BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Reynolds number: 50,000 Max Cl/Cd: 23.84 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr9-il-50000-n5.txt Download as CSV file: xf-vr9-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-9 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6656 0.11026 0.10372 0.0098 1.0000 0.1137
-8.750 -0.6453 0.10523 0.09865 0.0135 1.0000 0.1233
-8.500 -0.6592 0.10195 0.09550 0.0081 1.0000 0.1267
-8.000 -0.6435 0.08710 0.08059 -0.0010 1.0000 0.0558
-7.750 -0.6449 0.08070 0.07411 -0.0069 1.0000 0.0461
-7.500 -0.6419 0.07611 0.06947 -0.0088 1.0000 0.0456
-7.250 -0.6378 0.07146 0.06473 -0.0106 1.0000 0.0451
-7.000 -0.6319 0.06687 0.06002 -0.0121 1.0000 0.0444
-6.750 -0.6241 0.06230 0.05524 -0.0135 1.0000 0.0441
-6.500 -0.6139 0.05781 0.05050 -0.0144 1.0000 0.0435
-6.250 -0.6013 0.05337 0.04574 -0.0150 1.0000 0.0426
-6.000 -0.5864 0.04903 0.04101 -0.0152 1.0000 0.0411
-5.750 -0.5690 0.04481 0.03614 -0.0151 1.0000 0.0397
-5.500 -0.5494 0.04092 0.03171 -0.0145 1.0000 0.0387
-5.250 -0.5278 0.03739 0.02762 -0.0138 1.0000 0.0383
-5.000 -0.5047 0.03420 0.02392 -0.0130 1.0000 0.0386
-4.750 -0.4803 0.03140 0.02066 -0.0121 1.0000 0.0398
-4.500 -0.4551 0.02936 0.01812 -0.0113 1.0000 0.0461
-4.250 -0.4293 0.02696 0.01543 -0.0103 1.0000 0.0493
-4.000 -0.4034 0.02493 0.01324 -0.0092 1.0000 0.0518
-3.750 -0.3782 0.02332 0.01142 -0.0080 1.0000 0.0550
-3.500 -0.3535 0.02202 0.00984 -0.0069 1.0000 0.0593
-3.250 -0.3291 0.02090 0.00859 -0.0063 1.0000 0.0722
-3.000 -0.3051 0.01973 0.00717 -0.0056 1.0000 0.0835
-2.750 -0.2816 0.01845 0.00597 -0.0049 1.0000 0.1110
-2.500 -0.2731 0.01537 0.00550 -0.0017 1.0000 0.5955
-2.250 -0.2308 0.01466 0.00544 -0.0003 1.0000 0.9007
-2.000 -0.1646 0.01448 0.00470 -0.0074 1.0000 0.9751
-1.750 -0.1237 0.01427 0.00404 -0.0106 1.0000 1.0000
-1.500 -0.1045 0.01412 0.00369 -0.0095 1.0000 1.0000
-1.250 -0.0847 0.01401 0.00340 -0.0085 1.0000 1.0000
-1.000 -0.0648 0.01393 0.00318 -0.0074 1.0000 1.0000
-0.750 -0.0447 0.01388 0.00302 -0.0063 1.0000 1.0000
-0.500 -0.0245 0.01385 0.00288 -0.0052 1.0000 1.0000
-0.250 -0.0042 0.01385 0.00281 -0.0041 1.0000 1.0000
0.000 0.0160 0.01386 0.00280 -0.0030 1.0000 1.0000
0.250 0.0361 0.01390 0.00283 -0.0020 1.0000 1.0000
0.500 0.0560 0.01396 0.00292 -0.0009 1.0000 1.0000
0.750 0.0756 0.01406 0.00307 0.0001 1.0000 1.0000
1.000 0.0948 0.01419 0.00326 0.0012 1.0000 1.0000
1.250 0.1249 0.01436 0.00354 -0.0001 0.9881 1.0000
1.500 0.1741 0.01455 0.00391 -0.0048 0.9580 1.0000
1.750 0.2146 0.01473 0.00436 -0.0076 0.9334 1.0000
2.000 0.2540 0.01491 0.00480 -0.0101 0.9085 1.0000
2.250 0.2920 0.01510 0.00528 -0.0121 0.8829 1.0000
2.500 0.3276 0.01530 0.00582 -0.0134 0.8554 1.0000
2.750 0.3602 0.01541 0.00605 -0.0121 0.7745 1.0000
3.000 0.3772 0.01582 0.00619 -0.0073 0.6301 1.0000
3.250 0.3828 0.01822 0.00624 -0.0026 0.1801 1.0000
3.500 0.4036 0.02010 0.00746 -0.0021 0.0800 1.0000
3.750 0.4281 0.02123 0.00869 -0.0016 0.0663 1.0000
4.000 0.4516 0.02249 0.01006 -0.0009 0.0606 1.0000
4.250 0.4752 0.02374 0.01162 0.0002 0.0575 1.0000
4.500 0.4993 0.02524 0.01338 0.0015 0.0547 1.0000
4.750 0.5247 0.02710 0.01545 0.0027 0.0523 1.0000
5.000 0.5494 0.02933 0.01800 0.0036 0.0460 1.0000
5.250 0.5753 0.03169 0.02084 0.0046 0.0419 1.0000
5.500 0.6000 0.03463 0.02428 0.0056 0.0408 1.0000
5.750 0.6229 0.03797 0.02816 0.0066 0.0403 1.0000
6.000 0.6434 0.04155 0.03230 0.0075 0.0401 1.0000
6.250 0.6610 0.04492 0.03605 0.0080 0.0379 1.0000
6.500 0.6736 0.04929 0.04051 0.0081 0.0350 1.0000
6.750 0.6875 0.05291 0.04476 0.0085 0.0340 1.0000
7.000 0.6980 0.05726 0.04949 0.0086 0.0340 1.0000
7.250 0.7061 0.06189 0.05438 0.0084 0.0345 1.0000
7.500 0.7128 0.06687 0.05949 0.0080 0.0351 1.0000
7.750 0.7139 0.07108 0.06424 0.0063 0.0370 1.0000
8.000 0.7090 0.07670 0.07006 0.0033 0.0388 1.0000
8.250 0.7038 0.08212 0.07555 0.0001 0.0402 1.0000
8.500 0.6969 0.08742 0.08082 -0.0037 0.0413 1.0000
8.750 0.6932 0.09303 0.08637 -0.0080 0.0425 1.0000
9.000 0.6919 0.09816 0.09145 -0.0110 0.0441 1.0000
9.250 0.6937 0.10278 0.09602 -0.0127 0.0460 1.0000
9.500 0.6918 0.10860 0.10181 -0.0172 0.0527 1.0000
9.750 0.6923 0.11470 0.10787 -0.0205 0.0669 1.0000
10.000 0.5902 0.10989 0.10348 -0.0132 0.0503 1.0000
10.250 0.5835 0.11529 0.10882 -0.0163 0.0543 1.0000
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Polar data table (+)
Polar graphs
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