R140 (original) (r140-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: R140 (original) (r140-il) Reynolds number: 50,000 Max Cl/Cd: 28.7 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r140-il-50000-n5.txt Download as CSV file: xf-r140-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5503 0.09802 0.09125 -0.0328 1.0000 0.0222
-10.500 -0.5583 0.09165 0.08492 -0.0365 1.0000 0.0219
-10.250 -0.5692 0.08579 0.07909 -0.0400 1.0000 0.0216
-10.000 -0.5817 0.08069 0.07398 -0.0428 1.0000 0.0212
-9.750 -0.6000 0.07561 0.06886 -0.0448 1.0000 0.0211
-9.500 -0.6151 0.07178 0.06496 -0.0453 1.0000 0.0209
-9.250 -0.6334 0.06816 0.06125 -0.0442 1.0000 0.0208
-9.000 -0.6495 0.06519 0.05818 -0.0418 1.0000 0.0206
-8.750 -0.6625 0.06223 0.05507 -0.0390 1.0000 0.0205
-8.500 -0.6724 0.05909 0.05174 -0.0362 1.0000 0.0204
-8.250 -0.6791 0.05598 0.04838 -0.0331 1.0000 0.0203
-8.000 -0.6829 0.05289 0.04502 -0.0300 1.0000 0.0203
-7.750 -0.6832 0.04991 0.04172 -0.0268 1.0000 0.0201
-7.500 -0.6807 0.04693 0.03839 -0.0237 1.0000 0.0205
-7.250 -0.6741 0.04411 0.03520 -0.0207 1.0000 0.0209
-7.000 -0.6633 0.04135 0.03189 -0.0181 1.0000 0.0214
-6.750 -0.6481 0.03873 0.02884 -0.0159 1.0000 0.0230
-6.500 -0.6278 0.03631 0.02601 -0.0142 1.0000 0.0242
-6.250 -0.6085 0.03424 0.02380 -0.0127 1.0000 0.0265
-6.000 -0.5874 0.03252 0.02192 -0.0112 1.0000 0.0295
-5.750 -0.5659 0.03091 0.02008 -0.0095 1.0000 0.0321
-5.500 -0.5503 0.02953 0.01842 -0.0068 1.0000 0.0359
-5.250 -0.5417 0.02818 0.01705 -0.0038 1.0000 0.0450
-5.000 -0.5357 0.02676 0.01550 -0.0001 1.0000 0.0558
-4.750 -0.5302 0.02542 0.01425 0.0034 1.0000 0.0724
-4.500 -0.5229 0.02426 0.01319 0.0065 1.0000 0.1084
-4.250 -0.5181 0.02269 0.01206 0.0095 1.0000 0.1933
-4.000 -0.5230 0.02073 0.01158 0.0145 1.0000 0.4349
-3.750 -0.5172 0.02041 0.01172 0.0193 1.0000 0.5785
-3.500 -0.5111 0.02042 0.01187 0.0241 1.0000 0.6658
-3.250 -0.4860 0.02133 0.01288 0.0278 0.9960 0.7605
-3.000 -0.4477 0.02230 0.01360 0.0281 0.9885 0.8128
-2.750 -0.4017 0.02290 0.01385 0.0256 0.9820 0.8389
-2.500 -0.3550 0.02317 0.01378 0.0219 0.9747 0.8539
-2.250 -0.3099 0.02331 0.01360 0.0182 0.9661 0.8668
-2.000 -0.2617 0.02339 0.01331 0.0136 0.9584 0.8772
-1.750 -0.2122 0.02344 0.01312 0.0088 0.9500 0.8847
-1.500 -0.1675 0.02343 0.01290 0.0047 0.9411 0.8938
-1.250 -0.1160 0.02344 0.01267 -0.0007 0.9342 0.9008
-1.000 -0.0720 0.02342 0.01256 -0.0046 0.9251 0.9093
-0.750 -0.0257 0.02340 0.01243 -0.0090 0.9180 0.9187
-0.500 0.0237 0.02337 0.01235 -0.0140 0.9106 0.9262
-0.250 0.0695 0.02332 0.01224 -0.0184 0.9033 0.9352
