DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.64 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du84132v-il-1000000.txt Download as CSV file: xf-du84132v-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3140 0.10015 0.09849 -0.0552 0.9966 0.0251
-11.750 -0.6422 0.04976 0.04741 -0.0851 0.9972 0.0199
-11.500 -0.6425 0.04534 0.04275 -0.0919 0.9940 0.0200
-11.250 -0.6489 0.04068 0.03789 -0.0961 0.9890 0.0200
-11.000 -0.6534 0.03569 0.03251 -0.1015 0.9823 0.0202
-10.750 -0.6372 0.03339 0.03004 -0.1033 0.9787 0.0202
-10.500 -0.6186 0.03178 0.02830 -0.1042 0.9739 0.0201
-10.250 -0.5996 0.02903 0.02530 -0.1060 0.9708 0.0201
-10.000 -0.5763 0.02651 0.02255 -0.1080 0.9688 0.0202
-9.750 -0.5478 0.02468 0.02054 -0.1102 0.9675 0.0202
-9.500 -0.5280 0.02304 0.01873 -0.1101 0.9615 0.0202
-9.250 -0.5029 0.02067 0.01625 -0.1111 0.9574 0.0198
-9.000 -0.4716 0.01943 0.01485 -0.1129 0.9543 0.0198
-8.750 -0.4428 0.01923 0.01453 -0.1136 0.9485 0.0201
-8.500 -0.4191 0.01747 0.01260 -0.1138 0.9409 0.0203
-8.250 -0.3893 0.01661 0.01166 -0.1147 0.9356 0.0202
-8.000 -0.3642 0.01566 0.01062 -0.1146 0.9280 0.0203
-7.750 -0.3356 0.01467 0.00954 -0.1152 0.9219 0.0204
-7.500 -0.3099 0.01414 0.00895 -0.1151 0.9145 0.0203
-7.250 -0.2827 0.01352 0.00825 -0.1152 0.9073 0.0203
-7.000 -0.2578 0.01299 0.00768 -0.1149 0.8992 0.0202
-6.750 -0.2327 0.01239 0.00701 -0.1146 0.8910 0.0202
-6.500 -0.2090 0.01176 0.00632 -0.1140 0.8828 0.0203
-6.250 -0.1845 0.01123 0.00573 -0.1136 0.8749 0.0204
-6.000 -0.1604 0.01067 0.00512 -0.1131 0.8677 0.0207
-5.750 -0.1352 0.01026 0.00465 -0.1128 0.8602 0.0210
-5.500 -0.1093 0.00992 0.00425 -0.1125 0.8535 0.0214
-5.250 -0.0833 0.00963 0.00393 -0.1122 0.8462 0.0217
-5.000 -0.0568 0.00939 0.00363 -0.1121 0.8394 0.0222
-4.750 -0.0305 0.00914 0.00337 -0.1118 0.8311 0.0226
-4.500 -0.0041 0.00894 0.00312 -0.1115 0.8215 0.0230
-4.250 0.0220 0.00877 0.00289 -0.1111 0.8093 0.0234
-4.000 0.0482 0.00862 0.00268 -0.1108 0.7966 0.0238
-3.750 0.0745 0.00848 0.00249 -0.1104 0.7812 0.0242
-3.250 0.1264 0.00828 0.00213 -0.1095 0.7560 0.0268
-3.000 0.1531 0.00817 0.00203 -0.1093 0.7463 0.0314
-2.750 0.1802 0.00808 0.00197 -0.1091 0.7368 0.0453
-2.250 0.2340 0.00795 0.00178 -0.1087 0.7141 0.0564
-2.000 0.2606 0.00787 0.00171 -0.1085 0.7035 0.0657
-1.750 0.2867 0.00756 0.00161 -0.1083 0.6927 0.1394
-1.500 0.3131 0.00744 0.00155 -0.1081 0.6761 0.1701
-1.250 0.3384 0.00726 0.00149 -0.1077 0.6615 0.2351
-0.750 0.3882 0.00681 0.00142 -0.1070 0.6215 0.4074
-0.500 0.4138 0.00672 0.00141 -0.1067 0.6035 0.4584
-0.250 0.4389 0.00651 0.00139 -0.1063 0.5827 0.5466
0.000 0.4631 0.00636 0.00149 -0.1057 0.5665 0.6563
0.250 0.4892 0.00647 0.00161 -0.1052 0.5519 0.6939
0.500 0.5159 0.00660 0.00171 -0.1049 0.5390 0.7089
0.750 0.5426 0.00673 0.00179 -0.1046 0.5270 0.7188
1.250 0.5961 0.00701 0.00196 -0.1040 0.5041 0.7333
1.500 0.6222 0.00718 0.00210 -0.1035 0.4935 0.7405
1.750 0.6484 0.00738 0.00224 -0.1031 0.4802 0.7484
2.000 0.6744 0.00754 0.00235 -0.1027 0.4518 0.7532
2.250 0.6977 0.00787 0.00252 -0.1017 0.4180 0.7571
2.500 0.7207 0.00822 0.00272 -0.1008 0.3878 0.7610
2.750 0.7452 0.00852 0.00292 -0.1001 0.3694 0.7654
3.000 0.7699 0.00875 0.00308 -0.0995 0.3514 0.7688
3.250 0.7944 0.00898 0.00326 -0.0988 0.3311 0.7714
