DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Reynolds number: 500,000 Max Cl/Cd: 75.33 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-du84132v-il-500000-n5.txt Download as CSV file: xf-du84132v-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6523 0.06777 0.06469 -0.0714 1.0000 0.0162
-13.000 -0.6890 0.05829 0.05504 -0.0777 1.0000 0.0162
-12.750 -0.7146 0.05221 0.04880 -0.0810 1.0000 0.0161
-12.500 -0.7311 0.04720 0.04363 -0.0842 0.9992 0.0161
-12.250 -0.7336 0.04248 0.03868 -0.0893 0.9960 0.0161
-12.000 -0.7323 0.03887 0.03486 -0.0926 0.9916 0.0161
-11.750 -0.7271 0.03627 0.03207 -0.0946 0.9863 0.0162
-11.500 -0.7172 0.03377 0.02935 -0.0971 0.9815 0.0162
-11.250 -0.7087 0.03184 0.02723 -0.0977 0.9738 0.0162
-11.000 -0.6900 0.02989 0.02509 -0.0992 0.9697 0.0162
-10.750 -0.6704 0.02756 0.02254 -0.1010 0.9671 0.0164
-10.500 -0.6564 0.02608 0.02093 -0.1003 0.9599 0.0165
-10.250 -0.6334 0.02461 0.01935 -0.1013 0.9562 0.0168
-10.000 -0.6056 0.02343 0.01806 -0.1028 0.9538 0.0170
-9.750 -0.5790 0.02255 0.01713 -0.1038 0.9499 0.0173
-9.500 -0.5561 0.02174 0.01623 -0.1038 0.9430 0.0176
-9.250 -0.5268 0.02068 0.01505 -0.1052 0.9388 0.0177
-9.000 -0.4999 0.01971 0.01396 -0.1058 0.9335 0.0178
-8.750 -0.4724 0.01880 0.01295 -0.1065 0.9276 0.0179
-8.500 -0.4414 0.01793 0.01197 -0.1078 0.9229 0.0180
-8.250 -0.4135 0.01716 0.01112 -0.1084 0.9169 0.0181
-8.000 -0.3855 0.01646 0.01033 -0.1090 0.9111 0.0182
-7.750 -0.3557 0.01578 0.00956 -0.1099 0.9060 0.0184
-7.500 -0.3306 0.01522 0.00894 -0.1098 0.8987 0.0185
-7.250 -0.3036 0.01467 0.00831 -0.1100 0.8918 0.0187
-7.000 -0.2776 0.01417 0.00775 -0.1100 0.8842 0.0189
-6.750 -0.2514 0.01372 0.00723 -0.1099 0.8760 0.0191
-6.500 -0.2252 0.01329 0.00674 -0.1098 0.8680 0.0193
-6.250 -0.1990 0.01291 0.00628 -0.1097 0.8599 0.0195
-6.000 -0.1727 0.01256 0.00587 -0.1096 0.8530 0.0197
-5.750 -0.1467 0.01224 0.00550 -0.1094 0.8461 0.0199
-5.500 -0.1199 0.01196 0.00515 -0.1093 0.8395 0.0201
-5.250 -0.0951 0.01158 0.00474 -0.1089 0.8309 0.0204
-5.000 -0.0691 0.01127 0.00438 -0.1087 0.8226 0.0208
-4.750 -0.0431 0.01100 0.00408 -0.1084 0.8135 0.0213
-4.500 -0.0166 0.01078 0.00381 -0.1082 0.8045 0.0218
-4.250 0.0099 0.01059 0.00356 -0.1080 0.7948 0.0225
-4.000 0.0361 0.01040 0.00334 -0.1077 0.7814 0.0235
-3.750 0.0623 0.01026 0.00312 -0.1073 0.7683 0.0246
-3.500 0.0886 0.01012 0.00291 -0.1070 0.7577 0.0266
-3.250 0.1150 0.00999 0.00277 -0.1067 0.7483 0.0309
-3.000 0.1417 0.00990 0.00268 -0.1065 0.7373 0.0427
-2.750 0.1684 0.00983 0.00257 -0.1063 0.7239 0.0478
-2.500 0.1947 0.00976 0.00244 -0.1059 0.7133 0.0522
-2.250 0.2210 0.00970 0.00234 -0.1056 0.7012 0.0576
-2.000 0.2470 0.00948 0.00222 -0.1054 0.6865 0.0911
-1.750 0.2720 0.00925 0.00212 -0.1050 0.6709 0.1496
-1.500 0.2975 0.00912 0.00205 -0.1047 0.6576 0.1860
-1.000 0.3489 0.00877 0.00194 -0.1042 0.6272 0.2969
-0.750 0.3741 0.00853 0.00192 -0.1039 0.6143 0.3857
-0.500 0.4002 0.00834 0.00189 -0.1037 0.6015 0.4487
-0.250 0.4260 0.00816 0.00187 -0.1035 0.5878 0.5178
0.000 0.4505 0.00797 0.00195 -0.1029 0.5753 0.6078
0.250 0.4747 0.00807 0.00217 -0.1020 0.5628 0.6739
0.500 0.5000 0.00825 0.00230 -0.1014 0.5470 0.6966
0.750 0.5250 0.00844 0.00242 -0.1007 0.5263 0.7096
1.000 0.5493 0.00868 0.00254 -0.0999 0.5047 0.7197
1.250 0.5745 0.00889 0.00266 -0.0993 0.4878 0.7288
1.500 0.6006 0.00904 0.00278 -0.0989 0.4730 0.7362
1.750 0.6246 0.00930 0.00293 -0.0981 0.4423 0.7441
2.000 0.6477 0.00962 0.00310 -0.0971 0.4100 0.7515
2.250 0.6695 0.01001 0.00335 -0.0959 0.3839 0.7571