0.000 0.1155 0.02323 0.01214 -0.0227 0.8958 0.9435
0.250 0.1591 0.02315 0.01209 -0.0267 0.8872 0.9514
0.500 0.2030 0.02304 0.01203 -0.0306 0.8800 0.9599
0.750 0.2445 0.02297 0.01203 -0.0343 0.8698 0.9681
1.000 0.2859 0.02290 0.01206 -0.0379 0.8605 0.9773
1.250 0.3312 0.02277 0.01215 -0.0422 0.8531 0.9861
1.500 0.3734 0.02268 0.01222 -0.0460 0.8435 0.9955
1.750 0.4071 0.02261 0.01229 -0.0480 0.8341 1.0000
2.000 0.4320 0.02257 0.01238 -0.0480 0.8250 1.0000
2.250 0.4528 0.02265 0.01259 -0.0473 0.8150 1.0000
2.500 0.4708 0.02287 0.01305 -0.0461 0.8046 1.0000
2.750 0.4878 0.02313 0.01348 -0.0448 0.7943 1.0000
3.000 0.5061 0.02339 0.01393 -0.0436 0.7847 1.0000
3.250 0.5250 0.02361 0.01437 -0.0422 0.7742 1.0000
3.500 0.5450 0.02366 0.01465 -0.0406 0.7609 1.0000
3.750 0.5656 0.02355 0.01478 -0.0386 0.7441 1.0000
4.000 0.5877 0.02295 0.01441 -0.0355 0.7158 1.0000
4.250 0.6060 0.02222 0.01381 -0.0313 0.6767 1.0000
4.500 0.6138 0.02169 0.01332 -0.0255 0.6201 1.0000
4.750 0.6136 0.02138 0.01290 -0.0185 0.5128 1.0000
5.000 0.5983 0.02319 0.01259 -0.0105 0.2087 1.0000
5.250 0.5903 0.02565 0.01405 -0.0059 0.0777 1.0000
5.500 0.5924 0.02729 0.01540 -0.0020 0.0413 1.0000
5.750 0.5985 0.02856 0.01670 0.0014 0.0339 1.0000
6.000 0.6048 0.02983 0.01816 0.0049 0.0298 1.0000
6.250 0.6118 0.03108 0.01957 0.0083 0.0274 1.0000
6.500 0.6201 0.03239 0.02103 0.0113 0.0257 1.0000
6.750 0.6318 0.03400 0.02277 0.0140 0.0238 1.0000
7.000 0.6574 0.03618 0.02509 0.0149 0.0226 1.0000
7.250 0.6903 0.03843 0.02764 0.0150 0.0221 1.0000
7.500 0.7187 0.04119 0.03077 0.0156 0.0216 1.0000
7.750 0.7381 0.04391 0.03384 0.0170 0.0214 1.0000
8.000 0.7516 0.04672 0.03705 0.0191 0.0210 1.0000
8.250 0.7596 0.04966 0.04039 0.0217 0.0206 1.0000
8.500 0.7632 0.05256 0.04364 0.0244 0.0202 1.0000
8.750 0.7634 0.05547 0.04686 0.0272 0.0203 1.0000
9.000 0.7589 0.05837 0.05007 0.0302 0.0198 1.0000
9.250 0.7514 0.06136 0.05329 0.0330 0.0201 1.0000
9.500 0.7390 0.06413 0.05624 0.0362 0.0200 1.0000
9.750 0.7254 0.06710 0.05938 0.0385 0.0201 1.0000
10.000 0.7095 0.07046 0.06290 0.0399 0.0200 1.0000
10.250 0.6952 0.07411 0.06667 0.0402 0.0204 1.0000
10.500 0.6766 0.07859 0.07127 0.0393 0.0203 1.0000
10.750 0.6621 0.08323 0.07598 0.0377 0.0208 1.0000
11.000 0.6482 0.08832 0.08114 0.0353 0.0212 1.0000
11.250 0.6340 0.09419 0.08704 0.0322 0.0214 1.0000
11.500 0.6258 0.09952 0.09236 0.0296 0.0220 1.0000
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Polar data table (+)
Polar graphs
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