DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.14 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-du84132v-il-1000000-n5.txt Download as CSV file: xf-du84132v-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DELFT DU84-132V3 AIRFOIL (MEASURED)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.9338 0.05824 0.05525 -0.0812 1.0000 0.0107
-15.750 -0.9509 0.05216 0.04904 -0.0850 1.0000 0.0108
-15.500 -0.9862 0.04419 0.04083 -0.0896 1.0000 0.0106
-15.250 -0.9959 0.04055 0.03708 -0.0908 1.0000 0.0106
-15.000 -0.9788 0.04015 0.03671 -0.0904 1.0000 0.0109
-14.750 -0.9845 0.03710 0.03355 -0.0912 0.9998 0.0109
-14.500 -0.9717 0.03498 0.03135 -0.0934 0.9989 0.0110
-14.250 -0.9591 0.03292 0.02920 -0.0954 0.9975 0.0112
-14.000 -0.9396 0.03175 0.02800 -0.0968 0.9959 0.0114
-13.750 -0.9224 0.03037 0.02655 -0.0982 0.9935 0.0116
-13.500 -0.9113 0.02875 0.02483 -0.0989 0.9905 0.0117
-13.250 -0.8952 0.02753 0.02354 -0.0997 0.9873 0.0118
-13.000 -0.8762 0.02640 0.02234 -0.1008 0.9843 0.0120
-12.750 -0.8568 0.02511 0.02095 -0.1022 0.9816 0.0121
-12.500 -0.8448 0.02395 0.01970 -0.1020 0.9759 0.0122
-12.250 -0.8247 0.02303 0.01870 -0.1026 0.9715 0.0124
-12.000 -0.7977 0.02217 0.01776 -0.1042 0.9689 0.0125
-11.500 -0.7483 0.02065 0.01608 -0.1057 0.9610 0.0127
-11.250 -0.7186 0.02004 0.01540 -0.1072 0.9576 0.0128
-11.000 -0.6863 0.01936 0.01465 -0.1092 0.9548 0.0129
-10.750 -0.6564 0.01849 0.01369 -0.1109 0.9507 0.0130
-10.500 -0.6319 0.01756 0.01268 -0.1114 0.9413 0.0131
-10.250 -0.6031 0.01669 0.01172 -0.1128 0.9332 0.0134
-10.000 -0.5737 0.01614 0.01112 -0.1139 0.9245 0.0135
-9.750 -0.5461 0.01564 0.01055 -0.1145 0.9163 0.0137
-9.500 -0.5196 0.01519 0.01003 -0.1148 0.9076 0.0139
-9.250 -0.4956 0.01470 0.00947 -0.1146 0.8979 0.0140
-9.000 -0.4715 0.01428 0.00896 -0.1143 0.8873 0.0141
-8.750 -0.4474 0.01395 0.00857 -0.1139 0.8759 0.0143
-8.500 -0.4231 0.01364 0.00819 -0.1135 0.8664 0.0146
-8.250 -0.3993 0.01325 0.00772 -0.1130 0.8585 0.0147
-8.000 -0.3748 0.01292 0.00733 -0.1126 0.8525 0.0149
-7.750 -0.3503 0.01258 0.00693 -0.1123 0.8461 0.0151
-7.500 -0.3257 0.01222 0.00650 -0.1119 0.8406 0.0152
-7.250 -0.3007 0.01186 0.00610 -0.1115 0.8340 0.0154
-7.000 -0.2760 0.01154 0.00573 -0.1111 0.8249 0.0155
-6.750 -0.2507 0.01124 0.00538 -0.1108 0.8151 0.0157
-6.500 -0.2256 0.01098 0.00505 -0.1104 0.8040 0.0158
-6.250 -0.2004 0.01074 0.00474 -0.1099 0.7928 0.0160
-6.000 -0.1749 0.01051 0.00446 -0.1096 0.7770 0.0161
-5.750 -0.1499 0.01034 0.00420 -0.1091 0.7641 0.0162
