BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Reynolds number: 50,000 Max Cl/Cd: 24.02 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v43012-il-50000.txt Download as CSV file: xf-v43012-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V43012-1.58 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4183 0.11155 0.10463 -0.0135 1.0000 0.2241
-9.500 -0.4121 0.10847 0.10162 -0.0124 1.0000 0.2402
-9.250 -0.4129 0.10591 0.09915 -0.0116 1.0000 0.2568
-9.000 -0.3804 0.10195 0.09517 -0.0078 1.0000 0.2867
-8.750 -0.3665 0.09916 0.09244 -0.0052 1.0000 0.3172
-8.500 -0.3567 0.09688 0.09023 -0.0026 1.0000 0.3521
-8.250 -0.3498 0.09488 0.08831 0.0002 1.0000 0.3883
-8.000 -0.3278 0.09194 0.08541 0.0034 1.0000 0.4304
-7.750 -0.3182 0.09025 0.08379 0.0068 1.0000 0.4751
-7.500 -0.2977 0.08782 0.08140 0.0103 1.0000 0.5275
-7.250 -0.2553 0.08395 0.07753 0.0125 1.0000 0.5942
-7.000 -0.2235 0.08100 0.07459 0.0147 1.0000 0.6656
-6.750 -0.1679 0.07566 0.06924 0.0130 1.0000 0.7450
-6.500 -0.1526 0.07292 0.06656 0.0132 1.0000 0.7750
-6.250 -0.1375 0.06994 0.06363 0.0127 1.0000 0.7923
-6.000 -0.1310 0.06792 0.06169 0.0135 1.0000 0.8071
-5.000 -0.2461 0.06156 0.05606 0.0240 1.0000 0.6526
-4.750 -0.3176 0.05955 0.05438 0.0281 1.0000 0.5890
-4.500 -0.3740 0.05783 0.05293 0.0339 1.0000 0.5696
-4.250 -0.4301 0.05475 0.05005 0.0358 1.0000 0.5374
-4.000 -0.4708 0.04768 0.04264 0.0243 1.0000 0.4492
-3.750 -0.4483 0.04120 0.03479 0.0113 1.0000 0.3378
-3.500 -0.4227 0.03853 0.03127 0.0094 1.0000 0.2872
-3.250 -0.3989 0.03691 0.02899 0.0096 1.0000 0.2537
-3.000 -0.3750 0.03625 0.02754 0.0106 1.0000 0.2242
-2.750 -0.3538 0.03529 0.02622 0.0117 1.0000 0.2068
-2.500 -0.3334 0.03495 0.02544 0.0131 1.0000 0.1913
-2.250 -0.3141 0.03362 0.02409 0.0139 1.0000 0.1823
-2.000 -0.2689 0.03338 0.02343 0.0109 0.9896 0.1715
-1.750 -0.1891 0.03243 0.02214 0.0023 0.9632 0.1626
-1.500 -0.1153 0.03178 0.02125 -0.0047 0.9386 0.1557
-1.250 -0.0414 0.03062 0.02011 -0.0116 0.9147 0.1525
-1.000 0.0357 0.02945 0.01887 -0.0187 0.8900 0.1571
-0.750 0.1051 0.02785 0.01733 -0.0243 0.8640 0.1624
-0.500 0.3680 0.02176 0.01410 -0.0569 0.8290 1.0000
-0.250 0.4034 0.02132 0.01312 -0.0559 0.7824 1.0000
0.000 0.4296 0.02115 0.01248 -0.0537 0.7366 1.0000
0.250 0.4499 0.02127 0.01220 -0.0509 0.6917 1.0000
0.500 0.4707 0.02153 0.01204 -0.0486 0.6521 1.0000
0.750 0.4906 0.02193 0.01209 -0.0464 0.6173 1.0000
1.000 0.5098 0.02242 0.01231 -0.0444 0.5872 1.0000
1.250 0.5294 0.02295 0.01258 -0.0427 0.5625 1.0000
1.500 0.5486 0.02354 0.01298 -0.0410 0.5407 1.0000
1.750 0.5683 0.02416 0.01343 -0.0394 0.5222 1.0000
2.000 0.5881 0.02485 0.01398 -0.0379 0.5069 1.0000
2.250 0.6084 0.02553 0.01451 -0.0365 0.4934 1.0000
2.500 0.6289 0.02618 0.01502 -0.0351 0.4807 1.0000
2.750 0.6464 0.02704 0.01588 -0.0335 0.4682 1.0000
3.000 0.6654 0.02791 0.01669 -0.0321 0.4581 1.0000
3.250 0.6856 0.02872 0.01742 -0.0307 0.4487 1.0000
3.500 0.7015 0.02985 0.01861 -0.0291 0.4394 1.0000
3.750 0.7234 0.03060 0.01920 -0.0279 0.4310 1.0000
4.000 0.7357 0.03202 0.02078 -0.0260 0.4222 1.0000
4.250 0.7574 0.03289 0.02154 -0.0248 0.4146 1.0000
4.500 0.7672 0.03455 0.02338 -0.0227 0.4067 1.0000
4.750 0.7866 0.03556 0.02433 -0.0213 0.3988 1.0000
5.000 0.7973 0.03731 0.02620 -0.0194 0.3920 1.0000
5.250 0.8068 0.03907 0.02809 -0.0174 0.3847 1.0000
5.500 0.8310 0.04001 0.02889 -0.0164 0.3781 1.0000
5.750 0.8234 0.04308 0.03232 -0.0134 0.3723 1.0000
6.000 0.8302 0.04521 0.03454 -0.0114 0.3665 1.0000
6.250 0.8519 0.04645 0.03570 -0.0104 0.3607 1.0000
6.500 0.8222 0.05142 0.04101 -0.0069 0.3568 1.0000
6.750 0.7834 0.05754 0.04731 -0.0043 0.3545 1.0000
7.000 0.7122 0.06692 0.05675 -0.0030 0.3573 1.0000
7.250 0.6625 0.07616 0.06595 -0.0056 0.3637 1.0000
7.500 0.4771 0.09876 0.08867 -0.0221 0.5235 1.0000
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Polar data table (+)
Polar graphs
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