BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Reynolds number: 100,000 Max Cl/Cd: 40.61 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v43012-il-100000-n5.txt Download as CSV file: xf-v43012-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3768 0.09650 0.09146 -0.0274 1.0000 0.0562
-9.250 -0.3891 0.09237 0.08741 -0.0319 1.0000 0.0570
-9.000 -0.4082 0.08829 0.08337 -0.0359 1.0000 0.0572
-8.750 -0.4324 0.08586 0.08094 -0.0351 1.0000 0.0573
-8.500 -0.4502 0.08343 0.07844 -0.0339 1.0000 0.0575
-8.000 -0.4414 0.07579 0.07095 -0.0316 1.0000 0.0584
-7.750 -0.4403 0.07283 0.06804 -0.0300 1.0000 0.0591
-7.500 -0.4425 0.07011 0.06532 -0.0281 1.0000 0.0598
-7.250 -0.4457 0.06752 0.06272 -0.0260 1.0000 0.0605
-7.000 -0.4490 0.06502 0.06017 -0.0238 1.0000 0.0613
-6.750 -0.4519 0.06261 0.05770 -0.0213 1.0000 0.0624
-6.500 -0.4542 0.06036 0.05534 -0.0186 1.0000 0.0636
-6.250 -0.4534 0.05958 0.05401 -0.0162 0.9973 0.0663
-6.000 -0.4278 0.05479 0.04909 -0.0188 0.9890 0.0674
-5.750 -0.3995 0.05068 0.04505 -0.0214 0.9818 0.0696
-5.500 -0.3698 0.04773 0.04188 -0.0234 0.9721 0.0734
-5.000 -0.3078 0.04039 0.03352 -0.0244 0.9501 0.0491
-4.750 -0.2763 0.03775 0.03061 -0.0255 0.9389 0.0486
-4.500 -0.2410 0.03528 0.02784 -0.0269 0.9282 0.0485
-4.250 -0.2103 0.03300 0.02529 -0.0272 0.9136 0.0472
-4.000 -0.1800 0.03093 0.02291 -0.0271 0.8977 0.0460
-3.750 -0.1487 0.02904 0.02069 -0.0270 0.8817 0.0451
-3.500 -0.1155 0.02755 0.01898 -0.0276 0.8647 0.0460
-3.250 -0.0808 0.02615 0.01733 -0.0282 0.8463 0.0472
-3.000 -0.0472 0.02476 0.01568 -0.0285 0.8251 0.0471
-2.750 -0.0163 0.02356 0.01427 -0.0283 0.8008 0.0471
-2.250 0.0476 0.02151 0.01179 -0.0282 0.7488 0.0477
-2.000 0.0771 0.02080 0.01084 -0.0278 0.7207 0.0493
-1.750 0.1046 0.02011 0.01002 -0.0271 0.6922 0.0505
-1.500 0.1313 0.01947 0.00930 -0.0264 0.6659 0.0513
-1.250 0.1565 0.01892 0.00870 -0.0255 0.6398 0.0521
-1.000 0.1800 0.01847 0.00816 -0.0242 0.6145 0.0533
-0.750 0.2023 0.01811 0.00770 -0.0227 0.5883 0.0545
-0.500 0.2243 0.01788 0.00727 -0.0212 0.5623 0.0567
-0.250 0.2462 0.01767 0.00693 -0.0198 0.5348 0.0597
0.000 0.2685 0.01755 0.00663 -0.0184 0.5062 0.0633
0.250 0.2911 0.01746 0.00633 -0.0171 0.4750 0.0670
0.500 0.3138 0.01739 0.00606 -0.0159 0.4446 0.0729
0.750 0.3366 0.01738 0.00581 -0.0147 0.4210 0.0855
1.000 0.3580 0.01665 0.00557 -0.0137 0.4019 0.3223
1.250 0.4949 0.01610 0.00661 -0.0332 0.3601 0.9860
1.500 0.5485 0.01636 0.00660 -0.0387 0.3411 1.0000
1.750 0.5679 0.01656 0.00666 -0.0372 0.3301 1.0000
