EPPLER 330 AIRFOIL (e330-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 330 AIRFOIL (e330-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.76 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e330-il-1000000-n5.txt Download as CSV file: xf-e330-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 330 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5342 0.08691 0.08486 0.0006 0.7850 0.0051
-9.000 -0.5457 0.08121 0.07907 -0.0041 0.7559 0.0051
-8.750 -0.5591 0.07642 0.07418 -0.0066 0.7333 0.0051
-6.250 -0.5991 0.03267 0.02849 0.0165 0.6009 0.0029
-6.000 -0.5976 0.02540 0.02062 0.0220 0.5942 0.0028
-5.750 -0.5867 0.02006 0.01460 0.0260 0.5844 0.0026
-5.500 -0.5661 0.01736 0.01142 0.0279 0.5734 0.0026
-5.250 -0.5421 0.01591 0.00970 0.0289 0.5617 0.0026
-5.000 -0.5175 0.01468 0.00823 0.0297 0.5505 0.0026
-4.750 -0.4926 0.01382 0.00721 0.0305 0.5391 0.0026
-4.500 -0.4678 0.01312 0.00636 0.0312 0.5279 0.0026
-4.250 -0.4433 0.01247 0.00557 0.0321 0.5176 0.0027
-4.000 -0.4184 0.01201 0.00501 0.0328 0.5075 0.0027
-3.750 -0.3936 0.01158 0.00449 0.0335 0.4977 0.0028
-3.500 -0.3687 0.01121 0.00403 0.0342 0.4876 0.0029
-3.250 -0.3434 0.01090 0.00365 0.0348 0.4783 0.0030
-3.000 -0.3178 0.01066 0.00336 0.0354 0.4693 0.0031
-2.750 -0.2931 0.01031 0.00293 0.0361 0.4607 0.0037
-2.500 -0.2672 0.01013 0.00271 0.0366 0.4522 0.0041
-2.250 -0.2412 0.00998 0.00251 0.0371 0.4441 0.0047
-2.000 -0.2150 0.00983 0.00231 0.0375 0.4357 0.0050
-1.750 -0.1889 0.00969 0.00214 0.0379 0.4279 0.0063
-1.500 -0.1626 0.00956 0.00199 0.0383 0.4204 0.0089
-1.250 -0.1370 0.00937 0.00185 0.0388 0.4139 0.0247
-1.000 -0.1117 0.00917 0.00174 0.0393 0.4060 0.0553
-0.750 -0.0879 0.00885 0.00165 0.0401 0.3997 0.1302
-0.500 -0.0622 0.00869 0.00157 0.0405 0.3935 0.1692
-0.250 -0.0407 0.00823 0.00145 0.0417 0.3873 0.2860
0.000 -0.0600 0.00587 0.00115 0.0513 0.3846 0.8314
0.250 -0.0350 0.00595 0.00133 0.0523 0.3782 0.8897
0.500 -0.0088 0.00605 0.00138 0.0529 0.3723 0.9026
0.750 0.0190 0.00614 0.00145 0.0531 0.3671 0.9097
1.000 0.0454 0.00625 0.00150 0.0535 0.3606 0.9172
1.250 0.0740 0.00635 0.00156 0.0535 0.3553 0.9205
1.500 0.1020 0.00643 0.00160 0.0535 0.3500 0.9235
2.000 0.1560 0.00655 0.00163 0.0539 0.3392 0.9281
2.250 0.1829 0.00661 0.00165 0.0541 0.3340 0.9297
2.500 0.2116 0.00668 0.00168 0.0539 0.3290 0.9308
2.750 0.2401 0.00674 0.00173 0.0538 0.3236 0.9320
3.000 0.2682 0.00683 0.00178 0.0537 0.3183 0.9332
3.250 0.2963 0.00690 0.00183 0.0536 0.3133 0.9343
3.500 0.3243 0.00697 0.00189 0.0535 0.3081 0.9354
3.750 0.3519 0.00708 0.00196 0.0535 0.3024 0.9372
4.000 0.3795 0.00715 0.00203 0.0535 0.2975 0.9386
4.250 0.4065 0.00724 0.00209 0.0536 0.2918 0.9402
