BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.95 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v43015-il-1000000-n5.txt Download as CSV file: xf-v43015-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V43015-2.48 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9687 0.03979 0.03659 -0.0732 1.0000 0.0170
-14.500 -0.9660 0.03840 0.03513 -0.0716 1.0000 0.0172
-14.250 -0.9962 0.03389 0.03027 -0.0680 1.0000 0.0174
-14.000 -1.0059 0.03163 0.02780 -0.0644 1.0000 0.0176
-13.750 -1.0066 0.03029 0.02633 -0.0611 1.0000 0.0178
-13.500 -1.0108 0.02885 0.02474 -0.0570 1.0000 0.0180
-13.250 -1.0158 0.02766 0.02341 -0.0522 1.0000 0.0181
-13.000 -1.0199 0.02684 0.02248 -0.0471 1.0000 0.0182
-12.750 -0.9990 0.02548 0.02097 -0.0470 0.9983 0.0184
-12.500 -0.9756 0.02439 0.01975 -0.0471 0.9958 0.0185
-12.250 -0.9516 0.02342 0.01866 -0.0470 0.9928 0.0186
-12.000 -0.9303 0.02227 0.01742 -0.0465 0.9893 0.0188
-11.750 -0.9048 0.02138 0.01646 -0.0466 0.9864 0.0189
-11.500 -0.8770 0.02073 0.01578 -0.0470 0.9841 0.0191
-11.250 -0.8491 0.02014 0.01516 -0.0473 0.9819 0.0192
-11.000 -0.8257 0.01963 0.01462 -0.0466 0.9775 0.0193
-10.750 -0.7980 0.01921 0.01419 -0.0467 0.9742 0.0195
-10.500 -0.7686 0.01858 0.01350 -0.0472 0.9718 0.0197
-10.250 -0.7365 0.01814 0.01304 -0.0482 0.9698 0.0199
-10.000 -0.7106 0.01754 0.01239 -0.0480 0.9645 0.0201
-9.750 -0.6787 0.01693 0.01172 -0.0489 0.9608 0.0203
-9.500 -0.6434 0.01627 0.01100 -0.0506 0.9569 0.0205
-9.250 -0.6095 0.01566 0.01032 -0.0518 0.9464 0.0208
-9.000 -0.5733 0.01506 0.00964 -0.0536 0.9319 0.0210
-8.750 -0.5428 0.01455 0.00903 -0.0541 0.9134 0.0212
-8.500 -0.5169 0.01420 0.00859 -0.0536 0.8972 0.0214
-8.250 -0.4930 0.01391 0.00821 -0.0526 0.8791 0.0216
-8.000 -0.4713 0.01354 0.00773 -0.0512 0.8593 0.0217
-7.750 -0.4512 0.01312 0.00723 -0.0495 0.8402 0.0220
-7.500 -0.4308 0.01282 0.00686 -0.0479 0.8210 0.0221
-7.250 -0.4103 0.01257 0.00652 -0.0461 0.8009 0.0223
-7.000 -0.3903 0.01237 0.00623 -0.0443 0.7756 0.0225
-6.750 -0.3704 0.01222 0.00596 -0.0425 0.7488 0.0227
-6.500 -0.3509 0.01208 0.00570 -0.0405 0.7152 0.0228
-6.250 -0.3306 0.01194 0.00544 -0.0388 0.6873 0.0230
-6.000 -0.3094 0.01178 0.00518 -0.0372 0.6641 0.0232
-5.750 -0.2880 0.01165 0.00496 -0.0356 0.6390 0.0235
-5.500 -0.2666 0.01152 0.00472 -0.0341 0.6145 0.0238
-5.250 -0.2450 0.01140 0.00449 -0.0326 0.5892 0.0240
-5.000 -0.2234 0.01131 0.00429 -0.0311 0.5590 0.0243
-4.750 -0.2013 0.01121 0.00408 -0.0297 0.5347 0.0245
