R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: R140 12.04% (smoothed) (r140sm-il) Reynolds number: 200,000 Max Cl/Cd: 53.48 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r140sm-il-200000.txt Download as CSV file: xf-r140sm-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4422 0.10589 0.10255 -0.0286 1.0000 0.0505
-11.250 -0.4515 0.10037 0.09705 -0.0316 1.0000 0.0520
-11.000 -0.5535 0.10125 0.09772 -0.0295 1.0000 0.0465
-10.750 -0.5580 0.09616 0.09267 -0.0320 1.0000 0.0475
-10.500 -0.5665 0.09000 0.08655 -0.0359 1.0000 0.0486
-10.250 -0.5815 0.08267 0.07924 -0.0417 1.0000 0.0485
-8.000 -0.7344 0.05164 0.04707 -0.0248 1.0000 0.0563
-7.750 -0.7299 0.04891 0.04433 -0.0223 1.0000 0.0579
-7.500 -0.7284 0.04670 0.04203 -0.0189 1.0000 0.0600
-7.250 -0.7294 0.04485 0.03996 -0.0147 1.0000 0.0634
-7.000 -0.7404 0.04285 0.03755 -0.0089 1.0000 0.0690
-6.750 -0.7333 0.04014 0.03483 -0.0063 1.0000 0.0710
-6.500 -0.7160 0.03111 0.02448 0.0013 1.0000 0.0288
-6.250 -0.7056 0.02840 0.02147 0.0044 1.0000 0.0278
-6.000 -0.6931 0.02694 0.01973 0.0073 1.0000 0.0290
-5.750 -0.6794 0.02571 0.01826 0.0099 1.0000 0.0296
-5.500 -0.6475 0.02343 0.01566 0.0093 0.9975 0.0299
-5.250 -0.6090 0.02133 0.01338 0.0073 0.9942 0.0306
-5.000 -0.5772 0.01892 0.01095 0.0062 0.9895 0.0329
-4.750 -0.5392 0.01795 0.00996 0.0036 0.9841 0.0393
-4.500 -0.5084 0.01656 0.00853 0.0026 0.9764 0.0452
-4.250 -0.4740 0.01525 0.00725 0.0008 0.9702 0.0722
-4.000 -0.4697 0.01204 0.00608 0.0036 0.9582 0.4594
-3.750 -0.4446 0.01155 0.00608 0.0043 0.9492 0.6071
-3.500 -0.4104 0.01139 0.00607 0.0035 0.9433 0.6768
-3.250 -0.3766 0.01130 0.00602 0.0028 0.9361 0.7119
-3.000 -0.3383 0.01122 0.00589 0.0010 0.9304 0.7365
-2.750 -0.3043 0.01123 0.00589 0.0002 0.9232 0.7623
-2.500 -0.2687 0.01123 0.00586 -0.0008 0.9162 0.7814
-2.250 -0.2359 0.01117 0.00572 -0.0016 0.9075 0.7946
-2.000 -0.2000 0.01106 0.00553 -0.0031 0.9004 0.8054
-1.750 -0.1721 0.01097 0.00537 -0.0030 0.8894 0.8161
-1.500 -0.1402 0.01091 0.00526 -0.0037 0.8798 0.8250
-1.250 -0.1073 0.01082 0.00510 -0.0045 0.8716 0.8342
-1.000 -0.0810 0.01078 0.00501 -0.0041 0.8601 0.8449
-0.750 -0.0517 0.01077 0.00497 -0.0042 0.8497 0.8545
-0.500 -0.0201 0.01076 0.00493 -0.0049 0.8406 0.8635
-0.250 0.0093 0.01076 0.00487 -0.0051 0.8311 0.8738
0.000 0.0388 0.01081 0.00491 -0.0053 0.8210 0.8839
0.250 0.0743 0.01089 0.00496 -0.0068 0.8125 0.8913
0.500 0.1056 0.01096 0.00500 -0.0074 0.8036 0.9011
0.750 0.1433 0.01110 0.00515 -0.0095 0.7948 0.9075
1.000 0.1785 0.01121 0.00522 -0.0110 0.7873 0.9157
1.250 0.2183 0.01137 0.00542 -0.0135 0.7782 0.9213
1.500 0.2540 0.01150 0.00556 -0.0152 0.7706 0.9292
1.750 0.2985 0.01166 0.00574 -0.0188 0.7626 0.9329
2.000 0.3320 0.01181 0.00593 -0.0202 0.7546 0.9418
2.250 0.3771 0.01194 0.00612 -0.0239 0.7475 0.9452
2.500 0.4151 0.01208 0.00634 -0.0263 0.7381 0.9522
2.750 0.4530 0.01211 0.00640 -0.0283 0.7238 0.9585
3.000 0.4911 0.01210 0.00643 -0.0303 0.7064 0.9650
3.250 0.5282 0.01211 0.00647 -0.0322 0.6901 0.9718
3.500 0.5641 0.01197 0.00635 -0.0337 0.6581 0.9790
3.750 0.5987 0.01180 0.00615 -0.0348 0.6107 0.9861
4.000 0.6316 0.01181 0.00595 -0.0358 0.5232 0.9937
4.250 0.6317 0.01491 0.00673 -0.0326 0.0823 1.0000
4.500 0.6387 0.01599 0.00761 -0.0290 0.0450 1.0000
4.750 0.6510 0.01650 0.00819 -0.0264 0.0376 1.0000
5.000 0.6576 0.01744 0.00918 -0.0227 0.0342 1.0000
5.250 0.6656 0.01829 0.01009 -0.0192 0.0326 1.0000
5.500 0.6746 0.01916 0.01103 -0.0158 0.0314 1.0000
5.750 0.6854 0.02010 0.01205 -0.0126 0.0301 1.0000
6.000 0.6983 0.02106 0.01306 -0.0099 0.0285 1.0000
6.250 0.7121 0.02205 0.01406 -0.0075 0.0261 1.0000
6.500 0.7308 0.02360 0.01569 -0.0057 0.0258 1.0000
6.750 0.7525 0.02555 0.01781 -0.0042 0.0257 1.0000
7.000 0.7762 0.02829 0.02093 -0.0025 0.0276 1.0000
7.250 0.7944 0.03199 0.02504 -0.0002 0.0310 1.0000
11.750 0.5529 0.09555 0.09220 0.0363 0.0568 1.0000
12.000 0.5303 0.10329 0.09995 0.0314 0.0568 1.0000
12.250 0.5187 0.10993 0.10658 0.0278 0.0568 1.0000
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Polar data table (+)
Polar graphs
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