BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Reynolds number: 200,000 Max Cl/Cd: 49.24 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr12-il-200000.txt Download as CSV file: xf-vr12-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4759 0.08912 0.08585 -0.0167 1.0000 0.0416
-8.500 -0.4758 0.08462 0.08139 -0.0204 1.0000 0.0426
-8.250 -0.4801 0.07942 0.07622 -0.0259 1.0000 0.0434
-8.000 -0.4854 0.07463 0.07140 -0.0295 1.0000 0.0444
-7.750 -0.4915 0.06926 0.06590 -0.0334 1.0000 0.0463
-7.500 -0.5142 0.06651 0.06281 -0.0316 1.0000 0.0474
-7.250 -0.5298 0.06505 0.06118 -0.0268 1.0000 0.0475
-7.000 -0.5470 0.06134 0.05737 -0.0226 1.0000 0.0479
-6.750 -0.5469 0.05726 0.05347 -0.0204 1.0000 0.0488
-6.500 -0.5260 0.05442 0.05067 -0.0217 0.9969 0.0506
-6.250 -0.4982 0.05342 0.04886 -0.0236 0.9904 0.0587
-6.000 -0.4236 0.03271 0.02886 -0.0333 0.9780 0.0649
-5.750 -0.4059 0.02789 0.02352 -0.0343 0.9731 0.0736
-5.500 -0.3793 0.02556 0.02124 -0.0356 0.9694 0.0802
-5.250 -0.4031 0.03784 0.03271 -0.0297 0.9735 0.0876
-5.000 -0.3719 0.03552 0.03040 -0.0315 0.9704 0.0946
-4.750 -0.3482 0.03320 0.02787 -0.0317 0.9644 0.1059
-4.500 -0.3089 0.02709 0.02010 -0.0289 0.9608 0.0590
-4.250 -0.2729 0.02364 0.01641 -0.0306 0.9589 0.0570
-4.000 -0.2453 0.02255 0.01504 -0.0302 0.9528 0.0580
-3.750 -0.2114 0.02103 0.01331 -0.0311 0.9490 0.0581
-3.500 -0.1751 0.01983 0.01193 -0.0324 0.9461 0.0591
-3.250 -0.1459 0.01836 0.01048 -0.0327 0.9413 0.0619
-3.000 -0.1163 0.01760 0.00971 -0.0329 0.9355 0.0638
-2.750 -0.0814 0.01683 0.00894 -0.0338 0.9306 0.0665
-2.500 -0.0569 0.01633 0.00842 -0.0326 0.9198 0.0698
-2.250 -0.0319 0.01570 0.00777 -0.0312 0.9102 0.0722
-2.000 -0.0094 0.01499 0.00710 -0.0294 0.9012 0.0763
-1.750 0.0127 0.01460 0.00672 -0.0277 0.8911 0.0826
-1.500 0.0350 0.01408 0.00620 -0.0257 0.8835 0.0945
-1.250 0.0496 0.01274 0.00574 -0.0230 0.8727 0.2987
-1.000 0.1428 0.01130 0.00644 -0.0330 0.8700 0.9722
-0.750 0.2252 0.01129 0.00627 -0.0435 0.8625 1.0000
-0.500 0.2450 0.01113 0.00599 -0.0415 0.8528 1.0000
-0.250 0.2677 0.01100 0.00578 -0.0403 0.8406 1.0000
0.000 0.2902 0.01088 0.00557 -0.0390 0.8287 1.0000
0.250 0.3127 0.01075 0.00535 -0.0376 0.8166 1.0000
0.500 0.3353 0.01061 0.00513 -0.0362 0.8037 1.0000
0.750 0.3583 0.01050 0.00492 -0.0348 0.7892 1.0000
1.000 0.3820 0.01040 0.00474 -0.0336 0.7728 1.0000
1.250 0.4061 0.01032 0.00459 -0.0325 0.7537 1.0000
1.500 0.4302 0.01025 0.00443 -0.0314 0.7316 1.0000
1.750 0.4547 0.01020 0.00430 -0.0305 0.7036 1.0000
2.000 0.4788 0.01018 0.00413 -0.0294 0.6645 1.0000
2.250 0.5023 0.01031 0.00394 -0.0281 0.5920 1.0000
2.500 0.5243 0.01095 0.00389 -0.0270 0.4722 1.0000
3.000 0.5698 0.01227 0.00437 -0.0258 0.3472 1.0000
3.250 0.5931 0.01275 0.00464 -0.0252 0.3221 1.0000
3.500 0.6166 0.01316 0.00491 -0.0245 0.3040 1.0000
3.750 0.6400 0.01357 0.00520 -0.0239 0.2897 1.0000
4.000 0.6632 0.01400 0.00550 -0.0231 0.2777 1.0000
4.250 0.6866 0.01436 0.00580 -0.0224 0.2668 1.0000
