BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il) Reynolds number: 50,000 Max Cl/Cd: 27.91 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v23010-il-50000-n5.txt Download as CSV file: xf-v23010-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL V23010-1.58 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5335 0.11475 0.10744 -0.0020 1.0000 0.1626
-9.500 -0.5022 0.11037 0.10300 0.0013 1.0000 0.1687
-9.250 -0.5295 0.10805 0.10086 -0.0034 1.0000 0.1786
-9.000 -0.4970 0.10389 0.09664 0.0000 1.0000 0.1851
-8.750 -0.5063 0.10086 0.09373 -0.0018 1.0000 0.1970
-8.500 -0.4944 0.09780 0.09068 -0.0010 1.0000 0.2063
-8.250 -0.4893 0.09465 0.08760 -0.0007 1.0000 0.2186
-8.000 -0.4875 0.09178 0.08480 -0.0004 1.0000 0.2338
-7.750 -0.4831 0.08907 0.08216 0.0004 1.0000 0.2507
-7.500 -0.5518 0.07224 0.06481 -0.0230 1.0000 0.0983
-7.250 -0.5482 0.06714 0.05948 -0.0236 1.0000 0.0835
-7.000 -0.5399 0.06342 0.05571 -0.0232 1.0000 0.0803
-6.750 -0.5357 0.05966 0.05172 -0.0228 1.0000 0.0772
-6.500 -0.5337 0.05680 0.04806 -0.0216 1.0000 0.0725
-6.250 -0.5207 0.05366 0.04483 -0.0207 1.0000 0.0720
-6.000 -0.5074 0.05073 0.04176 -0.0196 1.0000 0.0714
-5.750 -0.4934 0.04798 0.03885 -0.0185 1.0000 0.0705
-5.500 -0.4788 0.04539 0.03605 -0.0172 1.0000 0.0693
-5.250 -0.4634 0.04301 0.03343 -0.0157 1.0000 0.0681
-5.000 -0.4472 0.04079 0.03095 -0.0142 1.0000 0.0671
-4.750 -0.4300 0.03875 0.02862 -0.0126 1.0000 0.0661
-4.500 -0.4119 0.03688 0.02647 -0.0111 1.0000 0.0654
-4.250 -0.3929 0.03516 0.02449 -0.0095 1.0000 0.0648
-4.000 -0.3734 0.03360 0.02271 -0.0080 1.0000 0.0648
-3.750 -0.3540 0.03222 0.02118 -0.0066 1.0000 0.0656
-3.500 -0.3344 0.03098 0.01980 -0.0052 1.0000 0.0668
-3.250 -0.3146 0.02984 0.01850 -0.0037 1.0000 0.0679
-3.000 -0.2945 0.02877 0.01731 -0.0023 1.0000 0.0685
-2.750 -0.2742 0.02779 0.01625 -0.0009 1.0000 0.0687
-2.500 -0.2540 0.02690 0.01531 0.0006 1.0000 0.0692
-2.250 -0.2342 0.02614 0.01451 0.0020 1.0000 0.0698
-2.000 -0.2149 0.02549 0.01385 0.0035 1.0000 0.0705
-1.750 -0.1673 0.02474 0.01300 0.0000 0.9853 0.0726
-1.500 -0.1126 0.02362 0.01196 -0.0052 0.9629 0.0779
-1.250 -0.0611 0.02278 0.01104 -0.0094 0.9392 0.0827
-1.000 -0.0156 0.02198 0.01015 -0.0123 0.9156 0.0874
-0.750 0.0245 0.02126 0.00940 -0.0143 0.8930 0.0975
-0.250 0.1997 0.01743 0.00876 -0.0311 0.8516 1.0000
0.000 0.2279 0.01731 0.00838 -0.0309 0.8123 1.0000
0.250 0.2530 0.01725 0.00805 -0.0299 0.7737 1.0000
0.500 0.2756 0.01727 0.00777 -0.0283 0.7364 1.0000
0.750 0.2948 0.01736 0.00763 -0.0263 0.6957 1.0000
