R140 (original) (r140-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: R140 (original) (r140-il) Reynolds number: 100,000 Max Cl/Cd: 36.12 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r140-il-100000-n5.txt Download as CSV file: xf-r140-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5525 0.09318 0.08839 -0.0330 1.0000 0.0124
-10.500 -0.5621 0.08560 0.08085 -0.0378 1.0000 0.0122
-10.250 -0.5744 0.07912 0.07435 -0.0420 1.0000 0.0120
-10.000 -0.5891 0.07364 0.06882 -0.0451 1.0000 0.0119
-9.750 -0.6086 0.06854 0.06364 -0.0469 1.0000 0.0118
-9.500 -0.6243 0.06487 0.05987 -0.0470 1.0000 0.0117
-9.250 -0.6434 0.06131 0.05621 -0.0453 1.0000 0.0117
-9.000 -0.6599 0.05852 0.05330 -0.0422 1.0000 0.0116
-8.750 -0.6739 0.05577 0.05040 -0.0386 1.0000 0.0115
-8.500 -0.6849 0.05271 0.04714 -0.0350 1.0000 0.0114
-8.250 -0.6926 0.04970 0.04390 -0.0313 1.0000 0.0112
-8.000 -0.6976 0.04669 0.04063 -0.0275 1.0000 0.0111
-7.750 -0.6997 0.04376 0.03739 -0.0237 1.0000 0.0110
-7.500 -0.6994 0.04080 0.03411 -0.0199 1.0000 0.0109
-7.250 -0.6959 0.03807 0.03103 -0.0162 1.0000 0.0108
-7.000 -0.6895 0.03539 0.02799 -0.0127 1.0000 0.0107
-6.750 -0.6800 0.03285 0.02510 -0.0096 1.0000 0.0107
-6.500 -0.6674 0.03062 0.02243 -0.0069 1.0000 0.0107
-6.250 -0.6526 0.02852 0.02005 -0.0044 1.0000 0.0107
-6.000 -0.6376 0.02671 0.01801 -0.0019 1.0000 0.0109
-5.750 -0.6238 0.02526 0.01638 0.0006 1.0000 0.0110
-5.500 -0.6083 0.02391 0.01486 0.0027 0.9989 0.0113
-5.250 -0.5775 0.02237 0.01308 0.0017 0.9916 0.0118
-5.000 -0.5463 0.02116 0.01159 0.0006 0.9837 0.0127
-4.750 -0.5147 0.02022 0.01036 -0.0005 0.9753 0.0139
-4.500 -0.4842 0.01933 0.00933 -0.0013 0.9668 0.0183
-4.250 -0.4499 0.01859 0.00857 -0.0031 0.9603 0.0438
-4.000 -0.4218 0.01773 0.00783 -0.0037 0.9513 0.0955
-3.750 -0.3895 0.01686 0.00705 -0.0053 0.9449 0.1644
-3.500 -0.3691 0.01543 0.00642 -0.0049 0.9346 0.3558
-3.250 -0.3463 0.01474 0.00617 -0.0042 0.9236 0.4716
-3.000 -0.3209 0.01436 0.00613 -0.0035 0.9138 0.5746
-2.750 -0.2957 0.01411 0.00622 -0.0023 0.9056 0.6789
-2.500 -0.2646 0.01411 0.00640 -0.0022 0.8970 0.7218
-2.250 -0.2339 0.01415 0.00634 -0.0023 0.8881 0.7508
-2.000 -0.2007 0.01417 0.00629 -0.0031 0.8801 0.7707
-1.750 -0.1726 0.01420 0.00625 -0.0030 0.8684 0.7855
-1.500 -0.1449 0.01420 0.00618 -0.0028 0.8565 0.8011
-1.250 -0.1148 0.01418 0.00605 -0.0031 0.8456 0.8141
-1.000 -0.0814 0.01416 0.00598 -0.0041 0.8367 0.8260
-0.750 -0.0479 0.01414 0.00589 -0.0051 0.8284 0.8375
-0.500 -0.0128 0.01416 0.00586 -0.0064 0.8203 0.8473