-5.500 -0.1242 0.01015 0.00395 -0.1087 0.7568 0.0163
-5.250 -0.0987 0.00988 0.00361 -0.1084 0.7500 0.0166
-5.000 -0.0721 0.00963 0.00334 -0.1083 0.7417 0.0169
-4.750 -0.0454 0.00943 0.00311 -0.1081 0.7314 0.0172
-4.500 -0.0196 0.00931 0.00292 -0.1077 0.7170 0.0175
-4.250 0.0062 0.00921 0.00275 -0.1073 0.7034 0.0178
-4.000 0.0327 0.00910 0.00259 -0.1071 0.6884 0.0182
-3.750 0.0581 0.00905 0.00245 -0.1066 0.6683 0.0186
-3.500 0.0841 0.00900 0.00232 -0.1062 0.6549 0.0191
-3.250 0.1110 0.00893 0.00221 -0.1060 0.6369 0.0196
-3.000 0.1367 0.00892 0.00211 -0.1056 0.6188 0.0201
-2.750 0.1634 0.00886 0.00200 -0.1054 0.6091 0.0220
-2.500 0.1906 0.00878 0.00191 -0.1053 0.5957 0.0245
-2.250 0.2167 0.00874 0.00186 -0.1050 0.5784 0.0400
-2.000 0.2431 0.00874 0.00182 -0.1047 0.5650 0.0439
-1.750 0.2702 0.00873 0.00178 -0.1045 0.5546 0.0471
-1.500 0.2971 0.00875 0.00175 -0.1043 0.5432 0.0486
-1.250 0.3237 0.00877 0.00172 -0.1041 0.5282 0.0512
-1.000 0.3496 0.00882 0.00171 -0.1037 0.5101 0.0552
-0.750 0.3755 0.00877 0.00168 -0.1034 0.4957 0.0890
-0.500 0.4014 0.00866 0.00167 -0.1032 0.4800 0.1413
-0.250 0.4274 0.00869 0.00167 -0.1029 0.4477 0.1633
0.000 0.4499 0.00879 0.00173 -0.1021 0.3985 0.2257
0.250 0.4738 0.00886 0.00181 -0.1016 0.3710 0.2787
0.500 0.4988 0.00873 0.00187 -0.1013 0.3502 0.3718
0.750 0.5242 0.00879 0.00194 -0.1010 0.3263 0.4107
1.000 0.5492 0.00888 0.00201 -0.1005 0.3054 0.4454
1.250 0.5749 0.00881 0.00208 -0.1003 0.2920 0.5153
1.500 0.5998 0.00863 0.00218 -0.1000 0.2766 0.6313
1.750 0.6248 0.00874 0.00237 -0.0994 0.2640 0.6890
2.000 0.6505 0.00891 0.00252 -0.0989 0.2547 0.7049
2.250 0.6768 0.00905 0.00264 -0.0986 0.2479 0.7155
2.500 0.7028 0.00921 0.00277 -0.0982 0.2422 0.7222
2.750 0.7294 0.00933 0.00289 -0.0980 0.2372 0.7293
3.000 0.7546 0.00954 0.00303 -0.0975 0.2222 0.7351
3.250 0.7786 0.00981 0.00321 -0.0968 0.2009 0.7391
3.500 0.8017 0.01014 0.00342 -0.0959 0.1784 0.7427
3.750 0.8239 0.01053 0.00367 -0.0949 0.1496 0.7479
4.000 0.8479 0.01079 0.00387 -0.0942 0.1410 0.7505
4.250 0.8727 0.01096 0.00404 -0.0937 0.1360 0.7528
4.500 0.8975 0.01114 0.00422 -0.0931 0.1310 0.7550
4.750 0.9211 0.01139 0.00444 -0.0924 0.1237 0.7569
5.000 0.9426 0.01175 0.00470 -0.0913 0.1001 0.7589
5.250 0.9646 0.01208 0.00495 -0.0902 0.0881 0.7607
5.500 0.9878 0.01231 0.00517 -0.0894 0.0830 0.7625
5.750 1.0109 0.01255 0.00538 -0.0886 0.0796 0.7643
6.000 1.0335 0.01279 0.00562 -0.0877 0.0765 0.7659
6.250 1.0555 0.01302 0.00584 -0.0867 0.0734 0.7677
6.500 1.0770 0.01321 0.00605 -0.0855 0.0720 0.7694
