DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Reynolds number: 500,000 Max Cl/Cd: 82.01 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du84132v-il-500000.txt Download as CSV file: xf-du84132v-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3881 0.11446 0.11201 -0.0425 1.0000 0.0365
-11.500 -0.3885 0.11148 0.10905 -0.0426 1.0000 0.0370
-11.250 -0.3904 0.10836 0.10596 -0.0428 1.0000 0.0377
-11.000 -0.3491 0.08892 0.08672 -0.0564 0.9966 0.0411
-10.750 -0.3362 0.08579 0.08358 -0.0578 0.9952 0.0414
-10.500 -0.3259 0.08199 0.07979 -0.0601 0.9939 0.0417
-10.250 -0.3162 0.07806 0.07586 -0.0626 0.9925 0.0421
-10.000 -0.3118 0.07323 0.07103 -0.0655 0.9900 0.0425
-9.750 -0.3114 0.06708 0.06488 -0.0698 0.9873 0.0429
-9.500 -0.3605 0.04863 0.04632 -0.0861 0.9835 0.0435
-9.250 -0.3940 0.04031 0.03780 -0.0941 0.9759 0.0436
-9.000 -0.4017 0.03504 0.03231 -0.0993 0.9692 0.0441
-8.750 -0.3991 0.03093 0.02797 -0.1017 0.9632 0.0450
-8.500 -0.3914 0.02815 0.02463 -0.1039 0.9567 0.0476
-8.250 -0.3690 0.02582 0.02190 -0.1063 0.9541 0.0479
-8.000 -0.4052 0.02348 0.01800 -0.1062 0.9531 0.0292
-7.750 -0.3827 0.02139 0.01581 -0.1059 0.9480 0.0286
-7.500 -0.3557 0.01967 0.01394 -0.1063 0.9439 0.0282
-7.250 -0.3241 0.01816 0.01230 -0.1075 0.9411 0.0279
-7.000 -0.2906 0.01687 0.01091 -0.1089 0.9386 0.0277
-6.750 -0.2624 0.01589 0.00986 -0.1092 0.9339 0.0277
-6.500 -0.2353 0.01504 0.00894 -0.1092 0.9279 0.0278
-6.250 -0.2036 0.01422 0.00807 -0.1102 0.9237 0.0279
-6.000 -0.1745 0.01355 0.00735 -0.1107 0.9185 0.0282
-5.750 -0.1481 0.01300 0.00675 -0.1105 0.9118 0.0285
-5.500 -0.1167 0.01244 0.00612 -0.1114 0.9067 0.0288
-5.250 -0.0912 0.01201 0.00566 -0.1111 0.8990 0.0291
-5.000 -0.0638 0.01145 0.00506 -0.1112 0.8919 0.0299
-4.750 -0.0364 0.01109 0.00466 -0.1112 0.8848 0.0308
-4.500 -0.0093 0.01081 0.00436 -0.1110 0.8769 0.0318
-4.250 0.0192 0.01056 0.00408 -0.1112 0.8698 0.0331
-4.000 0.0461 0.01034 0.00383 -0.1109 0.8612 0.0351
-3.750 0.0745 0.01018 0.00365 -0.1110 0.8534 0.0396
-3.500 0.1014 0.00996 0.00340 -0.1108 0.8444 0.0471
-3.250 0.1280 0.00968 0.00311 -0.1105 0.8357 0.0590
-3.000 0.1542 0.00932 0.00289 -0.1103 0.8264 0.0952
-2.750 0.1791 0.00889 0.00272 -0.1100 0.8164 0.1675
-2.500 0.2053 0.00852 0.00256 -0.1099 0.8069 0.2380
-2.250 0.2310 0.00814 0.00241 -0.1097 0.7957 0.3130
-2.000 0.2562 0.00778 0.00231 -0.1094 0.7827 0.4035
-1.750 0.2821 0.00748 0.00219 -0.1091 0.7704 0.4689
-1.500 0.3074 0.00715 0.00211 -0.1088 0.7593 0.5684
-1.250 0.3322 0.00709 0.00233 -0.1079 0.7490 0.6628
-1.000 0.3587 0.00722 0.00245 -0.1073 0.7369 0.6938
-0.750 0.3851 0.00737 0.00256 -0.1068 0.7238 0.7148
-0.500 0.4116 0.00757 0.00270 -0.1062 0.7131 0.7295
-0.250 0.4382 0.00773 0.00282 -0.1057 0.7024 0.7378
0.000 0.4646 0.00791 0.00295 -0.1052 0.6901 0.7468
0.250 0.4902 0.00808 0.00308 -0.1045 0.6758 0.7535
0.500 0.5151 0.00831 0.00323 -0.1036 0.6610 0.7601
0.750 0.5404 0.00849 0.00332 -0.1029 0.6424 0.7670
1.000 0.5639 0.00870 0.00346 -0.1017 0.6240 0.7715
1.250 0.5884 0.00891 0.00358 -0.1008 0.6096 0.7769
1.750 0.6380 0.00924 0.00385 -0.0992 0.5817 0.7886
2.000 0.6624 0.00946 0.00401 -0.0983 0.5691 0.7962
2.250 0.6860 0.00959 0.00411 -0.0972 0.5565 0.8014
2.500 0.7099 0.00973 0.00421 -0.0963 0.5430 0.8056
2.750 0.7348 0.00987 0.00430 -0.0957 0.5288 0.8090
