BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-12 AIRFOIL (vr12-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.39 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr12-il-1000000.txt Download as CSV file: xf-vr12-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3992 0.13211 0.13063 0.0003 1.0000 0.0104
-12.250 -0.3959 0.12921 0.12772 -0.0007 1.0000 0.0105
-12.000 -1.0395 0.03218 0.02924 -0.0302 1.0000 0.0063
-11.750 -1.0326 0.02924 0.02602 -0.0287 1.0000 0.0064
-11.500 -1.0201 0.02699 0.02353 -0.0275 1.0000 0.0065
-11.250 -1.0040 0.02516 0.02149 -0.0265 1.0000 0.0066
-11.000 -0.9858 0.02355 0.01969 -0.0257 1.0000 0.0067
-10.750 -0.9658 0.02215 0.01811 -0.0251 0.9985 0.0069
-10.500 -0.9413 0.02084 0.01662 -0.0251 0.9896 0.0070
-10.250 -0.9185 0.01974 0.01535 -0.0247 0.9815 0.0072
-10.000 -0.9001 0.01886 0.01432 -0.0230 0.9726 0.0074
-9.750 -0.8814 0.01808 0.01340 -0.0212 0.9647 0.0075
-9.500 -0.8640 0.01728 0.01244 -0.0192 0.9577 0.0078
-9.250 -0.8438 0.01638 0.01144 -0.0178 0.9513 0.0083
-9.000 -0.8223 0.01598 0.01099 -0.0165 0.9455 0.0088
-8.750 -0.7980 0.01559 0.01054 -0.0157 0.9400 0.0094
-8.500 -0.7741 0.01521 0.01007 -0.0148 0.9342 0.0101
-8.250 -0.7513 0.01471 0.00954 -0.0138 0.9288 0.0111
-8.000 -0.7247 0.01460 0.00942 -0.0134 0.9229 0.0119
-7.750 -0.6996 0.01437 0.00912 -0.0127 0.9173 0.0127
-7.500 -0.6749 0.01394 0.00863 -0.0120 0.9118 0.0135
-7.250 -0.6478 0.01392 0.00863 -0.0118 0.9059 0.0141
-7.000 -0.6217 0.01388 0.00856 -0.0113 0.9002 0.0148
-6.750 -0.5946 0.01371 0.00834 -0.0110 0.8941 0.0156
-6.500 -0.5680 0.01355 0.00809 -0.0106 0.8880 0.0162
-6.250 -0.5433 0.01299 0.00748 -0.0099 0.8824 0.0170
-6.000 -0.5157 0.01292 0.00742 -0.0098 0.8758 0.0176
-5.750 -0.4890 0.01282 0.00728 -0.0094 0.8696 0.0183
-5.500 -0.4618 0.01257 0.00698 -0.0092 0.8634 0.0191
-5.250 -0.4346 0.01237 0.00671 -0.0089 0.8573 0.0198
-5.000 -0.4086 0.01191 0.00617 -0.0084 0.8519 0.0206
-4.750 -0.3823 0.01138 0.00563 -0.0081 0.8459 0.0215
-4.500 -0.3551 0.01122 0.00545 -0.0079 0.8397 0.0225
-4.250 -0.3272 0.01111 0.00532 -0.0077 0.8321 0.0237
-4.000 -0.2992 0.01111 0.00527 -0.0076 0.8234 0.0248
-3.750 -0.2738 0.01043 0.00455 -0.0070 0.8154 0.0261
-3.500 -0.2470 0.01017 0.00425 -0.0067 0.8077 0.0272
-3.250 -0.2194 0.00996 0.00404 -0.0065 0.7997 0.0284
-2.750 -0.1647 0.00951 0.00350 -0.0060 0.7829 0.0303
-2.500 -0.1372 0.00937 0.00330 -0.0057 0.7749 0.0308
-2.250 -0.1110 0.00889 0.00279 -0.0053 0.7668 0.0323
-2.000 -0.0837 0.00870 0.00255 -0.0050 0.7591 0.0339
-1.750 -0.0557 0.00852 0.00238 -0.0049 0.7509 0.0352
-1.500 -0.0279 0.00840 0.00220 -0.0047 0.7433 0.0365
-1.250 0.0004 0.00827 0.00207 -0.0047 0.7356 0.0378
-1.000 0.0283 0.00813 0.00189 -0.0046 0.7272 0.0392
-0.750 0.0563 0.00796 0.00171 -0.0044 0.7163 0.0431
-0.500 0.0844 0.00784 0.00158 -0.0043 0.7051 0.0504
-0.250 0.1082 0.00716 0.00143 -0.0037 0.6924 0.2253
0.000 0.1270 0.00606 0.00130 -0.0022 0.6762 0.5372
0.250 0.1415 0.00512 0.00122 0.0007 0.6578 0.7980
0.500 0.1742 0.00492 0.00135 0.0001 0.6282 0.9351
0.750 0.2274 0.00550 0.00163 -0.0053 0.5505 0.9663
1.000 0.2737 0.00628 0.00199 -0.0094 0.4537 0.9793
1.250 0.3144 0.00686 0.00222 -0.0123 0.3765 0.9855
1.500 0.3574 0.00728 0.00237 -0.0158 0.3222 0.9881
1.750 0.4012 0.00762 0.00254 -0.0194 0.2899 0.9925
2.000 0.4449 0.00785 0.00263 -0.0229 0.2681 0.9955
2.250 0.4820 0.00799 0.00267 -0.0251 0.2528 0.9970
2.500 0.5159 0.00811 0.00271 -0.0265 0.2401 0.9982