2.500 0.6934 0.01030 0.00354 -0.0951 0.3659 0.7621
2.750 0.7180 0.01055 0.00370 -0.0945 0.3471 0.7655
3.000 0.7420 0.01079 0.00386 -0.0938 0.3272 0.7677
3.250 0.7652 0.01107 0.00404 -0.0930 0.3086 0.7699
3.500 0.7890 0.01131 0.00422 -0.0922 0.2936 0.7719
3.750 0.8135 0.01151 0.00439 -0.0916 0.2838 0.7739
4.000 0.8377 0.01173 0.00456 -0.0910 0.2717 0.7763
4.250 0.8618 0.01195 0.00474 -0.0903 0.2636 0.7789
4.500 0.8857 0.01219 0.00493 -0.0896 0.2558 0.7815
4.750 0.9095 0.01239 0.00512 -0.0890 0.2476 0.7835
5.000 0.9323 0.01262 0.00532 -0.0881 0.2404 0.7851
5.250 0.9566 0.01277 0.00551 -0.0874 0.2333 0.7866
5.500 0.9793 0.01300 0.00571 -0.0866 0.2214 0.7879
5.750 1.0006 0.01331 0.00594 -0.0855 0.2028 0.7891
6.000 1.0196 0.01370 0.00622 -0.0840 0.1812 0.7903
6.250 1.0341 0.01426 0.00661 -0.0818 0.1482 0.7917
6.500 1.0516 0.01466 0.00694 -0.0800 0.1386 0.7931
6.750 1.0710 0.01498 0.00725 -0.0786 0.1287 0.7948
7.000 1.0901 0.01532 0.00759 -0.0771 0.1185 0.7964
7.250 1.1054 0.01589 0.00803 -0.0752 0.0984 0.7978
7.500 1.1231 0.01628 0.00841 -0.0735 0.0923 0.7988
7.750 1.1407 0.01668 0.00880 -0.0719 0.0873 0.7998
8.000 1.1593 0.01703 0.00918 -0.0705 0.0845 0.8009
8.250 1.1779 0.01738 0.00957 -0.0691 0.0824 0.8020
8.500 1.1955 0.01778 0.01001 -0.0676 0.0797 0.8032
8.750 1.2121 0.01824 0.01049 -0.0659 0.0767 0.8044
9.000 1.2282 0.01873 0.01100 -0.0642 0.0737 0.8056
9.250 1.2460 0.01914 0.01146 -0.0629 0.0721 0.8069
9.500 1.2632 0.01957 0.01195 -0.0614 0.0700 0.8082
9.750 1.2796 0.02006 0.01248 -0.0599 0.0672 0.8095
10.000 1.2947 0.02063 0.01307 -0.0583 0.0642 0.8108
10.250 1.3093 0.02125 0.01372 -0.0567 0.0614 0.8121
10.500 1.3251 0.02179 0.01432 -0.0552 0.0585 0.8134
10.750 1.3390 0.02244 0.01499 -0.0536 0.0529 0.8148
11.000 1.3501 0.02327 0.01580 -0.0518 0.0455 0.8161
11.250 1.3611 0.02414 0.01668 -0.0500 0.0430 0.8174
11.500 1.3718 0.02506 0.01762 -0.0482 0.0412 0.8188
11.750 1.3822 0.02604 0.01864 -0.0465 0.0395 0.8201
12.000 1.3923 0.02706 0.01972 -0.0449 0.0380 0.8215
12.250 1.4029 0.02808 0.02083 -0.0434 0.0367 0.8230
12.500 1.4116 0.02927 0.02210 -0.0419 0.0351 0.8244
12.750 1.4178 0.03069 0.02358 -0.0403 0.0335 0.8258
13.000 1.4237 0.03220 0.02514 -0.0388 0.0320 0.8271
13.250 1.4355 0.03329 0.02633 -0.0378 0.0305 0.8284
13.500 1.4446 0.03461 0.02774 -0.0367 0.0280 0.8298
13.750 1.4517 0.03614 0.02934 -0.0356 0.0262 0.8313
14.000 1.4583 0.03776 0.03104 -0.0347 0.0246 0.8328
14.250 1.4634 0.03958 0.03290 -0.0338 0.0228 0.8343
14.500 1.4674 0.04157 0.03494 -0.0330 0.0215 0.8359
14.750 1.4713 0.04366 0.03710 -0.0323 0.0208 0.8376
15.000 1.4734 0.04600 0.03951 -0.0318 0.0199 0.8393
15.250 1.4742 0.04858 0.04216 -0.0314 0.0190 0.8409
15.500 1.4755 0.05123 0.04489 -0.0312 0.0184 0.8425
16.000 1.4782 0.05679 0.05069 -0.0314 0.0176 0.8459
16.250 1.4780 0.05991 0.05393 -0.0317 0.0172 0.8479
16.500 1.4769 0.06326 0.05739 -0.0323 0.0168 0.8500
16.750 1.4748 0.06685 0.06109 -0.0330 0.0164 0.8522
17.000 1.4712 0.07076 0.06512 -0.0340 0.0160 0.8545
17.250 1.4667 0.07494 0.06941 -0.0353 0.0157 0.8570
17.750 1.4533 0.08428 0.07900 -0.0385 0.0150 0.8635
18.000 1.4503 0.08855 0.08342 -0.0401 0.0148 0.8687
18.500 1.4427 0.09791 0.09317 -0.0444 0.0141 0.9107
18.750 1.4355 0.10296 0.09835 -0.0467 0.0138 1.0000
19.000 1.4287 0.10811 0.10362 -0.0491 0.0135 1.0000
19.250 1.4213 0.11342 0.10904 -0.0516 0.0131 1.0000
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Polar data table (+)
Polar graphs
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