-4.500 -0.1783 0.01113 0.00391 -0.0285 0.5126 0.0248
-4.250 -0.1553 0.01104 0.00373 -0.0273 0.4917 0.0251
-4.000 -0.1330 0.01090 0.00352 -0.0260 0.4718 0.0254
-3.750 -0.1099 0.01080 0.00336 -0.0248 0.4530 0.0258
-3.500 -0.0864 0.01074 0.00323 -0.0237 0.4349 0.0261
-3.250 -0.0627 0.01069 0.00311 -0.0226 0.4166 0.0264
-3.000 -0.0388 0.01065 0.00300 -0.0216 0.3993 0.0269
-2.750 -0.0145 0.01059 0.00288 -0.0206 0.3849 0.0273
-2.500 0.0102 0.01054 0.00279 -0.0197 0.3732 0.0277
-2.250 0.0348 0.01051 0.00270 -0.0188 0.3616 0.0282
-2.000 0.0598 0.01045 0.00261 -0.0180 0.3515 0.0287
-1.750 0.0843 0.01041 0.00253 -0.0171 0.3415 0.0293
-1.500 0.1095 0.01037 0.00247 -0.0163 0.3323 0.0301
-1.250 0.1345 0.01036 0.00243 -0.0155 0.3227 0.0311
-1.000 0.1598 0.01035 0.00238 -0.0148 0.3130 0.0322
-0.750 0.1847 0.01035 0.00235 -0.0140 0.3039 0.0336
-0.500 0.2101 0.01033 0.00232 -0.0133 0.2956 0.0352
-0.250 0.2350 0.01035 0.00231 -0.0125 0.2868 0.0379
0.000 0.2603 0.01034 0.00230 -0.0118 0.2786 0.0437
0.250 0.2849 0.01035 0.00232 -0.0110 0.2697 0.0567
0.500 0.3101 0.01036 0.00234 -0.0103 0.2611 0.0703
0.750 0.3348 0.01041 0.00237 -0.0095 0.2511 0.0799
1.000 0.3596 0.01045 0.00239 -0.0087 0.2425 0.0894
1.250 0.3837 0.01045 0.00241 -0.0078 0.2351 0.1152
1.500 0.3920 0.00941 0.00230 -0.0042 0.2310 0.4548
1.750 0.4092 0.00909 0.00232 -0.0020 0.2255 0.5691
2.000 0.4262 0.00886 0.00238 0.0003 0.2204 0.6628
2.250 0.4456 0.00874 0.00245 0.0023 0.2166 0.7225
2.500 0.4648 0.00865 0.00252 0.0043 0.2129 0.7748
2.750 0.4853 0.00861 0.00261 0.0060 0.2095 0.8156
3.000 0.5079 0.00864 0.00271 0.0073 0.2060 0.8470
3.250 0.5334 0.00867 0.00284 0.0080 0.2034 0.8815
3.500 0.5626 0.00874 0.00297 0.0079 0.2015 0.9054
3.750 0.5972 0.00887 0.00313 0.0065 0.1989 0.9253
4.000 0.6314 0.00903 0.00328 0.0052 0.1961 0.9366
4.250 0.6690 0.00923 0.00346 0.0031 0.1929 0.9457
4.500 0.7006 0.00942 0.00363 0.0023 0.1898 0.9556
4.750 0.7383 0.00960 0.00380 0.0001 0.1877 0.9588
5.000 0.7741 0.00977 0.00395 -0.0016 0.1856 0.9617
5.250 0.8045 0.00994 0.00411 -0.0022 0.1832 0.9661
5.500 0.8315 0.01011 0.00426 -0.0021 0.1803 0.9707
5.750 0.8644 0.01033 0.00445 -0.0033 0.1768 0.9723
6.000 0.8960 0.01054 0.00464 -0.0042 0.1738 0.9742
6.250 0.9268 0.01071 0.00481 -0.0049 0.1720 0.9764
6.500 0.9555 0.01088 0.00499 -0.0052 0.1698 0.9793
6.750 0.9808 0.01107 0.00516 -0.0048 0.1671 0.9826
7.000 1.0127 0.01129 0.00536 -0.0059 0.1638 0.9838
7.250 1.0437 0.01153 0.00558 -0.0069 0.1605 0.9852
