DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Reynolds number: 50,000 Max Cl/Cd: 31.36 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du84132v-il-50000.txt Download as CSV file: xf-du84132v-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3347 0.10653 0.09967 -0.0240 1.0000 0.3179
-8.250 -0.3312 0.10429 0.09748 -0.0222 1.0000 0.3275
-8.000 -0.3399 0.10227 0.09558 -0.0203 1.0000 0.3352
-7.750 -0.3437 0.10055 0.09394 -0.0180 1.0000 0.3461
-7.500 -0.3480 0.09820 0.09167 -0.0160 1.0000 0.3527
-7.250 -0.3855 0.09892 0.09261 -0.0119 1.0000 0.3661
-7.000 -0.3628 0.09447 0.08814 -0.0110 1.0000 0.3695
-6.750 -0.3632 0.09215 0.08589 -0.0089 1.0000 0.3741
-6.500 -0.3872 0.09121 0.08509 -0.0052 1.0000 0.3856
-6.250 -0.5595 0.06538 0.05886 -0.0359 1.0000 0.1653
-6.000 -0.5580 0.05857 0.05155 -0.0389 1.0000 0.1491
-5.750 -0.5467 0.05437 0.04699 -0.0398 1.0000 0.1419
-5.500 -0.5329 0.04999 0.04217 -0.0411 1.0000 0.1362
-5.250 -0.5120 0.04576 0.03686 -0.0431 1.0000 0.1297
-5.000 -0.4926 0.04311 0.03396 -0.0430 1.0000 0.1286
-4.750 -0.4720 0.04077 0.03128 -0.0430 1.0000 0.1280
-4.500 -0.4505 0.03882 0.02896 -0.0429 1.0000 0.1285
-4.250 -0.4284 0.03727 0.02698 -0.0426 1.0000 0.1302
-4.000 -0.4089 0.03567 0.02540 -0.0421 1.0000 0.1339
-3.750 -0.3885 0.03454 0.02416 -0.0414 1.0000 0.1379
-3.500 -0.3675 0.03351 0.02293 -0.0405 1.0000 0.1423
-3.250 -0.3469 0.03258 0.02183 -0.0394 1.0000 0.1473
-3.000 -0.3284 0.03177 0.02114 -0.0380 1.0000 0.1558
-2.750 -0.3097 0.03104 0.02050 -0.0366 1.0000 0.1705
-2.500 -0.2914 0.03029 0.01994 -0.0353 1.0000 0.1996
-2.250 -0.2679 0.02743 0.01921 -0.0354 1.0000 0.4408
-2.000 -0.2864 0.02815 0.02137 -0.0226 1.0000 0.7016
-1.750 -0.2916 0.02924 0.02233 -0.0145 1.0000 0.7905
-1.500 -0.2959 0.02936 0.02234 -0.0072 1.0000 0.8443
-1.250 -0.2993 0.02900 0.02194 0.0001 1.0000 0.8954
-1.000 -0.1797 0.03072 0.02312 -0.0152 1.0000 1.0000
-0.750 -0.1815 0.03035 0.02259 -0.0129 1.0000 1.0000
-0.500 -0.1642 0.03061 0.02262 -0.0138 0.9953 1.0000
-0.250 -0.1163 0.03198 0.02365 -0.0198 0.9807 1.0000
0.000 -0.0769 0.03296 0.02436 -0.0240 0.9668 1.0000
0.250 -0.0486 0.03356 0.02477 -0.0261 0.9551 1.0000
0.500 -0.0192 0.03430 0.02533 -0.0283 0.9436 1.0000
0.750 0.0144 0.03521 0.02606 -0.0311 0.9317 1.0000
1.000 0.0520 0.03623 0.02691 -0.0344 0.9191 1.0000
1.250 0.0926 0.03724 0.02778 -0.0380 0.9047 1.0000
1.500 0.1310 0.03810 0.02850 -0.0410 0.8891 1.0000