2.250 0.6068 0.01703 0.00688 -0.0342 0.3131 1.0000
2.500 0.6261 0.01731 0.00702 -0.0326 0.3062 1.0000
2.750 0.6459 0.01758 0.00720 -0.0312 0.2994 1.0000
3.000 0.6656 0.01787 0.00740 -0.0297 0.2930 1.0000
3.250 0.6851 0.01822 0.00760 -0.0283 0.2876 1.0000
3.500 0.7055 0.01851 0.00788 -0.0269 0.2817 1.0000
3.750 0.7255 0.01885 0.00814 -0.0255 0.2764 1.0000
4.000 0.7453 0.01926 0.00840 -0.0241 0.2714 1.0000
4.250 0.7655 0.01958 0.00874 -0.0228 0.2653 1.0000
4.500 0.7854 0.01993 0.00905 -0.0214 0.2596 1.0000
4.750 0.8055 0.02037 0.00937 -0.0201 0.2550 1.0000
5.000 0.8259 0.02075 0.00978 -0.0188 0.2502 1.0000
5.250 0.8463 0.02114 0.01020 -0.0175 0.2456 1.0000
5.500 0.8668 0.02156 0.01060 -0.0163 0.2416 1.0000
5.750 0.8875 0.02205 0.01100 -0.0151 0.2381 1.0000
6.000 0.9078 0.02249 0.01151 -0.0139 0.2341 1.0000
6.250 0.9278 0.02292 0.01202 -0.0126 0.2298 1.0000
6.500 0.9479 0.02337 0.01248 -0.0114 0.2259 1.0000
6.750 0.9682 0.02384 0.01290 -0.0102 0.2225 1.0000
7.000 0.9878 0.02435 0.01349 -0.0089 0.2189 1.0000
7.250 1.0072 0.02487 0.01413 -0.0076 0.2150 1.0000
7.500 1.0267 0.02539 0.01469 -0.0064 0.2116 1.0000
7.750 1.0466 0.02590 0.01520 -0.0052 0.2086 1.0000
8.000 1.0668 0.02648 0.01575 -0.0042 0.2059 1.0000
8.250 1.0845 0.02715 0.01663 -0.0027 0.2025 1.0000
8.500 1.1027 0.02782 0.01741 -0.0014 0.1991 1.0000
8.750 1.1212 0.02845 0.01811 -0.0002 0.1962 1.0000
9.000 1.1404 0.02908 0.01877 0.0010 0.1936 1.0000
9.250 1.1606 0.02975 0.01942 0.0019 0.1914 1.0000
9.500 1.1759 0.03067 0.02053 0.0034 0.1887 1.0000
9.750 1.1901 0.03158 0.02165 0.0051 0.1856 1.0000
10.000 1.2049 0.03243 0.02264 0.0066 0.1828 1.0000
10.250 1.2206 0.03322 0.02352 0.0080 0.1803 1.0000
10.500 1.2375 0.03399 0.02433 0.0093 0.1782 1.0000
10.750 1.2560 0.03481 0.02517 0.0102 0.1764 1.0000
11.000 1.2676 0.03599 0.02652 0.0119 0.1745 1.0000
11.250 1.2727 0.03740 0.02820 0.0143 0.1725 1.0000
11.500 1.2769 0.03882 0.02986 0.0167 0.1706 1.0000
11.750 1.2790 0.04022 0.03145 0.0194 0.1688 1.0000
12.000 1.2808 0.04166 0.03305 0.0220 0.1672 1.0000
12.250 1.2829 0.04314 0.03469 0.0242 0.1658 1.0000
12.500 1.2872 0.04455 0.03621 0.0260 0.1644 1.0000
12.750 1.2951 0.04581 0.03756 0.0274 0.1630 1.0000
13.000 1.3099 0.04681 0.03859 0.0282 0.1616 1.0000
13.250 1.3008 0.04920 0.04117 0.0301 0.1603 1.0000
13.500 1.2644 0.05372 0.04601 0.0319 0.1591 1.0000
13.750 1.1855 0.06365 0.05631 0.0302 0.1577 1.0000
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Polar data table (+)
Polar graphs
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