2.750 0.5495 0.00823 0.00276 -0.0279 0.2289 0.9993
3.000 0.5815 0.00836 0.00281 -0.0290 0.2187 1.0000
3.250 0.6078 0.00844 0.00287 -0.0287 0.2117 1.0000
3.500 0.6339 0.00857 0.00294 -0.0285 0.2032 1.0000
3.750 0.6600 0.00866 0.00300 -0.0282 0.1964 1.0000
4.000 0.6860 0.00881 0.00308 -0.0280 0.1882 1.0000
4.250 0.7120 0.00890 0.00317 -0.0277 0.1827 1.0000
4.500 0.7377 0.00904 0.00326 -0.0274 0.1765 1.0000
4.750 0.7634 0.00918 0.00337 -0.0271 0.1710 1.0000
5.000 0.7889 0.00930 0.00348 -0.0267 0.1664 1.0000
5.250 0.8139 0.00947 0.00361 -0.0263 0.1608 1.0000
5.500 0.8388 0.00963 0.00376 -0.0258 0.1564 1.0000
5.750 0.8637 0.00976 0.00389 -0.0253 0.1527 1.0000
6.000 0.8882 0.00994 0.00405 -0.0248 0.1482 1.0000
6.250 0.9124 0.01016 0.00424 -0.0242 0.1431 1.0000
6.500 0.9371 0.01029 0.00439 -0.0237 0.1402 1.0000
6.750 0.9614 0.01047 0.00457 -0.0231 0.1368 1.0000
7.000 0.9852 0.01070 0.00477 -0.0225 0.1332 1.0000
7.250 1.0088 0.01095 0.00503 -0.0218 0.1296 1.0000
7.500 1.0330 0.01111 0.00522 -0.0212 0.1279 1.0000
7.750 1.0569 0.01129 0.00542 -0.0206 0.1255 1.0000
8.000 1.0805 0.01151 0.00564 -0.0199 0.1230 1.0000
8.250 1.1036 0.01177 0.00589 -0.0192 0.1200 1.0000
8.500 1.1260 0.01209 0.00621 -0.0184 0.1164 1.0000
8.750 1.1498 0.01225 0.00641 -0.0177 0.1149 1.0000
9.000 1.1732 0.01243 0.00663 -0.0170 0.1124 1.0000
9.250 1.1959 0.01267 0.00687 -0.0163 0.1092 1.0000
9.500 1.2178 0.01298 0.00717 -0.0154 0.1057 1.0000
9.750 1.2398 0.01326 0.00748 -0.0145 0.1030 1.0000
10.000 1.2626 0.01346 0.00772 -0.0138 0.1009 1.0000
10.250 1.2847 0.01371 0.00800 -0.0129 0.0978 1.0000
10.500 1.3055 0.01405 0.00832 -0.0119 0.0935 1.0000
10.750 1.3267 0.01434 0.00864 -0.0109 0.0900 1.0000
11.000 1.3480 0.01462 0.00893 -0.0100 0.0855 1.0000
11.250 1.3673 0.01504 0.00932 -0.0088 0.0789 1.0000
11.500 1.3861 0.01548 0.00972 -0.0075 0.0707 1.0000
11.750 1.4032 0.01602 0.01023 -0.0061 0.0631 1.0000
12.000 1.4196 0.01659 0.01077 -0.0045 0.0576 1.0000
12.250 1.4360 0.01711 0.01131 -0.0029 0.0545 1.0000
12.500 1.4507 0.01772 0.01193 -0.0011 0.0509 1.0000
12.750 1.4661 0.01823 0.01249 0.0006 0.0487 1.0000
13.000 1.4794 0.01873 0.01304 0.0027 0.0466 1.0000
13.250 1.4881 0.01937 0.01370 0.0055 0.0442 1.0000
13.500 1.4969 0.02015 0.01449 0.0080 0.0412 1.0000
13.750 1.5107 0.02071 0.01512 0.0096 0.0397 1.0000
14.000 1.5236 0.02138 0.01585 0.0112 0.0373 1.0000
14.250 1.5333 0.02232 0.01680 0.0130 0.0342 1.0000
14.500 1.5440 0.02324 0.01776 0.0146 0.0318 1.0000
14.750 1.5534 0.02429 0.01885 0.0161 0.0296 1.0000
15.000 1.5604 0.02556 0.02014 0.0177 0.0273 1.0000
15.250 1.5698 0.02670 0.02134 0.0189 0.0260 1.0000
15.500 1.5775 0.02800 0.02271 0.0201 0.0247 1.0000
15.750 1.5829 0.02955 0.02432 0.0213 0.0235 1.0000
16.000 1.5861 0.03135 0.02619 0.0224 0.0222 1.0000
16.250 1.5895 0.03321 0.02813 0.0232 0.0213 1.0000
16.500 1.5952 0.03491 0.02993 0.0238 0.0208 1.0000
16.750 1.5984 0.03691 0.03202 0.0244 0.0200 1.0000
17.000 1.5988 0.03928 0.03448 0.0247 0.0193 1.0000
17.250 1.5960 0.04208 0.03737 0.0248 0.0186 1.0000
17.500 1.5901 0.04537 0.04075 0.0246 0.0179 1.0000
17.750 1.5809 0.04927 0.04476 0.0239 0.0173 1.0000
18.000 1.5708 0.05356 0.04917 0.0228 0.0169 1.0000
18.250 1.5617 0.05800 0.05375 0.0212 0.0166 1.0000
18.500 1.5468 0.06356 0.05944 0.0189 0.0163 1.0000
18.750 1.5239 0.07065 0.06671 0.0157 0.0162 1.0000
19.000 1.4897 0.07994 0.07619 0.0113 0.0163 1.0000
19.250 1.4313 0.09352 0.09000 0.0049 0.0168 1.0000
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