-0.250 0.0229 0.01415 0.00578 -0.0080 0.8135 0.8564
0.000 0.0532 0.01419 0.00579 -0.0086 0.8039 0.8665
0.250 0.0865 0.01426 0.00586 -0.0098 0.7951 0.8756
0.500 0.1224 0.01434 0.00595 -0.0115 0.7866 0.8837
0.750 0.1535 0.01443 0.00607 -0.0123 0.7770 0.8934
1.000 0.1899 0.01451 0.00618 -0.0142 0.7690 0.9003
1.250 0.2239 0.01456 0.00625 -0.0155 0.7615 0.9082
1.500 0.2585 0.01464 0.00639 -0.0171 0.7533 0.9159
1.750 0.2948 0.01469 0.00655 -0.0188 0.7456 0.9231
2.000 0.3265 0.01478 0.00669 -0.0197 0.7356 0.9328
2.250 0.3660 0.01485 0.00686 -0.0222 0.7246 0.9380
2.500 0.3977 0.01491 0.00699 -0.0230 0.7113 0.9469
2.750 0.4352 0.01495 0.00720 -0.0250 0.6961 0.9526
3.000 0.4612 0.01481 0.00690 -0.0239 0.6420 0.9611
3.250 0.4945 0.01481 0.00696 -0.0249 0.6087 0.9677
3.500 0.5261 0.01488 0.00712 -0.0257 0.5846 0.9749
3.750 0.5504 0.01524 0.00700 -0.0249 0.4492 0.9832
4.000 0.5668 0.01717 0.00762 -0.0241 0.1892 0.9917
4.250 0.5880 0.01919 0.00868 -0.0245 0.0212 0.9997
4.500 0.6017 0.01973 0.00933 -0.0220 0.0152 1.0000
4.750 0.6125 0.02041 0.01021 -0.0190 0.0122 1.0000
5.000 0.6238 0.02104 0.01096 -0.0162 0.0106 1.0000
5.250 0.6345 0.02171 0.01179 -0.0132 0.0098 1.0000
5.500 0.6437 0.02252 0.01277 -0.0099 0.0092 1.0000
5.750 0.6529 0.02340 0.01378 -0.0067 0.0091 1.0000
6.000 0.6614 0.02446 0.01499 -0.0033 0.0089 1.0000
6.250 0.6717 0.02562 0.01627 -0.0003 0.0088 1.0000
6.500 0.6845 0.02696 0.01773 0.0023 0.0088 1.0000
6.750 0.7006 0.02864 0.01956 0.0045 0.0087 1.0000
7.000 0.7190 0.03051 0.02163 0.0062 0.0088 1.0000
7.250 0.7373 0.03261 0.02398 0.0080 0.0089 1.0000
7.500 0.7533 0.03505 0.02673 0.0100 0.0089 1.0000
7.750 0.7657 0.03748 0.02949 0.0125 0.0090 1.0000
8.000 0.7742 0.04012 0.03248 0.0153 0.0092 1.0000
8.250 0.7786 0.04299 0.03570 0.0186 0.0093 1.0000
8.500 0.7797 0.04581 0.03884 0.0220 0.0095 1.0000
8.750 0.7781 0.04852 0.04196 0.0254 0.0096 1.0000
9.000 0.7723 0.05138 0.04509 0.0290 0.0097 1.0000
9.250 0.7628 0.05407 0.04800 0.0327 0.0099 1.0000
9.500 0.7495 0.05666 0.05077 0.0364 0.0099 1.0000
9.750 0.7354 0.05948 0.05376 0.0392 0.0100 1.0000
10.000 0.7196 0.06274 0.05719 0.0410 0.0101 1.0000
10.250 0.7047 0.06622 0.06080 0.0416 0.0101 1.0000
10.500 0.6859 0.07066 0.06539 0.0410 0.0102 1.0000
10.750 0.6696 0.07533 0.07016 0.0394 0.0102 1.0000
11.000 0.6533 0.08069 0.07562 0.0368 0.0104 1.0000
11.250 0.6363 0.08725 0.08214 0.0329 0.0104 1.0000
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Polar data table (+)
Polar graphs
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