BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Reynolds number: 100,000 Max Cl/Cd: 39.9 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr12-il-100000-n5.txt Download as CSV file: xf-vr12-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-12 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3605 0.09837 0.09380 -0.0204 1.0000 0.0513
-9.500 -0.3693 0.09107 0.08648 -0.0231 1.0000 0.0358
-9.000 -0.4913 0.08640 0.08163 -0.0247 1.0000 0.0305
-8.750 -0.4924 0.08182 0.07709 -0.0280 1.0000 0.0302
-8.500 -0.4975 0.07716 0.07243 -0.0306 1.0000 0.0298
-8.250 -0.5037 0.07254 0.06777 -0.0324 1.0000 0.0295
-8.000 -0.5092 0.06766 0.06280 -0.0337 1.0000 0.0295
-7.750 -0.5156 0.06274 0.05773 -0.0340 1.0000 0.0298
-7.500 -0.5244 0.05814 0.05289 -0.0324 1.0000 0.0303
-7.250 -0.5365 0.05421 0.04868 -0.0288 1.0000 0.0306
-7.000 -0.5465 0.05079 0.04492 -0.0246 1.0000 0.0309
-6.500 -0.5256 0.04447 0.03822 -0.0228 0.9934 0.0317
-6.250 -0.5031 0.04137 0.03483 -0.0236 0.9872 0.0324
-6.000 -0.4774 0.03884 0.03198 -0.0246 0.9820 0.0345
-5.750 -0.4533 0.03567 0.02823 -0.0247 0.9759 0.0365
-5.500 -0.4248 0.03257 0.02451 -0.0252 0.9719 0.0374
-5.250 -0.3991 0.03032 0.02183 -0.0252 0.9660 0.0393
-5.000 -0.3688 0.02887 0.02028 -0.0262 0.9615 0.0414
-4.750 -0.3368 0.02713 0.01821 -0.0271 0.9577 0.0428
-4.500 -0.3092 0.02573 0.01653 -0.0269 0.9515 0.0443
-4.250 -0.2768 0.02466 0.01512 -0.0276 0.9470 0.0471
-4.000 -0.2461 0.02330 0.01363 -0.0281 0.9423 0.0488
-3.750 -0.2179 0.02228 0.01260 -0.0282 0.9362 0.0504
-3.500 -0.1861 0.02150 0.01179 -0.0290 0.9317 0.0537
-3.250 -0.1588 0.02083 0.01105 -0.0288 0.9256 0.0565
-3.000 -0.1308 0.02018 0.01033 -0.0286 0.9197 0.0584
-2.750 -0.1020 0.01942 0.00962 -0.0288 0.9154 0.0613
-2.500 -0.0791 0.01903 0.00924 -0.0278 0.9079 0.0659
-2.250 -0.0514 0.01863 0.00876 -0.0276 0.9025 0.0708
-2.000 -0.0254 0.01820 0.00835 -0.0271 0.8963 0.0771
-1.750 0.0009 0.01777 0.00794 -0.0264 0.8877 0.0893
-1.500 0.0253 0.01696 0.00752 -0.0254 0.8769 0.1653
-1.250 0.1877 0.01468 0.00784 -0.0484 0.8731 1.0000
-1.000 0.2079 0.01453 0.00752 -0.0466 0.8576 1.0000
-0.750 0.2286 0.01438 0.00723 -0.0448 0.8422 1.0000
-0.500 0.2500 0.01426 0.00697 -0.0432 0.8274 1.0000
-0.250 0.2722 0.01416 0.00675 -0.0418 0.8136 1.0000
0.000 0.2946 0.01406 0.00655 -0.0405 0.7996 1.0000
0.250 0.3171 0.01398 0.00636 -0.0391 0.7849 1.0000
0.500 0.3399 0.01390 0.00618 -0.0377 0.7689 1.0000
0.750 0.3627 0.01385 0.00603 -0.0364 0.7509 1.0000
1.000 0.3856 0.01380 0.00589 -0.0351 0.7311 1.0000
1.250 0.4087 0.01378 0.00578 -0.0339 0.7072 1.0000
1.500 0.4316 0.01376 0.00565 -0.0326 0.6774 1.0000
1.750 0.4544 0.01377 0.00552 -0.0312 0.6383 1.0000
2.000 0.4764 0.01385 0.00533 -0.0295 0.5799 1.0000
2.250 0.4974 0.01417 0.00518 -0.0279 0.5031 1.0000
2.500 0.5183 0.01470 0.00524 -0.0265 0.4351 1.0000
