BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Reynolds number: 200,000 Max Cl/Cd: 50.71 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr14-il-200000.txt Download as CSV file: xf-vr14-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-14 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5411 0.09178 0.08850 0.0007 1.0000 0.0303
-8.000 -0.5393 0.08765 0.08440 -0.0023 1.0000 0.0308
-7.750 -0.5388 0.08325 0.08003 -0.0063 1.0000 0.0313
-7.500 -0.5349 0.07873 0.07549 -0.0102 1.0000 0.0319
-7.250 -0.5288 0.07411 0.07085 -0.0139 1.0000 0.0326
-7.000 -0.5208 0.06947 0.06615 -0.0171 1.0000 0.0336
-6.750 -0.5104 0.06485 0.06141 -0.0200 1.0000 0.0349
-6.500 -0.4926 0.06091 0.05710 -0.0232 1.0000 0.0374
-6.250 -0.4786 0.05807 0.05393 -0.0234 1.0000 0.0379
-6.000 -0.4743 0.05153 0.04719 -0.0234 1.0000 0.0386
-5.750 -0.4645 0.04717 0.04291 -0.0229 1.0000 0.0398
-5.500 -0.4538 0.04456 0.04029 -0.0216 1.0000 0.0412
-5.250 -0.4450 0.04225 0.03788 -0.0194 1.0000 0.0431
-5.000 -0.4362 0.04008 0.03552 -0.0168 1.0000 0.0466
-4.750 -0.4304 0.03751 0.03243 -0.0132 1.0000 0.0522
-4.500 -0.4209 0.03540 0.03047 -0.0115 1.0000 0.0556
-4.000 -0.3981 0.03133 0.02591 -0.0068 1.0000 0.0676
-3.750 -0.3817 0.02969 0.02413 -0.0052 0.9997 0.0732
-3.500 -0.3476 0.02733 0.02151 -0.0070 0.9960 0.0871
-3.250 -0.3051 0.02051 0.01335 -0.0046 0.9945 0.0421
-3.000 -0.2690 0.01900 0.01157 -0.0059 0.9908 0.0470
-2.750 -0.2308 0.01817 0.01043 -0.0074 0.9868 0.0508
-2.500 -0.1945 0.01612 0.00835 -0.0092 0.9845 0.0560
-2.250 -0.1582 0.01526 0.00743 -0.0107 0.9806 0.0603
-2.000 -0.1223 0.01455 0.00669 -0.0123 0.9758 0.0650
-1.750 -0.0801 0.01366 0.00588 -0.0153 0.9715 0.0722
-1.500 -0.0362 0.01300 0.00523 -0.0184 0.9632 0.0831
-1.250 0.0060 0.01157 0.00457 -0.0214 0.9555 0.2645
-1.000 0.1202 0.00947 0.00462 -0.0371 0.9672 1.0000
-0.750 0.1562 0.00939 0.00442 -0.0385 0.9532 1.0000
-0.500 0.1826 0.00936 0.00429 -0.0379 0.9378 1.0000
-0.250 0.2053 0.00934 0.00419 -0.0364 0.9232 1.0000
0.000 0.2264 0.00931 0.00408 -0.0346 0.9087 1.0000
0.250 0.2471 0.00926 0.00397 -0.0326 0.8945 1.0000
0.500 0.2677 0.00921 0.00385 -0.0306 0.8798 1.0000
0.750 0.2888 0.00916 0.00373 -0.0287 0.8645 1.0000
1.000 0.3102 0.00909 0.00361 -0.0269 0.8478 1.0000
1.250 0.3320 0.00903 0.00348 -0.0251 0.8302 1.0000
1.500 0.3546 0.00899 0.00338 -0.0235 0.8095 1.0000
1.750 0.3773 0.00895 0.00326 -0.0219 0.7868 1.0000
2.000 0.4007 0.00895 0.00317 -0.0205 0.7596 1.0000
2.250 0.4244 0.00899 0.00310 -0.0192 0.7261 1.0000
2.500 0.4480 0.00906 0.00303 -0.0179 0.6760 1.0000
