BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Reynolds number: 100,000 Max Cl/Cd: 39.83 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v43015-il-100000-n5.txt Download as CSV file: xf-v43015-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V43015-2.48 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3987 0.09606 0.09077 -0.0427 1.0000 0.0727
-10.500 -0.4147 0.09047 0.08522 -0.0464 1.0000 0.0727
-10.250 -0.4508 0.08532 0.08004 -0.0495 1.0000 0.0729
-10.000 -0.4690 0.08207 0.07679 -0.0487 1.0000 0.0728
-9.500 -0.5335 0.07177 0.06624 -0.0417 1.0000 0.0518
-9.250 -0.5326 0.06945 0.06398 -0.0394 1.0000 0.0513
-9.000 -0.5457 0.06720 0.06171 -0.0357 1.0000 0.0509
-8.750 -0.5593 0.06499 0.05945 -0.0317 1.0000 0.0504
-8.500 -0.5725 0.06275 0.05714 -0.0276 1.0000 0.0497
-8.000 -0.6026 0.05603 0.04973 -0.0190 0.9967 0.0461
-7.750 -0.5816 0.05268 0.04616 -0.0202 0.9894 0.0458
-7.500 -0.5587 0.04947 0.04266 -0.0214 0.9823 0.0456
-7.250 -0.5407 0.04628 0.03895 -0.0211 0.9727 0.0463
-7.000 -0.5143 0.04412 0.03674 -0.0221 0.9649 0.0471
-6.750 -0.4856 0.04166 0.03402 -0.0232 0.9572 0.0474
-6.500 -0.4617 0.03924 0.03125 -0.0229 0.9468 0.0472
-6.250 -0.4274 0.03683 0.02851 -0.0243 0.9400 0.0472
-6.000 -0.4021 0.03498 0.02643 -0.0238 0.9281 0.0474
-5.750 -0.3669 0.03328 0.02454 -0.0252 0.9202 0.0485
-5.500 -0.3376 0.03179 0.02284 -0.0253 0.9090 0.0497
-5.250 -0.3052 0.03021 0.02101 -0.0257 0.8992 0.0505
-5.000 -0.2718 0.02868 0.01926 -0.0262 0.8889 0.0509
-4.750 -0.2410 0.02735 0.01774 -0.0262 0.8769 0.0513
-4.500 -0.2024 0.02595 0.01615 -0.0275 0.8674 0.0520
-4.250 -0.1727 0.02498 0.01523 -0.0276 0.8528 0.0531
-4.000 -0.1402 0.02410 0.01434 -0.0281 0.8386 0.0548
-3.750 -0.1051 0.02315 0.01331 -0.0289 0.8240 0.0566
-3.500 -0.0697 0.02219 0.01227 -0.0296 0.8083 0.0578
-3.250 -0.0380 0.02133 0.01142 -0.0298 0.7885 0.0589
-3.000 -0.0098 0.02064 0.01073 -0.0293 0.7646 0.0605
-2.750 0.0169 0.02008 0.01011 -0.0285 0.7384 0.0631
-2.500 0.0423 0.01959 0.00949 -0.0274 0.7120 0.0658
-2.250 0.0640 0.01918 0.00902 -0.0258 0.6855 0.0684
-2.000 0.0858 0.01884 0.00853 -0.0242 0.6602 0.0713
-1.750 0.1073 0.01855 0.00808 -0.0226 0.6359 0.0745
-1.500 0.1291 0.01832 0.00770 -0.0210 0.6117 0.0801
-1.250 0.1503 0.01809 0.00734 -0.0194 0.5877 0.0870
-1.000 0.1718 0.01787 0.00698 -0.0179 0.5645 0.0974
-0.750 0.1929 0.01759 0.00663 -0.0163 0.5420 0.1190
-0.500 0.1971 0.01552 0.00649 -0.0121 0.5244 0.5998
-0.250 0.2347 0.01542 0.00696 -0.0123 0.5001 0.7914
0.000 0.2899 0.01611 0.00759 -0.0158 0.4745 0.8707
0.250 0.3321 0.01662 0.00790 -0.0177 0.4532 0.8953
0.500 0.3719 0.01707 0.00813 -0.0194 0.4336 0.9124
0.750 0.4123 0.01751 0.00836 -0.0214 0.4152 0.9279
1.000 0.4485 0.01788 0.00853 -0.0228 0.3993 0.9414
1.250 0.4874 0.01814 0.00863 -0.0250 0.3843 0.9486
