E176 (8.83%) (e176-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E176 (8.83%) (e176-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.94 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e176-il-1000000.txt Download as CSV file: xf-e176-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E176 (8.83%)
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
------ -------- --------- --------- -------- -------- --------
0.250 0.3436 0.00484 0.00105 -0.0606 0.6051 0.9782
0.500 0.3820 0.00489 0.00102 -0.0630 0.5998 1.0000
0.750 0.4095 0.00492 0.00102 -0.0628 0.5944 1.0000
1.000 0.4368 0.00498 0.00103 -0.0627 0.5887 1.0000
1.250 0.4643 0.00503 0.00104 -0.0625 0.5825 1.0000
1.500 0.4918 0.00508 0.00106 -0.0624 0.5756 1.0000
1.750 0.5193 0.00514 0.00109 -0.0624 0.5691 1.0000
2.000 0.5470 0.00520 0.00112 -0.0623 0.5615 1.0000
2.250 0.5746 0.00527 0.00115 -0.0622 0.5541 1.0000
2.500 0.6022 0.00534 0.00119 -0.0621 0.5464 1.0000
2.750 0.6299 0.00540 0.00125 -0.0621 0.5390 1.0000
3.000 0.6574 0.00549 0.00131 -0.0620 0.5309 1.0000
3.250 0.6852 0.00556 0.00138 -0.0620 0.5223 1.0000
3.500 0.7127 0.00566 0.00145 -0.0620 0.5131 1.0000
3.750 0.7401 0.00576 0.00153 -0.0619 0.5025 1.0000
4.000 0.7677 0.00586 0.00163 -0.0619 0.4916 1.0000
4.250 0.7950 0.00598 0.00173 -0.0618 0.4783 1.0000
4.500 0.8216 0.00619 0.00184 -0.0616 0.4496 1.0000
5.000 0.8721 0.00696 0.00224 -0.0611 0.3564 1.0000
5.250 0.8956 0.00762 0.00260 -0.0606 0.2909 1.0000
5.500 0.9177 0.00844 0.00305 -0.0600 0.2159 1.0000
5.750 0.9396 0.00927 0.00354 -0.0594 0.1485 1.0000
6.000 0.9610 0.01014 0.00409 -0.0588 0.0873 1.0000
6.250 0.9806 0.01122 0.00479 -0.0578 0.0254 1.0000
6.500 1.0035 0.01187 0.00535 -0.0572 0.0100 1.0000
6.750 1.0279 0.01228 0.00579 -0.0567 0.0088 1.0000
7.000 1.0512 0.01285 0.00644 -0.0560 0.0076 1.0000
7.250 1.0746 0.01336 0.00702 -0.0554 0.0073 1.0000
7.500 1.0975 0.01390 0.00763 -0.0547 0.0070 1.0000
7.750 1.1193 0.01454 0.00834 -0.0539 0.0067 1.0000
8.000 1.1403 0.01525 0.00912 -0.0530 0.0065 1.0000
8.250 1.1603 0.01601 0.00996 -0.0519 0.0063 1.0000
8.500 1.1798 0.01677 0.01080 -0.0509 0.0061 1.0000
8.750 1.1986 0.01755 0.01164 -0.0497 0.0059 1.0000
9.000 1.2154 0.01847 0.01263 -0.0483 0.0058 1.0000
9.250 1.2306 0.01949 0.01373 -0.0467 0.0057 1.0000
9.500 1.2448 0.02052 0.01484 -0.0450 0.0056 1.0000
9.750 1.2571 0.02164 0.01605 -0.0431 0.0056 1.0000
10.000 1.2660 0.02282 0.01732 -0.0406 0.0055 1.0000
10.250 1.2731 0.02398 0.01857 -0.0379 0.0055 1.0000
10.500 1.2793 0.02536 0.02005 -0.0354 0.0055 1.0000
10.750 1.2839 0.02701 0.02176 -0.0332 0.0052 1.0000
11.000 1.2918 0.02847 0.02333 -0.0313 0.0052 1.0000
11.250 1.2959 0.03080 0.02578 -0.0294 0.0051 1.0000
11.500 1.2996 0.03378 0.02893 -0.0275 0.0050 1.0000
11.750 1.3052 0.03555 0.03083 -0.0261 0.0050 1.0000
12.000 1.3089 0.03763 0.03305 -0.0248 0.0050 1.0000
12.250 1.3017 0.04214 0.03783 -0.0230 0.0049 1.0000
12.500 1.2995 0.04487 0.04073 -0.0220 0.0050 1.0000
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Polar data table (+)
Polar graphs
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