2.750 0.4704 0.00935 0.00292 -0.0164 0.5811 1.0000
3.000 0.4917 0.01016 0.00300 -0.0152 0.4462 1.0000
3.250 0.5146 0.01090 0.00328 -0.0146 0.3665 1.0000
3.500 0.5383 0.01149 0.00358 -0.0140 0.3269 1.0000
3.750 0.5625 0.01197 0.00392 -0.0135 0.3010 1.0000
4.000 0.5866 0.01246 0.00425 -0.0129 0.2821 1.0000
4.250 0.6109 0.01289 0.00460 -0.0124 0.2658 1.0000
4.500 0.6351 0.01333 0.00497 -0.0118 0.2518 1.0000
4.750 0.6592 0.01380 0.00537 -0.0112 0.2399 1.0000
5.000 0.6838 0.01415 0.00574 -0.0107 0.2285 1.0000
5.250 0.7081 0.01456 0.00614 -0.0101 0.2178 1.0000
5.500 0.7321 0.01497 0.00654 -0.0095 0.2076 1.0000
5.750 0.7562 0.01537 0.00692 -0.0090 0.1986 1.0000
6.000 0.7805 0.01581 0.00742 -0.0084 0.1909 1.0000
6.250 0.8044 0.01630 0.00787 -0.0078 0.1838 1.0000
6.500 0.8286 0.01674 0.00841 -0.0072 0.1765 1.0000
6.750 0.8522 0.01727 0.00891 -0.0066 0.1692 1.0000
7.000 0.8760 0.01754 0.00933 -0.0059 0.1600 1.0000
7.250 0.8992 0.01794 0.00978 -0.0053 0.1509 1.0000
7.500 0.9221 0.01836 0.01019 -0.0047 0.1416 1.0000
7.750 0.9452 0.01864 0.01064 -0.0040 0.1309 1.0000
8.000 0.9677 0.01910 0.01118 -0.0033 0.1199 1.0000
8.250 0.9896 0.01964 0.01178 -0.0025 0.1088 1.0000
8.500 1.0111 0.02022 0.01238 -0.0017 0.0977 1.0000
8.750 1.0317 0.02091 0.01307 -0.0008 0.0870 1.0000
9.000 1.0528 0.02155 0.01384 0.0001 0.0772 1.0000
9.250 1.0727 0.02247 0.01486 0.0012 0.0686 1.0000
9.500 1.0904 0.02370 0.01610 0.0024 0.0619 1.0000
9.750 1.1093 0.02473 0.01727 0.0035 0.0566 1.0000
10.000 1.1241 0.02680 0.01931 0.0049 0.0522 1.0000
10.250 1.1419 0.02808 0.02086 0.0062 0.0497 1.0000
10.500 1.1582 0.02944 0.02245 0.0075 0.0466 1.0000
10.750 1.1733 0.03083 0.02392 0.0087 0.0438 1.0000
11.000 1.1841 0.03374 0.02697 0.0102 0.0415 1.0000
11.250 1.1929 0.03627 0.02983 0.0120 0.0404 1.0000
11.500 1.2006 0.03833 0.03223 0.0139 0.0394 1.0000
11.750 1.2043 0.04071 0.03492 0.0160 0.0384 1.0000
12.000 1.2034 0.04312 0.03762 0.0183 0.0374 1.0000
12.250 1.1980 0.04551 0.04024 0.0209 0.0366 1.0000
12.500 1.1913 0.04808 0.04302 0.0227 0.0358 1.0000
12.750 1.1817 0.05110 0.04625 0.0239 0.0351 1.0000
13.000 1.1696 0.05466 0.05003 0.0242 0.0346 1.0000
13.250 1.1532 0.05918 0.05477 0.0234 0.0344 1.0000
13.500 1.1305 0.06517 0.06100 0.0208 0.0345 1.0000
13.750 1.0975 0.07392 0.07003 0.0153 0.0351 1.0000
14.000 1.0101 0.09702 0.09349 -0.0021 0.0387 1.0000
14.250 0.9306 0.12053 0.11696 -0.0158 0.0409 1.0000
14.500 0.8390 0.15669 0.15292 -0.0323 0.0536 1.0000
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Polar data table (+)
Polar graphs
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