BOEING-VERTOL VR-15 AIRFOIL (vr15-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-15 AIRFOIL (vr15-il) Reynolds number: 50,000 Max Cl/Cd: 28.14 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr15-il-50000.txt Download as CSV file: xf-vr15-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5679 0.10248 0.09601 0.0180 1.0000 0.2709
-8.000 -0.5739 0.09965 0.09326 0.0174 1.0000 0.2878
-7.750 -0.5846 0.09699 0.09071 0.0164 1.0000 0.3037
-7.500 -0.5701 0.09309 0.08681 0.0193 1.0000 0.3325
-7.250 -0.5571 0.08932 0.08307 0.0219 1.0000 0.3609
-7.000 -0.5539 0.08627 0.08007 0.0240 1.0000 0.3908
-6.750 -0.5305 0.08239 0.07618 0.0280 1.0000 0.4323
-6.500 -0.5086 0.07911 0.07289 0.0329 1.0000 0.4902
-6.250 -0.4851 0.07570 0.06947 0.0372 1.0000 0.5485
-6.000 -0.4724 0.07328 0.06705 0.0421 1.0000 0.6116
-4.750 -0.4708 0.04072 0.03177 -0.0103 1.0000 0.1564
-4.500 -0.4507 0.03720 0.02783 -0.0089 1.0000 0.1468
-4.250 -0.4298 0.03504 0.02489 -0.0069 1.0000 0.1432
-4.000 -0.4090 0.03240 0.02204 -0.0054 1.0000 0.1447
-3.750 -0.3858 0.03050 0.01960 -0.0038 1.0000 0.1432
-3.500 -0.3618 0.02834 0.01720 -0.0026 1.0000 0.1444
-3.250 -0.3381 0.02662 0.01544 -0.0016 1.0000 0.1517
-3.000 -0.3118 0.02522 0.01372 -0.0005 1.0000 0.1567
-2.750 -0.2821 0.02364 0.01214 -0.0002 1.0000 0.1629
-2.500 -0.2499 0.02239 0.01079 -0.0002 1.0000 0.1744
-2.250 -0.0842 0.01680 0.00797 -0.0213 1.0000 1.0000
-2.000 -0.0676 0.01673 0.00754 -0.0195 1.0000 1.0000
-1.750 -0.0527 0.01671 0.00726 -0.0174 1.0000 1.0000
-1.500 -0.0393 0.01672 0.00707 -0.0151 1.0000 1.0000
-1.250 -0.0264 0.01678 0.00693 -0.0127 1.0000 1.0000
-1.000 -0.0137 0.01686 0.00686 -0.0103 1.0000 1.0000
-0.750 -0.0011 0.01698 0.00681 -0.0079 1.0000 1.0000
-0.500 0.0117 0.01712 0.00681 -0.0056 1.0000 1.0000
-0.250 0.0248 0.01729 0.00686 -0.0034 1.0000 1.0000
0.000 0.0382 0.01749 0.00695 -0.0013 1.0000 1.0000
0.250 0.0521 0.01771 0.00708 0.0007 1.0000 1.0000
0.500 0.0665 0.01796 0.00725 0.0026 1.0000 1.0000
0.750 0.0814 0.01824 0.00747 0.0042 1.0000 1.0000
1.000 0.0969 0.01856 0.00774 0.0057 1.0000 1.0000
1.250 0.1126 0.01891 0.00807 0.0070 1.0000 1.0000
1.500 0.1287 0.01931 0.00845 0.0082 1.0000 1.0000
1.750 0.1449 0.01976 0.00891 0.0092 1.0000 1.0000
2.000 0.1610 0.02027 0.00945 0.0101 1.0000 1.0000
2.250 0.1768 0.02087 0.01009 0.0108 1.0000 1.0000
2.500 0.2512 0.02187 0.01131 0.0002 0.9750 1.0000
2.750 0.3732 0.02216 0.01207 -0.0173 0.9225 1.0000
3.000 0.4751 0.02091 0.01136 -0.0271 0.8567 1.0000
3.250 0.5100 0.01977 0.01037 -0.0234 0.7793 1.0000
3.500 0.5281 0.01913 0.00951 -0.0170 0.6786 1.0000
3.750 0.5451 0.01937 0.00915 -0.0122 0.5815 1.0000
4.000 0.5652 0.02023 0.00949 -0.0096 0.5144 1.0000
4.250 0.5884 0.02125 0.01019 -0.0081 0.4689 1.0000
4.500 0.6124 0.02233 0.01106 -0.0070 0.4351 1.0000
4.750 0.6369 0.02346 0.01214 -0.0062 0.4082 1.0000
5.000 0.6611 0.02463 0.01331 -0.0053 0.3850 1.0000
5.250 0.6853 0.02586 0.01453 -0.0045 0.3651 1.0000
5.500 0.7095 0.02723 0.01594 -0.0038 0.3479 1.0000
5.750 0.7322 0.02866 0.01755 -0.0030 0.3294 1.0000
6.000 0.7545 0.03016 0.01921 -0.0021 0.3113 1.0000
6.250 0.7762 0.03158 0.02067 -0.0010 0.2922 1.0000
6.500 0.7978 0.03320 0.02234 0.0000 0.2744 1.0000
6.750 0.8182 0.03532 0.02474 0.0010 0.2590 1.0000
7.000 0.8361 0.03755 0.02733 0.0022 0.2419 1.0000
7.250 0.8529 0.03988 0.02995 0.0035 0.2251 1.0000
7.500 0.8686 0.04237 0.03272 0.0048 0.2096 1.0000
7.750 0.8826 0.04505 0.03567 0.0061 0.1955 1.0000
8.000 0.8956 0.04806 0.03897 0.0075 0.1841 1.0000
8.250 0.9090 0.05059 0.04164 0.0088 0.1715 1.0000
8.500 0.9057 0.05582 0.04749 0.0099 0.1669 1.0000
8.750 0.9233 0.05855 0.05016 0.0112 0.1588 1.0000
9.000 0.9102 0.06456 0.05667 0.0117 0.1577 1.0000
9.250 0.8948 0.07066 0.06306 0.0116 0.1575 1.0000
9.500 0.8785 0.07681 0.06936 0.0109 0.1580 1.0000
9.750 0.8633 0.08295 0.07557 0.0097 0.1587 1.0000
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Polar data table (+)
Polar graphs
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