.9505 1.0000
0.750 0.2035 0.01378 0.00704 -0.0150 0.9163 1.0000
1.000 0.2184 0.01380 0.00704 -0.0123 0.8817 1.0000
1.250 0.2303 0.01381 0.00702 -0.0089 0.8514 1.0000
1.500 0.2426 0.01381 0.00699 -0.0054 0.8232 1.0000
1.750 0.2563 0.01379 0.00694 -0.0022 0.7964 1.0000
2.000 0.2716 0.01377 0.00687 0.0008 0.7697 1.0000
2.250 0.2889 0.01376 0.00682 0.0033 0.7414 1.0000
2.500 0.3072 0.01377 0.00678 0.0056 0.7128 1.0000
2.750 0.3265 0.01379 0.00678 0.0077 0.6834 1.0000
3.000 0.3466 0.01383 0.00676 0.0097 0.6528 1.0000
3.250 0.3671 0.01390 0.00676 0.0115 0.6210 1.0000
3.500 0.3884 0.01401 0.00682 0.0131 0.5862 1.0000
3.750 0.4101 0.01416 0.00693 0.0147 0.5495 1.0000
4.000 0.4320 0.01436 0.00705 0.0161 0.5105 1.0000
4.250 0.4540 0.01462 0.00720 0.0174 0.4686 1.0000
4.500 0.4761 0.01494 0.00742 0.0186 0.4226 1.0000
4.750 0.4981 0.01536 0.00773 0.0197 0.3729 1.0000
5.000 0.5197 0.01593 0.00811 0.0207 0.3208 1.0000
5.250 0.5408 0.01663 0.00858 0.0217 0.2632 1.0000
5.500 0.5614 0.01736 0.00906 0.0223 0.1983 1.0000
5.750 0.5807 0.01860 0.00997 0.0232 0.1374 1.0000
6.000 0.5981 0.02060 0.01165 0.0246 0.0878 1.0000
6.250 0.6171 0.02209 0.01302 0.0260 0.0719 1.0000
6.500 0.6372 0.02384 0.01479 0.0275 0.0651 1.0000
6.750 0.6584 0.02544 0.01647 0.0288 0.0607 1.0000
7.000 0.6792 0.02753 0.01857 0.0300 0.0579 1.0000
7.250 0.6994 0.03011 0.02137 0.0313 0.0562 1.0000
7.500 0.7182 0.03208 0.02380 0.0328 0.0541 1.0000
7.750 0.7347 0.03450 0.02663 0.0342 0.0523 1.0000
8.000 0.7479 0.03761 0.03020 0.0358 0.0522 1.0000
8.250 0.7572 0.04120 0.03424 0.0375 0.0528 1.0000
8.500 0.7620 0.04516 0.03862 0.0391 0.0536 1.0000
8.750 0.7637 0.04927 0.04306 0.0406 0.0547 1.0000
9.000 0.7636 0.05361 0.04762 0.0418 0.0558 1.0000
9.250 0.7678 0.05748 0.05172 0.0429 0.0578 1.0000
9.500 0.7037 0.06491 0.05981 0.0431 0.0622 1.0000
9.750 0.6692 0.07082 0.06580 0.0404 0.0636 1.0000
10.000 0.6428 0.07885 0.07383 0.0345 0.0658 1.0000
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Polar data table (+)
Polar graphs
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