1.750 0.1692 0.03888 0.02918 -0.0438 0.8728 1.0000
2.000 0.2070 0.03963 0.02983 -0.0463 0.8567 1.0000
2.250 0.2435 0.04032 0.03044 -0.0486 0.8402 1.0000
2.500 0.2752 0.04095 0.03102 -0.0500 0.8234 1.0000
2.750 0.3070 0.04156 0.03160 -0.0514 0.8063 1.0000
3.000 0.3395 0.04219 0.03220 -0.0528 0.7897 1.0000
3.250 0.3712 0.04290 0.03290 -0.0542 0.7745 1.0000
3.500 0.4023 0.04366 0.03366 -0.0554 0.7593 1.0000
3.750 0.4335 0.04441 0.03441 -0.0566 0.7441 1.0000
4.000 0.4655 0.04508 0.03510 -0.0577 0.7287 1.0000
4.250 0.4994 0.04566 0.03571 -0.0588 0.7137 1.0000
4.500 0.5312 0.04633 0.03640 -0.0598 0.6992 1.0000
4.750 0.5591 0.04717 0.03729 -0.0604 0.6849 1.0000
5.000 0.5874 0.04796 0.03813 -0.0609 0.6707 1.0000
5.250 0.6137 0.04884 0.03906 -0.0612 0.6566 1.0000
5.500 0.6352 0.05001 0.04030 -0.0612 0.6426 1.0000
5.750 0.6543 0.05138 0.04171 -0.0610 0.6289 1.0000
6.000 0.6721 0.05286 0.04325 -0.0609 0.6155 1.0000
6.250 0.6899 0.05437 0.04481 -0.0607 0.6025 1.0000
6.500 0.7140 0.05541 0.04594 -0.0606 0.5902 1.0000
6.750 0.7667 0.05423 0.04490 -0.0615 0.5802 1.0000
7.000 0.7582 0.05787 0.04856 -0.0605 0.5666 1.0000
7.250 0.7604 0.06062 0.05137 -0.0598 0.5534 1.0000
7.500 0.7836 0.06164 0.05250 -0.0594 0.5410 1.0000
7.750 0.8917 0.05416 0.04533 -0.0596 0.5303 1.0000
8.000 1.0299 0.04479 0.03627 -0.0636 0.5132 1.0000
8.250 0.8945 0.05937 0.05068 -0.0571 0.4998 1.0000
8.500 1.0942 0.04374 0.03547 -0.0621 0.4776 1.0000
8.750 1.1137 0.04409 0.03594 -0.0604 0.4598 1.0000
9.000 1.1971 0.04028 0.03211 -0.0637 0.4331 1.0000
9.250 1.2019 0.04140 0.03337 -0.0605 0.4126 1.0000
9.500 1.2468 0.04060 0.03245 -0.0609 0.3836 1.0000
9.750 1.2803 0.04083 0.03245 -0.0605 0.3526 1.0000
10.000 1.2788 0.04250 0.03425 -0.0566 0.3307 1.0000
10.250 1.3076 0.04279 0.03422 -0.0559 0.3031 1.0000
10.500 1.3123 0.04448 0.03601 -0.0531 0.2848 1.0000
10.750 1.3212 0.04623 0.03781 -0.0508 0.2684 1.0000
11.000 1.3350 0.04801 0.03961 -0.0492 0.2532 1.0000
11.250 1.3513 0.04998 0.04160 -0.0480 0.2393 1.0000
11.500 1.3374 0.05265 0.04459 -0.0437 0.2314 1.0000
11.750 1.3409 0.05491 0.04695 -0.0413 0.2210 1.0000
12.000 1.3559 0.05660 0.04862 -0.0400 0.2086 1.0000
12.250 1.3280 0.06028 0.05265 -0.0356 0.2050 1.0000
12.500 1.0029 0.10242 0.09525 -0.0451 0.2455 1.0000
12.750 0.9947 0.10870 0.10156 -0.0469 0.2390 1.0000
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Polar data table (+)
Polar graphs
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