6.750 1.0980 0.01340 0.00626 -0.0843 0.0709 0.7707
7.000 1.1187 0.01362 0.00650 -0.0830 0.0689 0.7720
7.250 1.1390 0.01387 0.00676 -0.0817 0.0671 0.7733
7.500 1.1584 0.01416 0.00705 -0.0803 0.0644 0.7746
7.750 1.1779 0.01445 0.00734 -0.0789 0.0619 0.7758
8.000 1.1981 0.01471 0.00762 -0.0776 0.0596 0.7769
8.250 1.2131 0.01522 0.00803 -0.0755 0.0445 0.7780
8.500 1.2305 0.01563 0.00840 -0.0739 0.0422 0.7791
8.750 1.2485 0.01599 0.00877 -0.0723 0.0408 0.7802
9.000 1.2663 0.01637 0.00916 -0.0708 0.0392 0.7812
9.250 1.2842 0.01674 0.00955 -0.0693 0.0381 0.7821
9.500 1.3018 0.01712 0.00996 -0.0678 0.0375 0.7830
9.750 1.3189 0.01752 0.01040 -0.0662 0.0368 0.7841
10.000 1.3353 0.01796 0.01088 -0.0646 0.0361 0.7851
10.250 1.3506 0.01846 0.01143 -0.0629 0.0350 0.7862
10.500 1.3642 0.01907 0.01206 -0.0610 0.0334 0.7873
10.750 1.3786 0.01964 0.01267 -0.0592 0.0324 0.7885
11.000 1.3943 0.02015 0.01323 -0.0577 0.0317 0.7898
11.250 1.4104 0.02065 0.01377 -0.0563 0.0306 0.7911
11.500 1.4251 0.02124 0.01440 -0.0547 0.0281 0.7922
12.000 1.4468 0.02293 0.01607 -0.0510 0.0212 0.7945
12.250 1.4568 0.02387 0.01702 -0.0491 0.0196 0.7956
12.500 1.4670 0.02482 0.01801 -0.0474 0.0184 0.7966
12.750 1.4781 0.02574 0.01898 -0.0458 0.0179 0.7975
13.000 1.4884 0.02674 0.02003 -0.0443 0.0174 0.7985
13.250 1.4978 0.02783 0.02118 -0.0427 0.0170 0.7997
13.500 1.5057 0.02906 0.02247 -0.0412 0.0164 0.8008
13.750 1.5131 0.03038 0.02384 -0.0397 0.0159 0.8019
14.000 1.5202 0.03177 0.02530 -0.0383 0.0154 0.8031
14.250 1.5273 0.03322 0.02681 -0.0371 0.0150 0.8042
14.500 1.5353 0.03463 0.02829 -0.0360 0.0148 0.8053
14.750 1.5428 0.03614 0.02987 -0.0350 0.0144 0.8064
15.000 1.5494 0.03779 0.03160 -0.0341 0.0139 0.8076
15.250 1.5548 0.03961 0.03349 -0.0333 0.0136 0.8087
15.500 1.5594 0.04156 0.03550 -0.0326 0.0131 0.8097
15.750 1.5630 0.04369 0.03770 -0.0319 0.0129 0.8107
16.000 1.5645 0.04612 0.04019 -0.0314 0.0123 0.8117
16.250 1.5677 0.04845 0.04260 -0.0311 0.0119 0.8126
16.750 1.5739 0.05335 0.04766 -0.0310 0.0112 0.8147
17.000 1.5754 0.05610 0.05050 -0.0311 0.0107 0.8158
17.250 1.5756 0.05911 0.05359 -0.0314 0.0102 0.8169
17.500 1.5743 0.06239 0.05695 -0.0318 0.0098 0.8179
17.750 1.5728 0.06578 0.06043 -0.0325 0.0092 0.8190
18.000 1.5711 0.06931 0.06404 -0.0333 0.0086 0.8200
18.250 1.5676 0.07319 0.06800 -0.0343 0.0079 0.8210
18.500 1.5624 0.07740 0.07229 -0.0356 0.0072 0.8221
18.750 1.5565 0.08182 0.07680 -0.0370 0.0066 0.8231
19.000 1.5494 0.08656 0.08164 -0.0388 0.0061 0.8240
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