4.500 0.4332 0.00733 0.00216 0.0537 0.2861 0.9417
4.750 0.4595 0.00741 0.00225 0.0540 0.2806 0.9434
5.000 0.4871 0.00753 0.00234 0.0539 0.2741 0.9448
5.250 0.5155 0.00764 0.00247 0.0537 0.2684 0.9467
5.500 0.5430 0.00776 0.00257 0.0536 0.2616 0.9475
5.750 0.5705 0.00787 0.00269 0.0535 0.2549 0.9483
6.000 0.5977 0.00801 0.00280 0.0535 0.2474 0.9491
6.250 0.6248 0.00814 0.00293 0.0534 0.2394 0.9500
6.500 0.6514 0.00830 0.00308 0.0535 0.2312 0.9510
6.750 0.6782 0.00844 0.00322 0.0535 0.2235 0.9520
7.000 0.7043 0.00861 0.00338 0.0536 0.2143 0.9531
7.250 0.7299 0.00882 0.00355 0.0538 0.2040 0.9543
7.500 0.7553 0.00901 0.00374 0.0540 0.1934 0.9555
7.750 0.7797 0.00925 0.00395 0.0543 0.1808 0.9570
8.000 0.8044 0.00949 0.00417 0.0546 0.1699 0.9583
8.250 0.8300 0.00982 0.00445 0.0547 0.1546 0.9593
8.500 0.8551 0.01017 0.00477 0.0547 0.1397 0.9603
8.750 0.8796 0.01056 0.00511 0.0549 0.1252 0.9615
9.000 0.9041 0.01093 0.00545 0.0550 0.1131 0.9627
9.250 0.9274 0.01138 0.00585 0.0553 0.0983 0.9642
9.500 0.9499 0.01187 0.00629 0.0557 0.0831 0.9659
9.750 0.9717 0.01236 0.00675 0.0563 0.0707 0.9679
10.000 0.9927 0.01281 0.00718 0.0570 0.0619 0.9701
10.250 1.0128 0.01328 0.00764 0.0578 0.0537 0.9723
10.500 1.0374 0.01380 0.00816 0.0576 0.0455 0.9735
10.750 1.0618 0.01435 0.00871 0.0574 0.0390 0.9748
11.000 1.0837 0.01508 0.00940 0.0573 0.0296 0.9766
11.250 1.1050 0.01582 0.01013 0.0574 0.0225 0.9787
11.500 1.1240 0.01665 0.01094 0.0577 0.0157 0.9812
11.750 1.1425 0.01724 0.01158 0.0584 0.0141 0.9842
12.000 1.1638 0.01817 0.01251 0.0578 0.0099 0.9855
12.250 1.1877 0.01893 0.01334 0.0570 0.0092 0.9866
12.500 1.2062 0.01997 0.01441 0.0566 0.0069 0.9885
12.750 1.2232 0.02102 0.01553 0.0562 0.0059 0.9910
13.000 1.2375 0.02229 0.01687 0.0556 0.0052 0.9941
13.250 1.2518 0.02395 0.01862 0.0540 0.0042 0.9969
13.500 1.2654 0.02605 0.02081 0.0517 0.0035 0.9992
13.750 1.2687 0.02830 0.02314 0.0510 0.0030 1.0000
14.000 1.2627 0.03062 0.02555 0.0520 0.0028 1.0000
14.250 1.2571 0.03333 0.02833 0.0523 0.0025 1.0000
14.500 1.2506 0.03641 0.03150 0.0520 0.0021 1.0000
14.750 1.2429 0.03980 0.03497 0.0515 0.0017 1.0000
15.250 1.2282 0.04681 0.04216 0.0500 0.0016 1.0000
15.500 1.2213 0.05034 0.04577 0.0491 0.0016 1.0000
15.750 1.2127 0.05416 0.04968 0.0480 0.0015 1.0000
16.000 1.2021 0.05829 0.05390 0.0468 0.0015 1.0000
16.250 1.1926 0.06245 0.05816 0.0454 0.0014 1.0000
16.500 1.1775 0.06752 0.06331 0.0435 0.0011 1.0000
16.750 1.1717 0.07143 0.06731 0.0421 0.0013 1.0000
17.000 1.1577 0.07660 0.07256 0.0401 0.0010 1.0000
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Polar data table (+)
Polar graphs
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