R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: R140 12.04% (smoothed) (r140sm-il) Reynolds number: 100,000 Max Cl/Cd: 41.39 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r140sm-il-100000-n5.txt Download as CSV file: xf-r140sm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: R140 12.04% (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5719 0.09412 0.08915 -0.0337 1.0000 0.0178
-11.000 -0.5833 0.08668 0.08171 -0.0382 1.0000 0.0175
-10.750 -0.5983 0.08005 0.07506 -0.0423 1.0000 0.0174
-10.500 -0.6136 0.07472 0.06967 -0.0453 1.0000 0.0172
-10.250 -0.6315 0.06990 0.06477 -0.0471 1.0000 0.0170
-10.000 -0.6493 0.06587 0.06063 -0.0475 1.0000 0.0169
-9.750 -0.6673 0.06236 0.05700 -0.0464 1.0000 0.0169
-9.500 -0.6849 0.05934 0.05384 -0.0437 1.0000 0.0169
-9.250 -0.7012 0.05662 0.05097 -0.0399 1.0000 0.0167
-9.000 -0.7126 0.05370 0.04785 -0.0365 1.0000 0.0167
-8.750 -0.7211 0.05072 0.04462 -0.0328 1.0000 0.0167
-8.500 -0.7263 0.04781 0.04145 -0.0292 1.0000 0.0167
-8.250 -0.7289 0.04495 0.03826 -0.0254 1.0000 0.0169
-8.000 -0.7280 0.04240 0.03534 -0.0217 1.0000 0.0176
-7.750 -0.7235 0.04057 0.03309 -0.0181 1.0000 0.0184
-7.500 -0.7214 0.03731 0.02952 -0.0147 1.0000 0.0192
-7.250 -0.7139 0.03483 0.02679 -0.0119 1.0000 0.0200
-7.000 -0.7025 0.03266 0.02435 -0.0093 1.0000 0.0205
-6.750 -0.6887 0.03064 0.02200 -0.0069 1.0000 0.0211
-6.500 -0.6731 0.02883 0.01998 -0.0047 1.0000 0.0220
-6.250 -0.6565 0.02719 0.01817 -0.0027 1.0000 0.0230
-6.000 -0.6406 0.02583 0.01664 -0.0005 1.0000 0.0248
-5.750 -0.6257 0.02489 0.01554 0.0018 1.0000 0.0276
-5.500 -0.6134 0.02362 0.01422 0.0044 1.0000 0.0297
-5.250 -0.5838 0.02210 0.01265 0.0033 0.9935 0.0330
-5.000 -0.5534 0.02095 0.01134 0.0023 0.9859 0.0377
-4.750 -0.5243 0.01992 0.01019 0.0014 0.9774 0.0491
-4.500 -0.4963 0.01874 0.00905 0.0008 0.9691 0.0739
-4.250 -0.4727 0.01704 0.00805 0.0003 0.9603 0.1953
-4.000 -0.4652 0.01497 0.00783 0.0035 0.9488 0.5402
-3.750 -0.4387 0.01481 0.00780 0.0042 0.9401 0.6317
-3.500 -0.4056 0.01473 0.00770 0.0036 0.9332 0.6771
-3.250 -0.3761 0.01478 0.00772 0.0041 0.9244 0.7176
-3.000 -0.3402 0.01483 0.00768 0.0031 0.9183 0.7437
-2.750 -0.3092 0.01478 0.00749 0.0026 0.9084 0.7576
-2.500 -0.2755 0.01468 0.00723 0.0014 0.8999 0.7684
-2.250 -0.2416 0.01457 0.00695 0.0001 0.8916 0.7789
-2.000 -0.2090 0.01452 0.00680 -0.0008 0.8817 0.7880
-1.750 -0.1757 0.01445 0.00662 -0.0019 0.8727 0.7978
-1.500 -0.1433 0.01438 0.00644 -0.0028 0.8637 0.8083
-1.250 -0.1120 0.01435 0.00632 -0.0035 0.8533 0.8181
-1.000 -0.0787 0.01432 0.00623 -0.0046 0.8439 0.8273
-0.750 -0.0456 0.01428 0.00611 -0.0056 0.8354 0.8373
-0.500 -0.0158 0.01427 0.00606 -0.0060 0.8249 0.8479