7.500 1.0745 0.01172 0.00578 -0.0077 0.1585 0.9867
7.750 1.1043 0.01193 0.00599 -0.0084 0.1558 0.9885
8.000 1.1328 0.01217 0.00622 -0.0088 0.1527 0.9906
8.250 1.1597 0.01244 0.00647 -0.0089 0.1493 0.9927
8.500 1.1886 0.01269 0.00672 -0.0095 0.1468 0.9943
8.750 1.2188 0.01292 0.00696 -0.0103 0.1440 0.9958
9.000 1.2486 0.01318 0.00722 -0.0112 0.1411 0.9973
9.250 1.2784 0.01350 0.00751 -0.0121 0.1374 0.9988
9.500 1.3094 0.01379 0.00781 -0.0132 0.1350 0.9999
9.750 1.3229 0.01400 0.00804 -0.0106 0.1332 1.0000
10.000 1.3303 0.01418 0.00824 -0.0068 0.1315 1.0000
10.250 1.3382 0.01440 0.00847 -0.0032 0.1293 1.0000
10.500 1.3474 0.01467 0.00875 0.0001 0.1271 1.0000
10.750 1.3576 0.01499 0.00907 0.0031 0.1245 1.0000
11.000 1.3707 0.01526 0.00937 0.0055 0.1233 1.0000
11.250 1.3841 0.01557 0.00971 0.0077 0.1215 1.0000
11.500 1.3976 0.01590 0.01007 0.0099 0.1204 1.0000
11.750 1.4103 0.01632 0.01049 0.0121 0.1178 1.0000
12.000 1.4227 0.01679 0.01097 0.0142 0.1155 1.0000
12.250 1.4357 0.01727 0.01147 0.0161 0.1138 1.0000
12.500 1.4509 0.01768 0.01192 0.0176 0.1126 1.0000
12.750 1.4654 0.01815 0.01243 0.0192 0.1116 1.0000
13.000 1.4795 0.01866 0.01298 0.0207 0.1100 1.0000
13.250 1.4926 0.01925 0.01360 0.0222 0.1085 1.0000
13.500 1.5055 0.01989 0.01427 0.0236 0.1071 1.0000
13.750 1.5168 0.02064 0.01505 0.0251 0.1052 1.0000
14.000 1.5280 0.02145 0.01589 0.0265 0.1040 1.0000
14.250 1.5412 0.02216 0.01666 0.0276 0.1030 1.0000
14.500 1.5543 0.02292 0.01747 0.0286 0.1020 1.0000
14.750 1.5663 0.02377 0.01838 0.0296 0.1009 1.0000
15.000 1.5773 0.02473 0.01939 0.0306 0.0994 1.0000
15.250 1.5870 0.02582 0.02053 0.0315 0.0979 1.0000
15.500 1.5954 0.02705 0.02180 0.0323 0.0965 1.0000
15.750 1.6023 0.02846 0.02325 0.0331 0.0949 1.0000
16.000 1.6103 0.02983 0.02469 0.0337 0.0937 1.0000
16.250 1.6191 0.03118 0.02611 0.0341 0.0925 1.0000
16.500 1.6259 0.03275 0.02775 0.0345 0.0908 1.0000
16.750 1.6308 0.03456 0.02961 0.0347 0.0888 1.0000
17.000 1.6326 0.03671 0.03181 0.0349 0.0869 1.0000
17.250 1.6332 0.03906 0.03423 0.0349 0.0847 1.0000
17.500 1.6347 0.04141 0.03665 0.0347 0.0828 1.0000
17.750 1.6328 0.04419 0.03949 0.0344 0.0803 1.0000
18.000 1.6239 0.04780 0.04315 0.0337 0.0772 1.0000
18.250 1.6166 0.05137 0.04680 0.0329 0.0748 1.0000
18.500 1.6035 0.05572 0.05122 0.0318 0.0720 1.0000
18.750 1.5866 0.06066 0.05625 0.0304 0.0700 1.0000
19.000 1.5699 0.06569 0.06137 0.0287 0.0680 1.0000
19.250 1.5483 0.07149 0.06727 0.0268 0.0662 1.0000
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