DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: DU 86-137/25 AIRFOIL (du861372-il) Reynolds number: 500,000 Max Cl/Cd: 48.86 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-du861372-il-500000-n5.txt Download as CSV file: xf-du861372-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DU 86-137/25 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7030 0.08909 0.08462 -0.0372 0.2388 0.0108
-13.250 -0.7217 0.08321 0.07865 -0.0405 0.2387 0.0107
-13.000 -0.7441 0.07785 0.07317 -0.0430 0.2388 0.0107
-12.750 -0.7647 0.07342 0.06861 -0.0444 0.2389 0.0108
-12.500 -0.7795 0.06945 0.06454 -0.0448 0.2389 0.0107
-12.250 -0.7995 0.06602 0.06097 -0.0444 0.2389 0.0107
-12.000 -0.8254 0.06339 0.05815 -0.0426 0.2389 0.0108
-11.750 -0.8402 0.06083 0.05545 -0.0408 0.2388 0.0108
-11.500 -0.8622 0.05888 0.05332 -0.0374 0.2390 0.0108
-11.250 -0.8850 0.05749 0.05175 -0.0325 0.2388 0.0109
-11.000 -0.8979 0.05586 0.04994 -0.0285 0.2387 0.0109
-10.750 -0.9125 0.05456 0.04835 -0.0242 0.2388 0.0109
-10.500 -0.9212 0.05330 0.04679 -0.0203 0.2386 0.0109
-10.250 -0.9291 0.05233 0.04543 -0.0163 0.2385 0.0110
-10.000 -0.9330 0.05147 0.04415 -0.0126 0.2385 0.0110
-9.750 -0.8938 0.04466 0.03762 -0.0160 0.2382 0.0112
-9.500 -0.8745 0.04159 0.03451 -0.0160 0.2379 0.0115
-9.250 -0.8600 0.03958 0.03236 -0.0150 0.2378 0.0117
-9.000 -0.8459 0.03791 0.03051 -0.0137 0.2378 0.0121
-8.750 -0.8314 0.03662 0.02901 -0.0123 0.2376 0.0126
-8.500 -0.8180 0.03613 0.02824 -0.0104 0.2374 0.0131
-8.250 -0.8054 0.03620 0.02798 -0.0082 0.2374 0.0133
-8.000 -0.7924 0.03623 0.02765 -0.0061 0.2373 0.0134
-7.750 -0.7768 0.03593 0.02700 -0.0044 0.2373 0.0135
-7.500 -0.7560 0.03516 0.02601 -0.0036 0.2372 0.0135
-7.250 -0.7338 0.03432 0.02497 -0.0030 0.2372 0.0135
-7.000 -0.7107 0.03346 0.02395 -0.0026 0.2371 0.0135
-6.750 -0.6865 0.03257 0.02293 -0.0023 0.2371 0.0135
-6.500 -0.6586 0.02976 0.02021 -0.0029 0.2371 0.0136
-6.250 -0.6283 0.02735 0.01793 -0.0039 0.2371 0.0138
-6.000 -0.5980 0.02565 0.01631 -0.0047 0.2372 0.0140
-5.750 -0.5705 0.02459 0.01525 -0.0051 0.2373 0.0142
-5.500 -0.5439 0.02376 0.01439 -0.0052 0.2373 0.0144
-5.250 -0.5177 0.02308 0.01368 -0.0052 0.2372 0.0145
-5.000 -0.4916 0.02245 0.01303 -0.0052 0.2370 0.0146
-4.750 -0.4656 0.02189 0.01245 -0.0052 0.2369 0.0148
-4.500 -0.4399 0.02138 0.01193 -0.0051 0.2369 0.0150
-4.250 -0.4145 0.02094 0.01147 -0.0049 0.2369 0.0153
-4.000 -0.3895 0.02061 0.01111 -0.0047 0.2370 0.0156
-3.750 -0.3650 0.02043 0.01087 -0.0044 0.2371 0.0159
-3.500 -0.3413 0.02058 0.01089 -0.0039 0.2373 0.0161
-3.250 -0.3176 0.02073 0.01089 -0.0034 0.2374 0.0162
-3.000 -0.2923 0.02055 0.01068 -0.0032 0.2375 0.0163
-2.750 -0.2660 0.01926 0.00965 -0.0033 0.2377 0.0165
-2.500 -0.2440 0.01854 0.00905 -0.0026 0.2378 0.0168
-2.250 -0.2228 0.01799 0.00856 -0.0018 0.2380 0.0175
-2.000 -0.1995 0.01775 0.00832 -0.0013 0.2381 0.0181
-1.750 -0.1716 0.01802 0.00850 -0.0015 0.2383 0.0191
-1.500 -0.1501 0.01757 0.00810 -0.0008 0.2385 0.0197
-1.250 -0.1290 0.01704 0.00762 -0.0001 0.2384 0.0210
-1.000 -0.0996 0.01739 0.00790 -0.0004 0.2378 0.0225
-0.750 -0.0801 0.01662 0.00723 0.0005 0.2371 0.0236
-0.250 -0.0301 0.01631 0.00688 0.0009 0.2368 0.0279
0.000 -0.0038 0.01632 0.00687 0.0010 0.2369 0.0295
1.000 0.1020 0.01636 0.00684 0.0009 0.2354 0.0315