3.500 0.8183 0.00926 0.00344 -0.0981 0.3106 0.7741
3.750 0.8429 0.00951 0.00362 -0.0974 0.2973 0.7779
4.000 0.8674 0.00974 0.00379 -0.0968 0.2829 0.7803
4.250 0.8920 0.00999 0.00396 -0.0962 0.2690 0.7822
4.500 0.9162 0.01016 0.00410 -0.0956 0.2599 0.7843
4.750 0.9407 0.01033 0.00426 -0.0950 0.2526 0.7860
5.000 0.9650 0.01051 0.00443 -0.0943 0.2452 0.7876
5.250 0.9894 0.01069 0.00459 -0.0937 0.2368 0.7891
5.500 1.0126 0.01093 0.00477 -0.0929 0.2196 0.7906
5.750 1.0325 0.01135 0.00502 -0.0916 0.1899 0.7923
6.000 1.0485 0.01198 0.00542 -0.0896 0.1493 0.7942
6.250 1.0690 0.01235 0.00572 -0.0883 0.1392 0.7961
6.500 1.0910 0.01261 0.00597 -0.0873 0.1308 0.7977
6.750 1.1107 0.01285 0.00619 -0.0858 0.1218 0.7993
7.000 1.1256 0.01330 0.00651 -0.0836 0.0978 0.8005
7.250 1.1445 0.01358 0.00678 -0.0820 0.0924 0.8016
7.500 1.1629 0.01390 0.00707 -0.0804 0.0868 0.8028
7.750 1.1830 0.01415 0.00734 -0.0791 0.0844 0.8039
8.000 1.2021 0.01445 0.00766 -0.0776 0.0813 0.8054
8.250 1.2204 0.01478 0.00800 -0.0760 0.0784 0.8069
8.500 1.2385 0.01514 0.00836 -0.0744 0.0750 0.8084
8.750 1.2574 0.01546 0.00870 -0.0730 0.0732 0.8097
9.000 1.2772 0.01572 0.00901 -0.0718 0.0722 0.8108
9.250 1.2963 0.01603 0.00934 -0.0704 0.0707 0.8118
9.500 1.3145 0.01638 0.00971 -0.0690 0.0682 0.8127
9.750 1.3312 0.01679 0.01012 -0.0674 0.0653 0.8139
10.000 1.3473 0.01721 0.01056 -0.0657 0.0622 0.8153
10.250 1.3651 0.01756 0.01096 -0.0643 0.0600 0.8166
10.500 1.3795 0.01810 0.01146 -0.0625 0.0526 0.8179
10.750 1.3919 0.01875 0.01206 -0.0604 0.0451 0.8192
11.000 1.4040 0.01943 0.01273 -0.0584 0.0424 0.8205
11.250 1.4158 0.02016 0.01346 -0.0563 0.0402 0.8219
11.500 1.4276 0.02090 0.01423 -0.0544 0.0381 0.8233
11.750 1.4413 0.02155 0.01495 -0.0528 0.0369 0.8247
12.000 1.4526 0.02236 0.01582 -0.0510 0.0354 0.8262
12.250 1.4606 0.02341 0.01690 -0.0488 0.0335 0.8275
12.500 1.4708 0.02436 0.01790 -0.0471 0.0319 0.8285
12.750 1.4853 0.02501 0.01862 -0.0458 0.0304 0.8302
13.000 1.4971 0.02588 0.01953 -0.0444 0.0282 0.8317
13.250 1.5067 0.02692 0.02061 -0.0428 0.0263 0.8333
13.500 1.5161 0.02801 0.02173 -0.0413 0.0244 0.8348
13.750 1.5240 0.02926 0.02299 -0.0398 0.0229 0.8363
14.000 1.5317 0.03056 0.02434 -0.0384 0.0220 0.8379
14.250 1.5384 0.03200 0.02584 -0.0370 0.0212 0.8394
14.500 1.5442 0.03357 0.02746 -0.0358 0.0205 0.8409
14.750 1.5487 0.03530 0.02925 -0.0346 0.0199 0.8424
15.000 1.5511 0.03731 0.03131 -0.0334 0.0190 0.8437
15.250 1.5533 0.03941 0.03350 -0.0324 0.0185 0.8456
15.500 1.5592 0.04122 0.03540 -0.0317 0.0182 0.8477
15.750 1.5628 0.04331 0.03759 -0.0311 0.0179 0.8496
16.000 1.5661 0.04553 0.03990 -0.0306 0.0173 0.8517
16.250 1.5673 0.04805 0.04250 -0.0303 0.0169 0.8538
16.500 1.5668 0.05087 0.04541 -0.0301 0.0164 0.8559
16.750 1.5652 0.05393 0.04855 -0.0301 0.0160 0.8579
17.000 1.5603 0.05751 0.05223 -0.0304 0.0155 0.8603
17.250 1.5534 0.06148 0.05632 -0.0309 0.0151 0.8633
17.500 1.5567 0.06420 0.05916 -0.0314 0.0149 0.8673
17.750 1.5588 0.06711 0.06219 -0.0319 0.0144 0.8723
18.000 1.5585 0.07025 0.06549 -0.0325 0.0140 0.8876
18.250 1.5657 0.07435 0.06979 -0.0357 0.0134 0.9526
18.500 1.5591 0.07846 0.07398 -0.0367 0.0129 1.0000
18.750 1.5507 0.08326 0.07888 -0.0383 0.0125 1.0000
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