BOEING-VERTOL VR-15 AIRFOIL (vr15-il) Xfoil prediction polar at RE=100,000 Ncrit=5
Details | Polar file |
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Airfoil: BOEING-VERTOL VR-15 AIRFOIL (vr15-il) Reynolds number: 100,000 Max Cl/Cd: 39.02 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr15-il-100000-n5.txt Download as CSV file: xf-vr15-il-100000-n5.csv |
XFOIL Version 6.96 Calculated polar for: BOEING-VERTOL VR-15 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 ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5891 0.08863 0.08387 -0.0017 1.0000 0.0294 -8.250 -0.6064 0.07726 0.07240 -0.0136 1.0000 0.0251 -8.000 -0.6054 0.07286 0.06795 -0.0147 1.0000 0.0248 -7.750 -0.6035 0.06821 0.06322 -0.0158 1.0000 0.0247 -7.500 -0.6005 0.06335 0.05822 -0.0167 1.0000 0.0245 -7.250 -0.5959 0.05841 0.05307 -0.0172 1.0000 0.0244 -7.000 -0.5900 0.05319 0.04753 -0.0171 1.0000 0.0246 -6.500 -0.5674 0.04727 0.04129 -0.0162 1.0000 0.0277 -6.250 -0.5541 0.04391 0.03763 -0.0152 1.0000 0.0291 -6.000 -0.5409 0.03994 0.03325 -0.0138 1.0000 0.0296 -5.750 -0.5261 0.03636 0.02920 -0.0121 1.0000 0.0304 -5.500 -0.5092 0.03350 0.02574 -0.0101 1.0000 0.0329 -5.250 -0.4925 0.03077 0.02248 -0.0081 1.0000 0.0345 -5.000 -0.4749 0.02841 0.01988 -0.0065 1.0000 0.0357 -4.750 -0.4561 0.02680 0.01807 -0.0050 1.0000 0.0374 -4.500 -0.4369 0.02558 0.01664 -0.0035 1.0000 0.0405 -4.250 -0.4165 0.02409 0.01483 -0.0018 1.0000 0.0424 -4.000 -0.3953 0.02273 0.01319 -0.0003 1.0000 0.0438 -3.750 -0.3742 0.02161 0.01186 0.0011 1.0000 0.0460 -3.500 -0.3538 0.02043 0.01070 0.0023 1.0000 0.0491 -3.250 -0.3328 0.01953 0.00973 0.0036 1.0000 0.0511 -3.000 -0.3119 0.01874 0.00889 0.0049 1.0000 0.0531 -2.750 -0.2914 0.01818 0.00825 0.0062 1.0000 0.0567 -2.500 -0.2591 0.01735 0.00742 0.0051 0.9953 0.0604 -2.250 -0.2258 0.01671 0.00675 0.0037 0.9897 0.0645 -2.000 -0.1905 0.01624 0.00618 0.0021 0.9843 0.0704 -1.750 -0.1568 0.01576 0.00573 0.0007 0.9783 0.0831 -1.500 -0.1225 0.01493 0.00535 -0.0009 0.9732 0.1594 -1.250 -0.0269 0.01266 0.00584 -0.0127 0.9984 1.0000 -1.000 0.0112 0.01268 0.00567 -0.0152 0.9904 1.0000 -0.750 0.0572 0.01265 0.00547 -0.0192 0.9805 1.0000 -0.500 0.1076 0.01256 0.00524 -0.0237 0.9633 1.0000 -0.250 0.1508 0.01244 0.00500 -0.0265 0.9409 1.0000 0.250 0.2072 0.01233 0.00473 -0.0259 0.8967 1.0000 0.500 0.2312 0.01231 0.00465 -0.0247 0.8773 1.0000 0.750 0.2545 0.01228 0.00457 -0.0233 0.8577 1.0000 1.000 0.2772 0.01227 0.00450 -0.0219 0.8362 1.0000 1.250 0.2996 0.01225 0.00442 -0.0203 0.8134 1.0000 1.500 0.3220 0.01224 0.00437 -0.0187 0.7875 1.0000 1.750 0.3444 0.01225 0.00430 -0.0170 0.7581 1.0000 2.000 0.3670 0.01229 0.00424 -0.0154 0.7219 1.0000 2.250 0.3896 0.01236 0.00419 -0.0138 0.6727 1.0000 2.500 0.4115 0.01254 0.00412 -0.0121 0.5984 1.0000 2.750 0.4327 0.01298 0.00406 -0.0103 0.5001 1.0000 3.000 0.4546 0.01360 0.00421 -0.0092 0.4158 1.0000 3.250 0.4774 0.01417 0.00446 -0.0084 0.3590 1.0000 3.500 0.5007 0.01468 0.00478 -0.0077 0.3221 1.0000 3.750 0.5244 0.01513 0.00511 -0.0071 0.2960 1.0000 4.000 0.5480 0.01558 0.00546 -0.0064 0.2767 1.0000 4.250 0.5716 0.01603 0.00583 -0.0057 0.2606 1.0000 4.500 0.5953 0.01647 0.00625 -0.0050 0.2461 1.0000 4.750 0.6190 0.01691 0.00668 -0.0043 0.2329 1.0000 5.000 0.6428 0.01736 0.00715 -0.0037 0.2218 1.0000 5.250 0.6664 0.01784 0.00763 -0.0030 0.2112 1.0000 5.500 0.6897 0.01831 0.00812 -0.0023 0.1994 1.0000 5.750 0.7129 0.01878 0.00857 -0.0016 0.1874 1.0000 6.000 0.7363 0.01921 0.00909 -0.0009 0.1760 1.0000 6.250 0.7596 0.01973 0.00969 -0.0002 0.1670 1.0000 6.500 0.7823 0.02028 0.01029 0.0006 0.1584 1.0000 6.750 0.8053 0.02077 0.01090 0.0013 0.1476 1.0000 7.000 0.8279 0.02127 0.01151 0.0021 0.1357 1.0000 7.250 0.8502 0.02179 0.01212 0.0028 0.1233 1.0000 7.500 0.8721 0.02236 0.01281 0.0036 0.1107 1.0000 7.750 0.8935 0.02302 0.01354 0.0044 0.0985 1.0000 8.000 0.9143 0.02380 0.01439 0.0053 0.0875 1.0000 8.250 0.9345 0.02463 0.01527 0.0063 0.0769 1.0000 8.500 0.9541 0.02556 0.01630 0.0072 0.0680 1.0000 8.750 0.9727 0.02674 0.01764 0.0084 0.0612 1.0000 9.000 0.9895 0.02796 0.01887 0.0096 0.0555 1.0000 9.250 1.0069 0.02931 0.02045 0.0108 0.0506 1.0000 9.500 1.0227 0.03075 0.02204 0.0121 0.0471 1.0000 9.750 1.0359 0.03248 0.02382 0.0136 0.0444 1.0000 10.000 1.0500 0.03428 0.02592 0.0150 0.0419 1.0000 10.250 1.0627 0.03604 0.02797 0.0165 0.0391 1.0000 10.500 1.0737 0.03779 0.02995 0.0179 0.0370 1.0000 10.750 1.0826 0.03973 0.03205 0.0195 0.0356 1.0000 11.000 1.0887 0.04198 0.03443 0.0211 0.0344 1.0000 11.250 1.0906 0.04476 0.03744 0.0230 0.0336 1.0000 11.500 1.0871 0.04751 0.04054 0.0251 0.0329 1.0000 11.750 1.0779 0.05049 0.04383 0.0272 0.0324 1.0000 12.000 1.0655 0.05401 0.04763 0.0282 0.0319 1.0000 12.250 1.0499 0.05825 0.05214 0.0279 0.0315 1.0000 12.500 1.0307 0.06355 0.05770 0.0260 0.0314 1.0000 12.750 1.0073 0.07045 0.06483 0.0219 0.0315 1.0000 13.000 0.9787 0.07977 0.07435 0.0151 0.0320 1.0000 13.250 0.9447 0.09176 0.08647 0.0065 0.0328 1.0000 13.500 0.9069 0.10526 0.10002 -0.0019 0.0335 1.0000 |
Polar data table (+)
Polar graphs
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