BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Reynolds number: 100,000 Max Cl/Cd: 40.62 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr14-il-100000.txt Download as CSV file: xf-vr14-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5358 0.09220 0.08765 -0.0046 1.0000 0.0753
-7.750 -0.5417 0.08788 0.08331 -0.0130 1.0000 0.0769
-7.500 -0.5471 0.08453 0.07972 -0.0201 1.0000 0.0778
-7.250 -0.5302 0.07883 0.07431 -0.0144 1.0000 0.0814
-7.000 -0.5217 0.07522 0.07068 -0.0152 1.0000 0.0855
-6.750 -0.5222 0.07256 0.06753 -0.0227 1.0000 0.0918
-6.500 -0.5096 0.06641 0.06165 -0.0211 1.0000 0.0945
-6.250 -0.4971 0.06319 0.05844 -0.0204 1.0000 0.1003
-6.000 -0.4893 0.05918 0.05419 -0.0224 1.0000 0.1085
-5.750 -0.4757 0.05617 0.05120 -0.0215 1.0000 0.1165
-5.500 -0.4655 0.05272 0.04766 -0.0211 1.0000 0.1258
-5.250 -0.4559 0.04983 0.04464 -0.0202 1.0000 0.1388
-5.000 -0.4468 0.04725 0.04200 -0.0185 1.0000 0.1534
-4.750 -0.4377 0.04485 0.03958 -0.0164 1.0000 0.1698
-4.500 -0.4311 0.04274 0.03741 -0.0140 1.0000 0.1964
-4.250 -0.4239 0.04079 0.03556 -0.0109 1.0000 0.2284
-3.750 -0.3681 0.03205 0.02460 -0.0083 1.0000 0.1074
-3.500 -0.3689 0.03181 0.02537 -0.0073 1.0000 0.1967
-3.250 -0.3212 0.02595 0.01731 -0.0038 1.0000 0.0791
-3.000 -0.2981 0.02450 0.01548 -0.0021 1.0000 0.0778
-2.750 -0.2743 0.02209 0.01296 -0.0014 1.0000 0.0815
-2.500 -0.2501 0.02082 0.01158 -0.0005 1.0000 0.0857
-2.250 -0.2251 0.01973 0.01031 0.0005 1.0000 0.0891
-2.000 -0.2005 0.01867 0.00925 0.0011 1.0000 0.0961
-1.750 -0.1762 0.01786 0.00847 0.0018 1.0000 0.1018
-1.500 -0.1532 0.01715 0.00782 0.0026 1.0000 0.1115
-1.250 -0.0457 0.01300 0.00680 -0.0108 1.0000 1.0000
-1.000 -0.0330 0.01317 0.00667 -0.0083 1.0000 1.0000
-0.750 -0.0194 0.01336 0.00665 -0.0062 1.0000 1.0000
-0.500 -0.0046 0.01357 0.00670 -0.0043 1.0000 1.0000
-0.250 0.0113 0.01381 0.00678 -0.0027 1.0000 1.0000
0.000 0.0428 0.01410 0.00692 -0.0042 0.9961 1.0000
0.250 0.1132 0.01438 0.00705 -0.0130 0.9820 1.0000
0.500 0.1745 0.01455 0.00713 -0.0200 0.9702 1.0000
0.750 0.2361 0.01458 0.00713 -0.0268 0.9574 1.0000
1.000 0.2973 0.01446 0.00702 -0.0331 0.9434 1.0000
1.250 0.3422 0.01434 0.00693 -0.0360 0.9252 1.0000
1.500 0.3798 0.01415 0.00678 -0.0370 0.9052 1.0000
1.750 0.4103 0.01392 0.00657 -0.0362 0.8845 1.0000
2.000 0.4326 0.01370 0.00637 -0.0337 0.8599 1.0000
2.250 0.4527 0.01347 0.00614 -0.0307 0.8329 1.0000
2.500 0.4718 0.01321 0.00587 -0.0273 0.8018 1.0000
2.750 0.4907 0.01298 0.00560 -0.0240 0.7611 1.0000
3.000 0.5094 0.01283 0.00531 -0.0207 0.7003 1.0000
3.250 0.5269 0.01297 0.00496 -0.0171 0.5805 1.0000
3.500 0.5446 0.01389 0.00502 -0.0146 0.4601 1.0000
3.750 0.5659 0.01479 0.00547 -0.0134 0.4017 1.0000
4.000 0.5886 0.01557 0.00594 -0.0124 0.3669 1.0000
4.250 0.6120 0.01631 0.00646 -0.0117 0.3419 1.0000
4.500 0.6361 0.01704 0.00707 -0.0110 0.3223 1.0000
4.750 0.6604 0.01777 0.00775 -0.0103 0.3057 1.0000
5.000 0.6847 0.01851 0.00843 -0.0097 0.2910 1.0000
5.250 0.7092 0.01927 0.00916 -0.0092 0.2781 1.0000
5.500 0.7339 0.02014 0.00994 -0.0087 0.2676 1.0000
5.750 0.7583 0.02088 0.01078 -0.0081 0.2561 1.0000
6.000 0.7822 0.02159 0.01158 -0.0075 0.2439 1.0000
6.250 0.8058 0.02233 0.01239 -0.0069 0.2321 1.0000
6.500 0.8294 0.02313 0.01322 -0.0063 0.2214 1.0000
6.750 0.8534 0.02397 0.01406 -0.0057 0.2116 1.0000
7.000 0.8764 0.02485 0.01521 -0.0050 0.2012 1.0000
7.250 0.8992 0.02588 0.01640 -0.0042 0.1909 1.0000
7.500 0.9214 0.02675 0.01734 -0.0035 0.1790 1.0000
7.750 0.9430 0.02748 0.01815 -0.0027 0.1660 1.0000
8.000 0.9644 0.02827 0.01897 -0.0018 0.1535 1.0000
8.250 0.9855 0.02916 0.01994 -0.0009 0.1417 1.0000
8.500 1.0049 0.03004 0.02105 0.0002 0.1295 1.0000
8.750 1.0235 0.03132 0.02258 0.0014 0.1184 1.0000
9.000 1.0418 0.03294 0.02438 0.0026 0.1091 1.0000
9.250 1.0618 0.03405 0.02541 0.0034 0.1003 1.0000
9.500 1.0757 0.03585 0.02773 0.0051 0.0924 1.0000
9.750 1.0937 0.03798 0.02983 0.0060 0.0872 1.0000
10.000 1.1004 0.04111 0.03365 0.0081 0.0829 1.0000
10.250 1.1146 0.04272 0.03540 0.0094 0.0781 1.0000
10.500 1.1250 0.04540 0.03819 0.0106 0.0745 1.0000
10.750 1.1187 0.04955 0.04296 0.0131 0.0729 1.0000
11.000 1.1064 0.05415 0.04805 0.0154 0.0720 1.0000
11.250 1.0864 0.05897 0.05325 0.0174 0.0717 1.0000
11.500 1.0587 0.06368 0.05822 0.0193 0.0720 1.0000
11.750 1.0276 0.06943 0.06416 0.0187 0.0726 1.0000
12.000 0.9948 0.07669 0.07157 0.0153 0.0735 1.0000
12.250 0.9630 0.08567 0.08062 0.0097 0.0745 1.0000
12.500 0.9364 0.09554 0.09049 0.0038 0.0753 1.0000
12.750 0.8395 0.13319 0.12788 -0.0173 0.1007 1.0000
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Polar data table (+)
Polar graphs
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