1.500 0.5185 0.01837 0.00874 -0.0258 0.3716 0.9575
1.750 0.5549 0.01863 0.00882 -0.0277 0.3594 0.9642
2.000 0.5879 0.01886 0.00895 -0.0289 0.3475 0.9720
2.250 0.6240 0.01910 0.00907 -0.0308 0.3368 0.9787
2.500 0.6592 0.01934 0.00919 -0.0326 0.3272 0.9853
2.750 0.6952 0.01957 0.00934 -0.0345 0.3179 0.9917
3.000 0.7316 0.01979 0.00946 -0.0366 0.3092 0.9976
3.250 0.7569 0.02004 0.00962 -0.0365 0.3024 1.0000
3.500 0.7736 0.02027 0.00984 -0.0347 0.2961 1.0000
3.750 0.7899 0.02053 0.01003 -0.0328 0.2907 1.0000
4.000 0.8065 0.02082 0.01025 -0.0309 0.2855 1.0000
4.250 0.8232 0.02109 0.01054 -0.0290 0.2795 1.0000
4.500 0.8396 0.02139 0.01078 -0.0271 0.2744 1.0000
4.750 0.8561 0.02174 0.01102 -0.0252 0.2700 1.0000
5.000 0.8729 0.02206 0.01141 -0.0233 0.2649 1.0000
5.250 0.8895 0.02241 0.01175 -0.0214 0.2602 1.0000
5.500 0.9060 0.02277 0.01206 -0.0195 0.2561 1.0000
5.750 0.9231 0.02319 0.01241 -0.0177 0.2525 1.0000
6.000 0.9396 0.02359 0.01289 -0.0159 0.2482 1.0000
6.250 0.9561 0.02401 0.01333 -0.0140 0.2443 1.0000
6.500 0.9727 0.02443 0.01373 -0.0122 0.2408 1.0000
6.750 0.9899 0.02489 0.01412 -0.0105 0.2376 1.0000
7.000 1.0059 0.02539 0.01468 -0.0086 0.2339 1.0000
7.250 1.0213 0.02589 0.01525 -0.0066 0.2301 1.0000
7.500 1.0370 0.02639 0.01577 -0.0047 0.2266 1.0000
7.750 1.0534 0.02689 0.01626 -0.0030 0.2236 1.0000
8.000 1.0712 0.02745 0.01676 -0.0015 0.2209 1.0000
8.250 1.0857 0.02808 0.01750 0.0005 0.2179 1.0000
8.500 1.0993 0.02873 0.01826 0.0026 0.2148 1.0000
8.750 1.1133 0.02936 0.01897 0.0046 0.2117 1.0000
9.000 1.1279 0.02997 0.01960 0.0064 0.2089 1.0000
9.250 1.1437 0.03056 0.02017 0.0081 0.2063 1.0000
9.500 1.1606 0.03125 0.02083 0.0095 0.2038 1.0000
9.750 1.1673 0.03208 0.02186 0.0124 0.2009 1.0000
10.000 1.1753 0.03292 0.02283 0.0150 0.1983 1.0000
10.250 1.1834 0.03372 0.02372 0.0177 0.1958 1.0000
10.500 1.1929 0.03449 0.02456 0.0200 0.1936 1.0000
10.750 1.2050 0.03523 0.02533 0.0219 0.1915 1.0000
11.000 1.2205 0.03599 0.02607 0.0233 0.1896 1.0000
11.250 1.2276 0.03703 0.02720 0.0256 0.1877 1.0000
11.500 1.2234 0.03837 0.02877 0.0290 0.1854 1.0000
11.750 1.2216 0.03977 0.03035 0.0318 0.1832 1.0000
12.000 1.2216 0.04118 0.03189 0.0341 0.1810 1.0000
12.250 1.2248 0.04254 0.03336 0.0359 0.1791 1.0000
12.500 1.2310 0.04383 0.03472 0.0373 0.1774 1.0000
12.750 1.2422 0.04489 0.03580 0.0384 0.1757 1.0000
13.000 1.2604 0.04570 0.03658 0.0389 0.1741 1.0000
13.250 1.2331 0.04911 0.04031 0.0413 0.1724 1.0000
13.500 1.2015 0.05349 0.04498 0.0426 0.1705 1.0000
13.750 1.1555 0.06002 0.05181 0.0422 0.1686 1.0000
14.000 0.9098 0.09827 0.09055 0.0251 0.1598 1.0000
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Polar data table (+)
Polar graphs
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