BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Reynolds number: 50,000 Max Cl/Cd: 31.92 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr8-il-50000-n5.txt Download as CSV file: xf-vr8-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5697 0.08902 0.08240 -0.0185 1.0000 0.0584
-8.250 -0.5641 0.08487 0.07825 -0.0185 1.0000 0.0573
-8.000 -0.5629 0.08052 0.07390 -0.0200 1.0000 0.0561
-7.750 -0.5624 0.07608 0.06946 -0.0218 1.0000 0.0549
-7.500 -0.5620 0.07152 0.06484 -0.0237 1.0000 0.0537
-7.250 -0.5603 0.06689 0.06010 -0.0253 1.0000 0.0522
-7.000 -0.5571 0.06209 0.05509 -0.0267 1.0000 0.0503
-6.750 -0.5534 0.05746 0.04966 -0.0278 1.0000 0.0466
-6.500 -0.5411 0.05321 0.04532 -0.0275 1.0000 0.0458
-6.250 -0.5283 0.04932 0.04117 -0.0271 1.0000 0.0452
-6.000 -0.5140 0.04563 0.03714 -0.0265 1.0000 0.0448
-5.750 -0.4977 0.04217 0.03326 -0.0257 1.0000 0.0445
-5.500 -0.4795 0.03903 0.02962 -0.0247 1.0000 0.0452
-5.250 -0.4603 0.03621 0.02629 -0.0237 1.0000 0.0474
-5.000 -0.4401 0.03368 0.02360 -0.0229 1.0000 0.0499
-4.750 -0.4173 0.03126 0.02080 -0.0219 1.0000 0.0506
-4.500 -0.3936 0.02912 0.01828 -0.0208 1.0000 0.0516
-4.250 -0.3695 0.02732 0.01623 -0.0197 1.0000 0.0538
-4.000 -0.3452 0.02595 0.01456 -0.0185 1.0000 0.0581
-3.750 -0.3217 0.02444 0.01297 -0.0173 1.0000 0.0603
-3.500 -0.2994 0.02318 0.01165 -0.0160 1.0000 0.0625
-3.250 -0.2776 0.02218 0.01053 -0.0148 1.0000 0.0653
-3.000 -0.2558 0.02130 0.00945 -0.0137 1.0000 0.0690
-2.750 -0.2347 0.02052 0.00853 -0.0125 1.0000 0.0739
-2.500 -0.2143 0.01975 0.00772 -0.0115 1.0000 0.0844
-2.250 -0.1944 0.01879 0.00700 -0.0106 1.0000 0.1179
-2.000 -0.1910 0.01595 0.00698 -0.0063 1.0000 0.6549
-1.750 -0.0665 0.01559 0.00668 -0.0201 1.0000 0.9987
-1.500 -0.0585 0.01552 0.00646 -0.0177 1.0000 1.0000
-1.250 -0.0541 0.01558 0.00639 -0.0146 1.0000 1.0000
-1.000 -0.0324 0.01572 0.00633 -0.0149 0.9910 1.0000
-0.750 0.0120 0.01585 0.00620 -0.0191 0.9717 1.0000
-0.500 0.0564 0.01596 0.00612 -0.0231 0.9541 1.0000
-0.250 0.1011 0.01602 0.00602 -0.0269 0.9336 1.0000
0.000 0.1506 0.01593 0.00577 -0.0309 0.9024 1.0000
0.250 0.1903 0.01590 0.00560 -0.0329 0.8729 1.0000
0.500 0.2228 0.01598 0.00557 -0.0338 0.8526 1.0000
0.750 0.2527 0.01610 0.00560 -0.0341 0.8348 1.0000
1.000 0.2789 0.01623 0.00565 -0.0336 0.8133 1.0000
1.250 0.3045 0.01637 0.00571 -0.0329 0.7934 1.0000
1.500 0.3293 0.01653 0.00579 -0.0320 0.7741 1.0000
1.750 0.3527 0.01672 0.00598 -0.0309 0.7548 1.0000
2.000 0.3762 0.01691 0.00615 -0.0299 0.7369 1.0000
2.250 0.3999 0.01713 0.00638 -0.0289 0.7210 1.0000
2.500 0.4241 0.01737 0.00668 -0.0282 0.7082 1.0000
2.750 0.4484 0.01763 0.00706 -0.0274 0.6959 1.0000
3.000 0.4723 0.01788 0.00740 -0.0265 0.6816 1.0000
3.250 0.4956 0.01811 0.00774 -0.0254 0.6642 1.0000
3.500 0.5188 0.01834 0.00807 -0.0243 0.6460 1.0000
3.750 0.5422 0.01858 0.00845 -0.0231 0.6283 1.0000
4.000 0.5643 0.01878 0.00885 -0.0217 0.6038 1.0000
4.250 0.5840 0.01888 0.00897 -0.0194 0.5620 1.0000
4.500 0.6025 0.01901 0.00906 -0.0170 0.5029 1.0000
4.750 0.6189 0.01939 0.00908 -0.0144 0.3838 1.0000
5.000 0.6288 0.02130 0.00964 -0.0122 0.1830 1.0000
5.250 0.6449 0.02306 0.01089 -0.0112 0.0994 1.0000
5.500 0.6633 0.02443 0.01225 -0.0101 0.0788 1.0000
5.750 0.6818 0.02569 0.01359 -0.0090 0.0706 1.0000
6.000 0.7000 0.02696 0.01499 -0.0077 0.0662 1.0000
6.250 0.7184 0.02821 0.01646 -0.0063 0.0631 1.0000
6.500 0.7372 0.02956 0.01799 -0.0049 0.0605 1.0000
6.750 0.7571 0.03103 0.01961 -0.0036 0.0585 1.0000
7.000 0.7786 0.03278 0.02149 -0.0025 0.0563 1.0000
7.250 0.8029 0.03453 0.02355 -0.0015 0.0527 1.0000
7.500 0.8276 0.03676 0.02607 -0.0006 0.0504 1.0000
7.750 0.8504 0.03935 0.02897 0.0002 0.0484 1.0000
8.000 0.8688 0.04229 0.03194 0.0008 0.0451 1.0000
8.250 0.8836 0.04531 0.03565 0.0022 0.0430 1.0000
8.500 0.8955 0.04898 0.03986 0.0035 0.0424 1.0000
8.750 0.9023 0.05285 0.04428 0.0049 0.0416 1.0000
9.000 0.9043 0.05665 0.04852 0.0061 0.0404 1.0000
9.250 0.9030 0.06033 0.05255 0.0071 0.0391 1.0000
9.500 0.8994 0.06388 0.05637 0.0080 0.0380 1.0000
9.750 0.8929 0.06752 0.06021 0.0086 0.0373 1.0000
10.000 0.8755 0.07152 0.06443 0.0091 0.0375 1.0000
10.250 0.8520 0.07663 0.06972 0.0075 0.0382 1.0000
10.500 0.8280 0.08313 0.07634 0.0034 0.0396 1.0000
10.750 0.8090 0.09029 0.08352 -0.0015 0.0411 1.0000
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Polar data table (+)
Polar graphs
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