4.500 0.7100 0.01476 0.00615 -0.0217 0.2572 1.0000
4.750 0.7328 0.01523 0.00650 -0.0209 0.2486 1.0000
5.000 0.7564 0.01554 0.00684 -0.0202 0.2401 1.0000
5.250 0.7791 0.01606 0.00723 -0.0194 0.2329 1.0000
5.500 0.8026 0.01638 0.00762 -0.0186 0.2261 1.0000
5.750 0.8257 0.01680 0.00799 -0.0179 0.2201 1.0000
6.000 0.8488 0.01732 0.00850 -0.0171 0.2147 1.0000
6.250 0.8721 0.01771 0.00895 -0.0163 0.2093 1.0000
6.500 0.8952 0.01819 0.00938 -0.0156 0.2046 1.0000
6.750 0.9185 0.01882 0.01000 -0.0149 0.2004 1.0000
7.000 0.9413 0.01921 0.01050 -0.0141 0.1955 1.0000
7.250 0.9640 0.01961 0.01089 -0.0133 0.1907 1.0000
7.500 0.9869 0.02027 0.01150 -0.0127 0.1862 1.0000
7.750 1.0086 0.02062 0.01200 -0.0117 0.1815 1.0000
8.000 1.0308 0.02102 0.01244 -0.0108 0.1771 1.0000
8.250 1.0537 0.02164 0.01300 -0.0102 0.1734 1.0000
8.500 1.0758 0.02230 0.01378 -0.0094 0.1701 1.0000
8.750 1.0972 0.02281 0.01445 -0.0084 0.1665 1.0000
9.000 1.1188 0.02332 0.01502 -0.0076 0.1629 1.0000
9.250 1.1412 0.02392 0.01560 -0.0069 0.1596 1.0000
9.500 1.1625 0.02478 0.01655 -0.0061 0.1563 1.0000
9.750 1.1817 0.02533 0.01732 -0.0049 0.1525 1.0000
10.000 1.2015 0.02579 0.01786 -0.0038 0.1485 1.0000
10.250 1.2229 0.02643 0.01840 -0.0031 0.1443 1.0000
10.500 1.2386 0.02697 0.01920 -0.0014 0.1398 1.0000
10.750 1.2553 0.02730 0.01964 0.0001 0.1350 1.0000
11.000 1.2750 0.02786 0.02009 0.0010 0.1305 1.0000
11.250 1.2878 0.02851 0.02102 0.0030 0.1260 1.0000
11.500 1.3022 0.02894 0.02154 0.0047 0.1212 1.0000
11.750 1.3206 0.02975 0.02223 0.0057 0.1166 1.0000
12.000 1.3282 0.03040 0.02320 0.0083 0.1124 1.0000
12.250 1.3392 0.03095 0.02384 0.0104 0.1080 1.0000
12.500 1.3539 0.03187 0.02463 0.0117 0.1036 1.0000
12.750 1.3541 0.03271 0.02578 0.0151 0.1004 1.0000
13.000 1.3588 0.03356 0.02677 0.0177 0.0966 1.0000
13.250 1.3658 0.03438 0.02759 0.0196 0.0933 1.0000
13.500 1.3710 0.03579 0.02910 0.0215 0.0898 1.0000
13.750 1.3721 0.03717 0.03072 0.0235 0.0864 1.0000
14.000 1.3760 0.03842 0.03204 0.0250 0.0830 1.0000
14.250 1.3816 0.03994 0.03349 0.0262 0.0797 1.0000
14.500 1.3787 0.04211 0.03594 0.0275 0.0771 1.0000
14.750 1.3775 0.04425 0.03827 0.0284 0.0742 1.0000
15.000 1.3778 0.04630 0.04039 0.0290 0.0716 1.0000
15.250 1.3790 0.04858 0.04258 0.0296 0.0688 1.0000
15.500 1.3699 0.05197 0.04626 0.0296 0.0671 1.0000
15.750 1.3616 0.05550 0.05000 0.0293 0.0651 1.0000
16.000 1.3544 0.05906 0.05372 0.0287 0.0633 1.0000
16.250 1.3479 0.06265 0.05739 0.0278 0.0616 1.0000
16.500 1.3430 0.06615 0.06092 0.0270 0.0599 1.0000
16.750 1.3331 0.07056 0.06541 0.0261 0.0585 1.0000
17.000 1.3134 0.07680 0.07191 0.0233 0.0578 1.0000
17.250 1.2906 0.08398 0.07933 0.0196 0.0573 1.0000
17.500 1.2634 0.09233 0.08790 0.0151 0.0569 1.0000
17.750 1.2286 0.10257 0.09837 0.0092 0.0567 1.0000
18.000 1.1723 0.11767 0.11371 0.0003 0.0573 1.0000
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Polar data table (+)
Polar graphs
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