1.250 0.1289 0.01645 0.00694 0.0008 0.2352 0.0307
1.500 0.1560 0.01656 0.00707 0.0007 0.2351 0.0290
1.750 0.1831 0.01667 0.00721 0.0006 0.2348 0.0265
2.000 0.2100 0.01676 0.00731 0.0005 0.2342 0.0245
2.250 0.2368 0.01686 0.00745 0.0004 0.2335 0.0228
2.500 0.2638 0.01697 0.00757 0.0003 0.2331 0.0221
2.750 0.2908 0.01708 0.00766 0.0002 0.2327 0.0255
3.000 0.3174 0.01724 0.00785 0.0002 0.2315 0.0250
3.250 0.3434 0.01723 0.00792 0.0003 0.2287 0.0246
3.500 0.3700 0.01693 0.00771 0.0004 0.2248 0.0244
3.750 0.3961 0.01681 0.00767 0.0005 0.2217 0.0243
4.000 0.4220 0.01671 0.00766 0.0007 0.2196 0.0247
4.250 0.4476 0.01647 0.00754 0.0010 0.2168 0.0264
4.500 0.4754 0.01632 0.00751 0.0008 0.2105 0.0838
4.750 0.4924 0.01439 0.00728 0.0016 0.2053 0.6708
5.000 0.5174 0.01398 0.00716 0.0022 0.1680 0.7448
5.250 0.5436 0.01311 0.00638 0.0030 0.1437 0.7769
5.500 0.5698 0.01324 0.00644 0.0032 0.1202 0.7821
5.750 0.5942 0.01361 0.00661 0.0035 0.0904 0.7868
6.000 0.6190 0.01395 0.00685 0.0037 0.0737 0.7905
6.250 0.6431 0.01428 0.00714 0.0041 0.0601 0.7949
6.500 0.6674 0.01464 0.00744 0.0045 0.0486 0.7992
6.750 0.6922 0.01495 0.00773 0.0047 0.0413 0.8023
7.000 0.7168 0.01529 0.00804 0.0050 0.0350 0.8044
7.250 0.7413 0.01564 0.00837 0.0052 0.0301 0.8062
7.500 0.7653 0.01601 0.00873 0.0056 0.0261 0.8079
7.750 0.7891 0.01634 0.00910 0.0060 0.0233 0.8096
8.000 0.8119 0.01677 0.00954 0.0065 0.0206 0.8116
8.250 0.8348 0.01717 0.00999 0.0070 0.0193 0.8137
8.500 0.8577 0.01757 0.01045 0.0075 0.0181 0.8158
8.750 0.8799 0.01801 0.01094 0.0081 0.0170 0.8178
9.000 0.9014 0.01850 0.01146 0.0088 0.0161 0.8199
9.250 0.9207 0.01912 0.01213 0.0097 0.0150 0.8220
9.500 0.9396 0.01972 0.01279 0.0108 0.0145 0.8243
9.750 0.9594 0.02022 0.01338 0.0117 0.0139 0.8265
10.000 0.9783 0.02073 0.01397 0.0127 0.0133 0.8287
10.250 0.9965 0.02128 0.01460 0.0138 0.0127 0.8310
10.500 1.0130 0.02190 0.01530 0.0151 0.0123 0.8334
10.750 1.0285 0.02251 0.01598 0.0166 0.0119 0.8360
11.000 1.0400 0.02319 0.01674 0.0187 0.0116 0.8389
11.250 1.0501 0.02399 0.01760 0.0208 0.0113 0.8421
11.500 1.0552 0.02500 0.01871 0.0235 0.0108 0.8454
11.750 1.0562 0.02623 0.02007 0.0265 0.0106 0.8491
12.000 1.0667 0.02712 0.02107 0.0281 0.0105 0.8526
12.250 1.0754 0.02815 0.02222 0.0298 0.0103 0.8563
12.500 1.0831 0.02929 0.02349 0.0313 0.0102 0.8602
12.750 1.0902 0.03050 0.02483 0.0329 0.0100 0.8642
13.000 1.0960 0.03181 0.02630 0.0344 0.0098 0.8694
13.250 1.1021 0.03319 0.02781 0.0357 0.0096 0.8751
13.500 1.1055 0.03478 0.02955 0.0371 0.0095 0.8812
13.750 1.1083 0.03643 0.03136 0.0384 0.0094 0.8888
14.250 1.1158 0.03977 0.03504 0.0403 0.0089 0.9117
14.500 1.1259 0.04173 0.03719 0.0395 0.0087 0.9360
15.500 1.1252 0.05252 0.04850 0.0379 0.0082 1.0000
15.750 1.1203 0.05590 0.05201 0.0371 0.0081 1.0000
16.000 1.1109 0.06008 0.05631 0.0356 0.0079 1.0000
16.250 1.0950 0.06563 0.06203 0.0332 0.0080 1.0000
16.500 1.0785 0.07198 0.06855 0.0298 0.0079 1.0000
16.750 1.0529 0.08095 0.07772 0.0243 0.0079 1.0000
17.000 1.0201 0.09172 0.08867 0.0177 0.0080 1.0000
17.250 0.9903 0.10201 0.09910 0.0114 0.0080 1.0000
17.500 0.9624 0.11176 0.10899 0.0056 0.0081 1.0000
17.750 0.9292 0.12327 0.12066 -0.0012 0.0082 1.0000
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Polar data table (+)
Polar graphs
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