BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Reynolds number: 50,000 Max Cl/Cd: 28.05 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v13006-il-50000-n5.txt Download as CSV file: xf-v13006-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V13006-.7 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6407 0.12163 0.11453 0.0244 1.0000 0.1056
-9.250 -0.6531 0.11932 0.11236 0.0185 1.0000 0.1085
-9.000 -0.6514 0.11484 0.10793 0.0165 1.0000 0.1097
-8.750 -0.6348 0.10994 0.10298 0.0192 1.0000 0.1129
-8.500 -0.6300 0.10617 0.09924 0.0182 1.0000 0.1163
-8.250 -0.6350 0.10276 0.09591 0.0140 1.0000 0.1215
-8.000 -0.6444 0.09861 0.09187 0.0063 1.0000 0.1243
-7.750 -0.6288 0.09433 0.08759 0.0102 1.0000 0.1278
-7.500 -0.6238 0.09040 0.08368 0.0077 1.0000 0.1337
-7.250 -0.6226 0.08598 0.07928 0.0035 1.0000 0.1412
-7.000 -0.6141 0.08222 0.07550 0.0023 1.0000 0.1491
-6.750 -0.5931 0.07068 0.06333 -0.0108 1.0000 0.0655
-6.500 -0.5808 0.06637 0.05898 -0.0112 1.0000 0.0635
-6.250 -0.5674 0.06192 0.05438 -0.0125 1.0000 0.0610
-5.750 -0.5322 0.05253 0.04408 -0.0154 1.0000 0.0522
-5.500 -0.5143 0.04874 0.04007 -0.0156 1.0000 0.0510
-5.250 -0.4946 0.04514 0.03612 -0.0157 1.0000 0.0500
-5.000 -0.4734 0.04176 0.03235 -0.0156 1.0000 0.0491
-4.750 -0.4509 0.03861 0.02877 -0.0153 1.0000 0.0484
-4.500 -0.4272 0.03573 0.02545 -0.0148 1.0000 0.0481
-4.250 -0.4026 0.03322 0.02249 -0.0143 1.0000 0.0491
-4.000 -0.3770 0.03107 0.01985 -0.0136 1.0000 0.0514
-3.750 -0.3506 0.02913 0.01740 -0.0128 1.0000 0.0529
-3.500 -0.3243 0.02714 0.01513 -0.0121 1.0000 0.0537
-3.250 -0.2984 0.02521 0.01310 -0.0114 1.0000 0.0553
-3.000 -0.2723 0.02370 0.01149 -0.0106 1.0000 0.0577
-2.750 -0.2461 0.02253 0.01019 -0.0098 1.0000 0.0637
-2.500 -0.2198 0.02136 0.00890 -0.0092 1.0000 0.0702
-2.250 -0.1949 0.02035 0.00778 -0.0083 1.0000 0.0770
-2.000 -0.1704 0.01944 0.00683 -0.0076 1.0000 0.0927
-1.750 -0.1458 0.01836 0.00586 -0.0069 1.0000 0.1200
-1.500 -0.0835 0.01443 0.00502 -0.0115 1.0000 1.0000
-1.250 -0.0619 0.01436 0.00463 -0.0103 1.0000 1.0000
-1.000 -0.0403 0.01431 0.00433 -0.0093 1.0000 1.0000
-0.750 -0.0186 0.01427 0.00411 -0.0082 1.0000 1.0000
-0.500 0.0030 0.01426 0.00393 -0.0071 1.0000 1.0000
-0.250 0.0247 0.01426 0.00381 -0.0061 1.0000 1.0000
0.000 0.0463 0.01429 0.00375 -0.0051 1.0000 1.0000
0.250 0.0679 0.01433 0.00374 -0.0041 1.0000 1.0000
0.500 0.0895 0.01440 0.00377 -0.0032 1.0000 1.0000
0.750 0.1112 0.01449 0.00385 -0.0023 1.0000 1.0000
1.000 0.1327 0.01461 0.00399 -0.0015 1.0000 1.0000
1.250 0.1540 0.01476 0.00419 -0.0007 1.0000 1.0000
1.500 0.1751 0.01495 0.00446 0.0000 1.0000 1.0000
1.750 0.2184 0.01520 0.00483 -0.0037 0.9799 1.0000
2.000 0.2745 0.01537 0.00519 -0.0094 0.9401 1.0000
2.250 0.3223 0.01545 0.00546 -0.0127 0.8861 1.0000
2.500 0.3620 0.01554 0.00564 -0.0140 0.8232 1.0000
2.750 0.3929 0.01573 0.00580 -0.0132 0.7553 1.0000
3.000 0.4181 0.01604 0.00600 -0.0115 0.6865 1.0000
3.250 0.4410 0.01648 0.00630 -0.0095 0.6188 1.0000
3.500 0.4636 0.01702 0.00667 -0.0078 0.5553 1.0000
3.750 0.4865 0.01763 0.00714 -0.0063 0.4988 1.0000
4.000 0.5100 0.01829 0.00772 -0.0052 0.4509 1.0000
4.250 0.5327 0.01899 0.00834 -0.0040 0.3986 1.0000
4.500 0.5525 0.01975 0.00869 -0.0027 0.3136 1.0000
4.750 0.5744 0.02064 0.00928 -0.0020 0.2203 1.0000
5.000 0.5965 0.02242 0.01024 -0.0018 0.0968 1.0000
5.250 0.6195 0.02418 0.01179 -0.0012 0.0731 1.0000
5.500 0.6422 0.02574 0.01346 -0.0005 0.0638 1.0000
5.750 0.6654 0.02717 0.01510 0.0004 0.0572 1.0000
6.000 0.6871 0.02882 0.01677 0.0011 0.0522 1.0000
6.250 0.7105 0.03055 0.01877 0.0021 0.0497 1.0000
6.500 0.7339 0.03255 0.02108 0.0031 0.0480 1.0000
6.750 0.7568 0.03485 0.02377 0.0039 0.0467 1.0000
7.000 0.7786 0.03747 0.02682 0.0047 0.0457 1.0000
7.250 0.7985 0.04048 0.03029 0.0054 0.0451 1.0000
7.500 0.8159 0.04386 0.03418 0.0061 0.0445 1.0000
7.750 0.8305 0.04741 0.03819 0.0065 0.0436 1.0000
8.000 0.8428 0.05092 0.04207 0.0068 0.0424 1.0000
8.250 0.8524 0.05464 0.04610 0.0069 0.0413 1.0000
8.500 0.8581 0.05884 0.05065 0.0068 0.0406 1.0000
8.750 0.8591 0.06354 0.05569 0.0063 0.0403 1.0000
9.000 0.8540 0.06875 0.06124 0.0050 0.0406 1.0000
9.250 0.8394 0.07505 0.06785 0.0020 0.0412 1.0000
9.500 0.8057 0.08590 0.07881 -0.0077 0.0432 1.0000
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Polar data table (+)
Polar graphs
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