-0.250 0.0192 0.01430 0.00605 -0.0075 0.8159 0.8559
0.000 0.0531 0.01429 0.00600 -0.0087 0.8079 0.8653
0.250 0.0836 0.01433 0.00602 -0.0093 0.7978 0.8756
0.500 0.1205 0.01439 0.00608 -0.0111 0.7894 0.8828
0.750 0.1537 0.01443 0.00611 -0.0123 0.7813 0.8922
1.000 0.1885 0.01451 0.00622 -0.0138 0.7724 0.9003
1.250 0.2244 0.01458 0.00632 -0.0155 0.7650 0.9080
1.500 0.2557 0.01467 0.00645 -0.0164 0.7563 0.9179
1.750 0.2952 0.01477 0.00661 -0.0189 0.7486 0.9233
2.000 0.3283 0.01487 0.00680 -0.0202 0.7410 0.9322
2.250 0.3674 0.01498 0.00702 -0.0227 0.7330 0.9377
2.500 0.4007 0.01509 0.00720 -0.0240 0.7259 0.9461
2.750 0.4384 0.01521 0.00748 -0.0264 0.7177 0.9521
3.000 0.4719 0.01532 0.00774 -0.0277 0.7109 0.9599
3.250 0.5084 0.01540 0.00801 -0.0297 0.6999 0.9661
3.500 0.5399 0.01539 0.00810 -0.0304 0.6810 0.9738
3.750 0.5734 0.01530 0.00809 -0.0313 0.6553 0.9804
4.000 0.6041 0.01520 0.00807 -0.0316 0.6164 0.9878
4.250 0.6292 0.01520 0.00777 -0.0307 0.5014 0.9964
4.500 0.6316 0.01684 0.00797 -0.0267 0.2390 1.0000
4.750 0.6282 0.01877 0.00891 -0.0222 0.0805 1.0000
5.000 0.6362 0.01973 0.00972 -0.0188 0.0476 1.0000
5.250 0.6457 0.02054 0.01056 -0.0156 0.0391 1.0000
5.500 0.6552 0.02132 0.01144 -0.0124 0.0347 1.0000
5.750 0.6624 0.02227 0.01244 -0.0089 0.0309 1.0000
6.000 0.6726 0.02304 0.01334 -0.0059 0.0272 1.0000
6.250 0.6815 0.02401 0.01439 -0.0027 0.0254 1.0000
6.500 0.6914 0.02514 0.01558 0.0003 0.0240 1.0000
6.750 0.7038 0.02650 0.01698 0.0029 0.0229 1.0000
7.000 0.7214 0.02862 0.01921 0.0045 0.0217 1.0000
7.250 0.7421 0.03056 0.02132 0.0058 0.0206 1.0000
7.500 0.7608 0.03204 0.02306 0.0074 0.0191 1.0000
7.750 0.7783 0.03395 0.02525 0.0092 0.0177 1.0000
8.000 0.7937 0.03631 0.02793 0.0112 0.0173 1.0000
8.250 0.8053 0.03886 0.03084 0.0137 0.0171 1.0000
8.500 0.8129 0.04155 0.03390 0.0166 0.0169 1.0000
8.750 0.8168 0.04433 0.03702 0.0198 0.0168 1.0000
9.000 0.8166 0.04727 0.04031 0.0232 0.0168 1.0000
9.250 0.8127 0.05023 0.04358 0.0268 0.0168 1.0000
9.500 0.8059 0.05312 0.04674 0.0303 0.0170 1.0000
9.750 0.7941 0.05587 0.04971 0.0342 0.0171 1.0000
10.000 0.7782 0.05873 0.05277 0.0379 0.0171 1.0000
10.250 0.7636 0.06167 0.05588 0.0403 0.0173 1.0000
10.500 0.7441 0.06540 0.05978 0.0418 0.0173 1.0000
10.750 0.7265 0.06930 0.06384 0.0420 0.0175 1.0000
11.000 0.7088 0.07368 0.06835 0.0410 0.0177 1.0000
11.250 0.6894 0.07898 0.07375 0.0388 0.0178 1.0000
11.500 0.6704 0.08508 0.07994 0.0355 0.0180 1.0000
11.750 0.6530 0.09211 0.08702 0.0312 0.0182 1.0000
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Polar data table (+)
Polar graphs
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