3.250 0.7843 0.01015 0.00444 -0.0945 0.4998 0.8144
3.500 0.8079 0.01025 0.00452 -0.0937 0.4841 0.8169
3.750 0.8321 0.01036 0.00460 -0.0929 0.4634 0.8196
4.000 0.8533 0.01059 0.00469 -0.0917 0.4342 0.8221
4.250 0.8750 0.01086 0.00485 -0.0906 0.4036 0.8246
4.500 0.8961 0.01121 0.00505 -0.0895 0.3834 0.8273
4.750 0.9181 0.01146 0.00523 -0.0885 0.3666 0.8295
5.000 0.9399 0.01165 0.00539 -0.0874 0.3512 0.8318
5.250 0.9622 0.01185 0.00556 -0.0864 0.3359 0.8343
5.750 1.0068 0.01231 0.00592 -0.0845 0.3090 0.8384
6.000 1.0292 0.01255 0.00614 -0.0837 0.2983 0.8398
6.250 1.0504 0.01283 0.00637 -0.0826 0.2860 0.8410
6.500 1.0712 0.01309 0.00658 -0.0815 0.2712 0.8422
6.750 1.0909 0.01338 0.00682 -0.0801 0.2604 0.8434
7.000 1.1108 0.01361 0.00705 -0.0788 0.2510 0.8446
7.250 1.1289 0.01391 0.00732 -0.0771 0.2406 0.8459
7.500 1.1490 0.01415 0.00756 -0.0759 0.2253 0.8473
7.750 1.1658 0.01456 0.00787 -0.0741 0.1997 0.8489
8.000 1.1791 0.01515 0.00831 -0.0718 0.1687 0.8509
8.250 1.1899 0.01588 0.00888 -0.0692 0.1454 0.8530
8.500 1.2048 0.01642 0.00939 -0.0673 0.1351 0.8550
9.000 1.2362 0.01746 0.01039 -0.0638 0.1103 0.8580
9.250 1.2502 0.01807 0.01094 -0.0618 0.1014 0.8595
9.500 1.2651 0.01859 0.01147 -0.0601 0.0963 0.8612
9.750 1.2791 0.01917 0.01208 -0.0582 0.0922 0.8630
10.000 1.2919 0.01984 0.01276 -0.0563 0.0883 0.8649
10.250 1.3055 0.02048 0.01346 -0.0545 0.0853 0.8668
10.500 1.3211 0.02102 0.01409 -0.0530 0.0831 0.8688
10.750 1.3349 0.02169 0.01482 -0.0514 0.0804 0.8708
11.000 1.3464 0.02253 0.01569 -0.0496 0.0770 0.8729
11.250 1.3540 0.02360 0.01680 -0.0474 0.0733 0.8753
11.500 1.3704 0.02413 0.01745 -0.0463 0.0711 0.8781
11.750 1.3840 0.02485 0.01825 -0.0449 0.0676 0.8813
12.000 1.3940 0.02584 0.01926 -0.0432 0.0637 0.8846
12.250 1.4064 0.02671 0.02021 -0.0419 0.0595 0.8882
12.500 1.4184 0.02766 0.02118 -0.0406 0.0536 0.8932
12.750 1.4290 0.02882 0.02236 -0.0395 0.0481 0.9004
13.000 1.4372 0.03033 0.02390 -0.0385 0.0436 0.9148
13.250 1.4435 0.03216 0.02580 -0.0378 0.0407 1.0000
13.500 1.4411 0.03454 0.02821 -0.0362 0.0381 1.0000
13.750 1.4466 0.03635 0.03013 -0.0352 0.0367 1.0000
14.000 1.4492 0.03848 0.03235 -0.0342 0.0353 1.0000
14.250 1.4489 0.04097 0.03492 -0.0334 0.0339 1.0000
14.500 1.4429 0.04412 0.03814 -0.0326 0.0326 1.0000
14.750 1.4443 0.04669 0.04080 -0.0322 0.0317 1.0000
15.000 1.4531 0.04853 0.04274 -0.0320 0.0305 1.0000
15.250 1.4578 0.05086 0.04517 -0.0319 0.0292 1.0000
15.500 1.4605 0.05349 0.04787 -0.0320 0.0283 1.0000
15.750 1.4605 0.05652 0.05097 -0.0322 0.0275 1.0000
16.000 1.4569 0.06010 0.05463 -0.0326 0.0269 1.0000
16.250 1.4597 0.06296 0.05760 -0.0330 0.0262 1.0000
16.500 1.4616 0.06600 0.06074 -0.0336 0.0254 1.0000
16.750 1.4626 0.06922 0.06406 -0.0343 0.0248 1.0000
17.000 1.4623 0.07272 0.06763 -0.0352 0.0240 1.0000
17.250 1.4595 0.07663 0.07162 -0.0363 0.0235 1.0000
17.500 1.4535 0.08109 0.07615 -0.0377 0.0229 1.0000
17.750 1.4463 0.08584 0.08101 -0.0393 0.0223 1.0000
18.000 1.4426 0.09018 0.08547 -0.0409 0.0218 1.0000
18.250 1.4378 0.09478 0.09018 -0.0428 0.0213 1.0000
18.500 1.4323 0.09958 0.09509 -0.0448 0.0207 1.0000
18.750 1.4257 0.10464 0.10026 -0.0470 0.0202 1.0000
19.000 1.4174 0.11005 0.10575 -0.0495 0.0196 1.0000
19.250 1.4072 0.11582 0.11160 -0.0523 0.0191 1.0000
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