R140 (original) (r140-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: R140 (original) (r140-il) Reynolds number: 500,000 Max Cl/Cd: 47.06 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r140-il-500000.txt Download as CSV file: xf-r140-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: R140 (original)
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5470 0.08546 0.08321 -0.0401 1.0000 0.0189
-10.250 -0.5608 0.07927 0.07696 -0.0444 1.0000 0.0189
-10.000 -0.5769 0.07413 0.07175 -0.0473 1.0000 0.0189
-9.750 -0.5932 0.07003 0.06757 -0.0487 1.0000 0.0189
-9.500 -0.6104 0.06662 0.06407 -0.0483 1.0000 0.0189
-9.250 -0.6279 0.06384 0.06119 -0.0463 1.0000 0.0189
-9.000 -0.6471 0.06160 0.05886 -0.0421 1.0000 0.0189
-8.750 -0.6614 0.05909 0.05623 -0.0382 1.0000 0.0189
-8.500 -0.6714 0.05664 0.05365 -0.0345 1.0000 0.0190
-8.250 -0.6815 0.05407 0.05093 -0.0304 1.0000 0.0190
-8.000 -0.6907 0.05172 0.04843 -0.0258 1.0000 0.0190
-6.500 -0.6334 0.02275 0.01731 -0.0146 0.9830 0.0107
-6.250 -0.6041 0.01929 0.01357 -0.0149 0.9805 0.0088
-6.000 -0.5776 0.01648 0.01047 -0.0144 0.9760 0.0075
-5.750 -0.5485 0.01473 0.00851 -0.0147 0.9720 0.0067
-5.500 -0.5156 0.01357 0.00719 -0.0160 0.9690 0.0064
-5.250 -0.4856 0.01269 0.00618 -0.0166 0.9633 0.0064
-5.000 -0.4520 0.01202 0.00533 -0.0180 0.9584 0.0065
-4.750 -0.4169 0.01147 0.00462 -0.0196 0.9532 0.0072
-4.500 -0.3868 0.01106 0.00413 -0.0202 0.9447 0.0089
-4.250 -0.3621 0.01052 0.00373 -0.0197 0.9335 0.0382
-4.000 -0.3353 0.01031 0.00348 -0.0196 0.9221 0.0460
-3.750 -0.3082 0.01010 0.00322 -0.0195 0.9109 0.0522
-3.500 -0.2820 0.00982 0.00295 -0.0193 0.8998 0.0666
-3.250 -0.2574 0.00954 0.00270 -0.0187 0.8871 0.1012
-3.000 -0.2378 0.00907 0.00246 -0.0173 0.8702 0.1737
-2.750 -0.2260 0.00804 0.00206 -0.0146 0.8499 0.3473
-2.500 -0.2128 0.00723 0.00180 -0.0119 0.8327 0.5002
-2.250 -0.1984 0.00688 0.00184 -0.0090 0.8182 0.6241
-2.000 -0.1735 0.00691 0.00179 -0.0084 0.8043 0.6430
-1.750 -0.1485 0.00690 0.00172 -0.0078 0.7895 0.6549
-1.500 -0.1234 0.00685 0.00165 -0.0073 0.7738 0.6667
-1.250 -0.0986 0.00680 0.00157 -0.0067 0.7604 0.6805
-1.000 -0.0731 0.00677 0.00150 -0.0062 0.7492 0.6914
-0.750 -0.0478 0.00674 0.00145 -0.0057 0.7390 0.7033
-0.500 -0.0229 0.00672 0.00145 -0.0051 0.7292 0.7172
-0.250 0.0024 0.00671 0.00147 -0.0046 0.7192 0.7316
0.000 0.0278 0.00672 0.00149 -0.0042 0.7091 0.7474
0.250 0.0528 0.00673 0.00152 -0.0036 0.6988 0.7649
0.750 0.1022 0.00676 0.00161 -0.0022 0.6802 0.8069
1.000 0.1278 0.00677 0.00167 -0.0018 0.6730 0.8237
1.250 0.1536 0.00680 0.00172 -0.0013 0.6638 0.8384
1.500 0.1792 0.00682 0.00177 -0.0009 0.6533 0.8526
1.750 0.2054 0.00684 0.00185 -0.0005 0.6452 0.8670
2.000 0.2326 0.00686 0.00192 -0.0004 0.6370 0.8799
2.250 0.2607 0.00688 0.00201 -0.0005 0.6287 0.8918
2.500 0.2892 0.00694 0.00210 -0.0006 0.6210 0.9032
2.750 0.3175 0.00700 0.00223 -0.0008 0.6117 0.9141
3.000 0.3407 0.00724 0.00222 0.0002 0.5443 0.9249
3.250 0.3605 0.00793 0.00232 0.0016 0.4028 0.9363
3.500 0.3793 0.00933 0.00289 0.0024 0.2048 0.9464
3.750 0.4055 0.01020 0.00338 0.0022 0.0941 0.9557
4.000 0.4403 0.01095 0.00386 0.0001 0.0258 0.9597
4.250 0.4747 0.01142 0.00432 -0.0015 0.0099 0.9649
4.500 0.5084 0.01179 0.00477 -0.0029 0.0087 0.9696
4.750 0.5444 0.01223 0.00532 -0.0048 0.0085 0.9724
5.000 0.5771 0.01280 0.00603 -0.0060 0.0085 0.9764
5.250 0.6051 0.01344 0.00677 -0.0063 0.0087 0.9819
5.500 0.6375 0.01427 0.00772 -0.0076 0.0090 0.9848
5.750 0.6668 0.01538 0.00896 -0.0083 0.0096 0.9889
6.000 0.6926 0.01693 0.01067 -0.0081 0.0103 0.9933
6.250 0.7220 0.01858 0.01251 -0.0087 0.0105 0.9958
6.500 0.7548 0.01937 0.01334 -0.0104 0.0090 0.9984
6.750 0.7851 0.02220 0.01645 -0.0105 0.0099 0.9998
13.500 0.4662 0.13111 0.12893 0.0157 0.0142 1.0000
13.750 0.4626 0.13424 0.13206 0.0140 0.0142 1.0000
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Polar data table (+)
Polar graphs
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