R140 (original) (r140-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: R140 (original) (r140-il) Reynolds number: 500,000 Max Cl/Cd: 37.51 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r140-il-500000-n5.txt Download as CSV file: xf-r140-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5837 0.08187 0.07971 -0.0347 1.0000 0.0015
-10.500 -0.6023 0.07191 0.06970 -0.0424 1.0000 0.0015
-10.250 -0.6185 0.06594 0.06365 -0.0461 1.0000 0.0014
-10.000 -0.6387 0.06064 0.05825 -0.0480 1.0000 0.0014
-9.750 -0.6595 0.05621 0.05370 -0.0477 1.0000 0.0014
-9.500 -0.6813 0.05223 0.04959 -0.0452 1.0000 0.0014
-9.250 -0.6984 0.04946 0.04669 -0.0412 1.0000 0.0014
-9.000 -0.7154 0.04644 0.04354 -0.0362 1.0000 0.0014
-8.750 -0.7300 0.04239 0.03927 -0.0313 1.0000 0.0014
-8.500 -0.7354 0.03812 0.03473 -0.0277 0.9977 0.0014
-8.250 -0.7300 0.03335 0.02954 -0.0258 0.9850 0.0013
-8.000 -0.7163 0.02913 0.02484 -0.0248 0.9754 0.0014
-7.750 -0.6931 0.02605 0.02131 -0.0250 0.9689 0.0016
-7.500 -0.6648 0.02397 0.01890 -0.0261 0.9633 0.0017
-7.250 -0.6317 0.02288 0.01756 -0.0278 0.9581 0.0019
-7.000 -0.6098 0.01893 0.01316 -0.0277 0.9514 0.0024
-6.750 -0.5795 0.01742 0.01147 -0.0288 0.9455 0.0025
-6.500 -0.5564 0.01638 0.01032 -0.0284 0.9349 0.0029
-6.250 -0.5335 0.01548 0.00932 -0.0278 0.9217 0.0032
-6.000 -0.5071 0.01489 0.00865 -0.0280 0.9099 0.0043
-5.750 -0.4817 0.01435 0.00800 -0.0278 0.8995 0.0048
-5.500 -0.4612 0.01356 0.00702 -0.0265 0.8888 0.0049
-5.250 -0.4432 0.01278 0.00610 -0.0246 0.8760 0.0048
-5.000 -0.4242 0.01220 0.00538 -0.0229 0.8553 0.0047
-4.750 -0.4032 0.01176 0.00474 -0.0215 0.8321 0.0047
-4.500 -0.3811 0.01145 0.00422 -0.0203 0.8195 0.0046
-4.250 -0.3581 0.01122 0.00381 -0.0193 0.8085 0.0046
-4.000 -0.3347 0.01101 0.00347 -0.0185 0.7950 0.0046
-3.750 -0.3112 0.01080 0.00316 -0.0176 0.7723 0.0046
-3.500 -0.2881 0.01067 0.00287 -0.0167 0.7528 0.0046
-3.250 -0.2648 0.01057 0.00260 -0.0158 0.7361 0.0048
-2.750 -0.2149 0.01044 0.00228 -0.0148 0.7138 0.0075
-2.500 -0.1917 0.01020 0.00214 -0.0140 0.7029 0.0295
-2.250 -0.1691 0.00993 0.00197 -0.0132 0.6914 0.0654
-2.000 -0.1443 0.00985 0.00184 -0.0127 0.6806 0.0951
-1.750 -0.1193 0.00977 0.00168 -0.0122 0.6706 0.0990
-1.500 -0.0951 0.00961 0.00158 -0.0117 0.6630 0.1226
-1.250 -0.0716 0.00935 0.00148 -0.0111 0.6557 0.1807
-1.000 -0.0459 0.00927 0.00141 -0.0108 0.6488 0.1888
-0.750 -0.0211 0.00912 0.00133 -0.0104 0.6420 0.2152