1.000 0.3137 0.01749 0.00751 -0.0242 0.6531 1.0000
1.250 0.3327 0.01766 0.00741 -0.0221 0.6093 1.0000
1.500 0.3519 0.01790 0.00732 -0.0201 0.5685 1.0000
1.750 0.3715 0.01821 0.00733 -0.0183 0.5297 1.0000
2.000 0.3916 0.01858 0.00742 -0.0167 0.4963 1.0000
2.250 0.4123 0.01897 0.00754 -0.0153 0.4697 1.0000
2.500 0.4338 0.01939 0.00776 -0.0141 0.4478 1.0000
2.750 0.4561 0.01984 0.00802 -0.0130 0.4292 1.0000
3.000 0.4793 0.02030 0.00833 -0.0122 0.4133 1.0000
3.250 0.5028 0.02079 0.00867 -0.0114 0.3998 1.0000
3.500 0.5267 0.02129 0.00907 -0.0106 0.3876 1.0000
3.750 0.5506 0.02180 0.00956 -0.0099 0.3759 1.0000
4.000 0.5743 0.02234 0.01001 -0.0092 0.3652 1.0000
4.250 0.5978 0.02288 0.01049 -0.0084 0.3544 1.0000
4.500 0.6210 0.02343 0.01107 -0.0076 0.3432 1.0000
4.750 0.6444 0.02400 0.01155 -0.0068 0.3332 1.0000
5.000 0.6674 0.02458 0.01217 -0.0060 0.3228 1.0000
5.250 0.6906 0.02522 0.01284 -0.0053 0.3137 1.0000
5.500 0.7138 0.02584 0.01347 -0.0045 0.3050 1.0000
5.750 0.7367 0.02656 0.01427 -0.0038 0.2966 1.0000
6.000 0.7599 0.02725 0.01498 -0.0030 0.2885 1.0000
6.250 0.7822 0.02806 0.01591 -0.0023 0.2803 1.0000
6.500 0.8051 0.02885 0.01675 -0.0016 0.2729 1.0000
6.750 0.8275 0.02979 0.01780 -0.0009 0.2661 1.0000
7.000 0.8490 0.03077 0.01896 -0.0001 0.2585 1.0000
7.250 0.8722 0.03163 0.01978 0.0006 0.2523 1.0000
7.500 0.8908 0.03287 0.02135 0.0015 0.2443 1.0000
7.750 0.9131 0.03382 0.02236 0.0022 0.2383 1.0000
8.000 0.9317 0.03524 0.02403 0.0031 0.2324 1.0000
8.250 0.9495 0.03662 0.02566 0.0040 0.2258 1.0000
8.500 0.9723 0.03749 0.02652 0.0047 0.2206 1.0000
8.750 0.9840 0.03945 0.02892 0.0059 0.2138 1.0000
9.000 1.0007 0.04082 0.03049 0.0069 0.2080 1.0000
9.250 1.0202 0.04187 0.03160 0.0078 0.2026 1.0000
9.500 1.0257 0.04411 0.03426 0.0093 0.1954 1.0000
9.750 1.0496 0.04428 0.03440 0.0101 0.1891 1.0000
10.000 1.0473 0.04691 0.03748 0.0119 0.1815 1.0000
10.250 1.0726 0.04625 0.03671 0.0129 0.1735 1.0000
10.500 1.0631 0.04929 0.04020 0.0149 0.1661 1.0000
10.750 1.0813 0.04906 0.03995 0.0162 0.1583 1.0000
11.000 1.0677 0.05228 0.04350 0.0180 0.1523 1.0000
11.250 1.0853 0.05196 0.04315 0.0194 0.1452 1.0000
11.500 1.0523 0.05684 0.04831 0.0211 0.1423 1.0000
11.750 1.0036 0.06486 0.05650 0.0190 0.1414 1.0000
12.000 0.8785 0.09070 0.08227 0.0027 0.1429 1.0000
12.250 0.8603 0.09803 0.08959 -0.0011 0.1366 1.0000
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Polar data table (+)
Polar graphs
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