2.750 0.5398 0.01524 0.00544 -0.0255 0.3830 1.0000
3.000 0.5616 0.01574 0.00567 -0.0246 0.3484 1.0000
3.250 0.5836 0.01619 0.00593 -0.0237 0.3245 1.0000
3.500 0.6060 0.01661 0.00621 -0.0228 0.3058 1.0000
3.750 0.6284 0.01702 0.00651 -0.0219 0.2908 1.0000
4.000 0.6506 0.01745 0.00681 -0.0210 0.2783 1.0000
4.250 0.6732 0.01784 0.00714 -0.0202 0.2671 1.0000
4.500 0.6956 0.01824 0.00751 -0.0193 0.2572 1.0000
4.750 0.7176 0.01870 0.00786 -0.0184 0.2485 1.0000
5.000 0.7403 0.01908 0.00825 -0.0175 0.2399 1.0000
5.250 0.7623 0.01956 0.00865 -0.0166 0.2333 1.0000
5.500 0.7850 0.01999 0.00912 -0.0157 0.2265 1.0000
5.750 0.8072 0.02045 0.00956 -0.0149 0.2204 1.0000
6.000 0.8294 0.02096 0.01004 -0.0140 0.2150 1.0000
6.250 0.8519 0.02143 0.01058 -0.0131 0.2089 1.0000
6.500 0.8737 0.02194 0.01106 -0.0123 0.2037 1.0000
6.750 0.8959 0.02248 0.01163 -0.0114 0.1987 1.0000
7.000 0.9181 0.02301 0.01224 -0.0106 0.1939 1.0000
7.250 0.9401 0.02358 0.01283 -0.0097 0.1899 1.0000
7.500 0.9622 0.02423 0.01346 -0.0089 0.1865 1.0000
7.750 0.9842 0.02486 0.01424 -0.0081 0.1824 1.0000
8.000 1.0057 0.02547 0.01497 -0.0072 0.1782 1.0000
8.250 1.0270 0.02609 0.01559 -0.0063 0.1744 1.0000
8.500 1.0481 0.02679 0.01635 -0.0055 0.1708 1.0000
8.750 1.0682 0.02745 0.01721 -0.0044 0.1661 1.0000
9.000 1.0877 0.02800 0.01784 -0.0033 0.1613 1.0000
9.250 1.1071 0.02862 0.01843 -0.0023 0.1572 1.0000
9.500 1.1253 0.02934 0.01941 -0.0011 0.1525 1.0000
9.750 1.1437 0.03002 0.02022 0.0000 0.1484 1.0000
10.000 1.1624 0.03070 0.02094 0.0011 0.1451 1.0000
10.250 1.1803 0.03159 0.02198 0.0023 0.1419 1.0000
10.500 1.1964 0.03254 0.02319 0.0036 0.1380 1.0000
10.750 1.2125 0.03339 0.02418 0.0049 0.1344 1.0000
11.000 1.2288 0.03411 0.02496 0.0062 0.1312 1.0000
11.250 1.2418 0.03516 0.02621 0.0078 0.1275 1.0000
11.500 1.2524 0.03619 0.02749 0.0097 0.1231 1.0000
11.750 1.2636 0.03692 0.02831 0.0114 0.1192 1.0000
12.000 1.2737 0.03778 0.02920 0.0133 0.1158 1.0000
12.500 1.2788 0.04021 0.03211 0.0183 0.1078 1.0000
12.750 1.2843 0.04116 0.03309 0.0203 0.1047 1.0000
13.000 1.2847 0.04288 0.03502 0.0222 0.1014 1.0000
13.250 1.2827 0.04487 0.03727 0.0239 0.0978 1.0000
13.500 1.2828 0.04667 0.03921 0.0252 0.0948 1.0000
13.750 1.2844 0.04834 0.04092 0.0262 0.0922 1.0000
14.000 1.2789 0.05105 0.04384 0.0270 0.0896 1.0000
14.250 1.2679 0.05460 0.04767 0.0273 0.0869 1.0000
14.500 1.2572 0.05825 0.05153 0.0270 0.0845 1.0000
14.750 1.2478 0.06195 0.05538 0.0263 0.0824 1.0000
15.000 1.2403 0.06556 0.05908 0.0254 0.0806 1.0000
15.250 1.2266 0.07037 0.06399 0.0237 0.0791 1.0000
15.500 1.1919 0.07912 0.07303 0.0194 0.0784 1.0000
15.750 1.1368 0.09271 0.08686 0.0116 0.0783 1.0000
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Polar data table (+)
Polar graphs
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