-0.500 -0.0011 0.00858 0.00119 -0.0092 0.6356 0.3368
-0.250 0.0208 0.00822 0.00110 -0.0083 0.6278 0.4207
0.000 0.0458 0.00811 0.00108 -0.0079 0.6208 0.4463
0.250 0.0693 0.00795 0.00104 -0.0072 0.6120 0.4892
0.500 0.0911 0.00782 0.00103 -0.0061 0.5985 0.5370
0.750 0.1135 0.00781 0.00106 -0.0051 0.5752 0.5789
1.000 0.1370 0.00790 0.00107 -0.0044 0.5419 0.5935
1.250 0.1586 0.00816 0.00108 -0.0032 0.4795 0.5995
1.500 0.1797 0.00852 0.00117 -0.0021 0.4031 0.6068
1.750 0.1974 0.00917 0.00139 -0.0005 0.2845 0.6152
2.000 0.2126 0.01011 0.00172 0.0014 0.1210 0.6232
2.250 0.2302 0.01085 0.00197 0.0032 0.0075 0.6327
2.500 0.2574 0.01078 0.00205 0.0031 0.0040 0.6402
2.750 0.2828 0.01086 0.00222 0.0034 0.0040 0.6483
3.000 0.3078 0.01099 0.00240 0.0039 0.0036 0.6541
3.250 0.3325 0.01113 0.00261 0.0044 0.0034 0.6602
3.500 0.3567 0.01127 0.00284 0.0051 0.0033 0.6692
4.000 0.4033 0.01166 0.00349 0.0067 0.0033 0.6903
4.250 0.4251 0.01187 0.00392 0.0079 0.0033 0.7034
4.500 0.4428 0.01199 0.00437 0.0100 0.0033 0.7603
4.750 0.4621 0.01232 0.00491 0.0118 0.0034 0.7906
5.000 0.4808 0.01282 0.00556 0.0136 0.0034 0.8121
5.250 0.4978 0.01342 0.00633 0.0157 0.0035 0.8262
5.500 0.5128 0.01417 0.00726 0.0182 0.0037 0.8458
6.500 0.6129 0.01830 0.01209 0.0197 0.0059 0.9271
6.750 0.6498 0.02039 0.01445 0.0177 0.0062 0.9422
7.000 0.6861 0.02267 0.01697 0.0157 0.0062 0.9513
7.250 0.7212 0.02524 0.01984 0.0137 0.0061 0.9608
7.500 0.7513 0.02770 0.02260 0.0125 0.0058 0.9688
7.750 0.7752 0.03026 0.02545 0.0123 0.0056 0.9787
8.000 0.7936 0.03295 0.02843 0.0129 0.0054 0.9890
8.250 0.8084 0.03567 0.03142 0.0139 0.0052 0.9986
8.500 0.8136 0.03834 0.03432 0.0166 0.0051 1.0000
8.750 0.8119 0.04071 0.03689 0.0205 0.0050 1.0000
9.000 0.8068 0.04336 0.03975 0.0246 0.0050 1.0000
9.250 0.7989 0.04600 0.04257 0.0288 0.0050 1.0000
9.500 0.7855 0.04804 0.04475 0.0336 0.0049 1.0000
9.750 0.7713 0.05040 0.04724 0.0376 0.0048 1.0000
10.000 0.7557 0.05341 0.05040 0.0405 0.0048 1.0000
10.250 0.7417 0.05642 0.05355 0.0421 0.0048 1.0000
10.500 0.7251 0.06033 0.05760 0.0426 0.0048 1.0000
10.750 0.7071 0.06507 0.06247 0.0420 0.0049 1.0000
11.000 0.6908 0.06987 0.06738 0.0401 0.0049 1.0000
11.250 0.6707 0.07642 0.07404 0.0367 0.0049 1.0000
11.500 0.6505 0.08494 0.08266 0.0314 0.0050 1.0000
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Polar data table (+)
Polar graphs
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