BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Reynolds number: 500,000 Max Cl/Cd: 77.74 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v43012-il-500000.txt Download as CSV file: xf-v43012-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V43012-1.58 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4167 0.09918 0.09679 -0.0257 1.0000 0.0218
-10.250 -0.4186 0.09452 0.09215 -0.0286 1.0000 0.0218
-10.000 -0.4206 0.09004 0.08769 -0.0300 1.0000 0.0220
-9.750 -0.4213 0.08611 0.08379 -0.0316 1.0000 0.0220
-9.500 -0.4183 0.08344 0.08114 -0.0313 1.0000 0.0221
-9.250 -0.4204 0.07977 0.07750 -0.0330 1.0000 0.0223
-9.000 -0.4355 0.07498 0.07271 -0.0365 1.0000 0.0223
-8.750 -0.4489 0.07224 0.06996 -0.0354 1.0000 0.0224
-8.500 -0.4648 0.06978 0.06749 -0.0326 1.0000 0.0224
-8.250 -0.4732 0.06729 0.06498 -0.0305 1.0000 0.0226
-8.000 -0.4824 0.06478 0.06243 -0.0280 1.0000 0.0227
-7.750 -0.4899 0.06246 0.06008 -0.0251 1.0000 0.0228
-7.500 -0.4962 0.06026 0.05784 -0.0220 1.0000 0.0231
-7.250 -0.4825 0.05671 0.05417 -0.0233 0.9975 0.0237
-7.000 -0.4602 0.05011 0.04697 -0.0259 0.9906 0.0258
-6.750 -0.4350 0.04664 0.04347 -0.0284 0.9863 0.0261
-6.500 -0.4069 0.04383 0.04061 -0.0308 0.9830 0.0264
-6.250 -0.3828 0.04143 0.03812 -0.0318 0.9768 0.0271
-6.000 -0.3522 0.03865 0.03517 -0.0336 0.9725 0.0282
-5.750 -0.3260 0.03491 0.03098 -0.0332 0.9646 0.0304
-5.500 -0.2926 0.03267 0.02869 -0.0356 0.9589 0.0310
-5.250 -0.2650 0.03090 0.02682 -0.0362 0.9464 0.0319
-5.000 -0.2366 0.02851 0.02403 -0.0355 0.9319 0.0354
-4.750 -0.2069 0.02681 0.02227 -0.0366 0.9142 0.0361
-4.500 -0.1792 0.02547 0.02078 -0.0367 0.8894 0.0376
-4.250 -0.1538 0.02393 0.01884 -0.0353 0.8620 0.0412
-4.000 -0.1302 0.02276 0.01755 -0.0347 0.8337 0.0421
-3.750 -0.1073 0.02195 0.01654 -0.0334 0.8025 0.0442
-3.500 -0.0856 0.02094 0.01516 -0.0315 0.7722 0.0479
-3.250 -0.0634 0.02004 0.01413 -0.0304 0.7432 0.0493
-3.000 -0.0385 0.02169 0.01536 -0.0282 0.7142 0.0540
-2.500 0.0060 0.01774 0.01122 -0.0265 0.6617 0.0577
-2.250 0.0365 0.01530 0.00820 -0.0244 0.6400 0.0404
-2.000 0.0624 0.01405 0.00689 -0.0238 0.6169 0.0393
-1.750 0.0877 0.01321 0.00595 -0.0230 0.5934 0.0384
-1.500 0.1115 0.01243 0.00504 -0.0217 0.5708 0.0374
-1.250 0.1340 0.01197 0.00445 -0.0204 0.5485 0.0371
-1.000 0.1568 0.01165 0.00403 -0.0191 0.5245 0.0374
-0.750 0.1793 0.01143 0.00369 -0.0178 0.4961 0.0377
-0.500 0.2015 0.01129 0.00340 -0.0165 0.4562 0.0382
-0.250 0.2236 0.01129 0.00320 -0.0152 0.4197 0.0391
0.000 0.2466 0.01132 0.00308 -0.0141 0.3940 0.0402
0.250 0.2698 0.01123 0.00289 -0.0130 0.3705 0.0411
0.500 0.2936 0.01125 0.00281 -0.0121 0.3459 0.0428
0.750 0.3181 0.01129 0.00275 -0.0112 0.3243 0.0451
1.000 0.3426 0.01134 0.00271 -0.0104 0.3071 0.0484
1.250 0.3670 0.01140 0.00272 -0.0096 0.2934 0.0584
1.500 0.3914 0.01142 0.00273 -0.0088 0.2827 0.0890
1.750 0.3940 0.00978 0.00265 -0.0043 0.2770 0.6461
2.000 0.4067 0.00919 0.00287 -0.0005 0.2707 0.8763
2.250 0.4545 0.00953 0.00323 -0.0043 0.2615 0.9414
2.500 0.5097 0.00989 0.00355 -0.0097 0.2533 0.9629
2.750 0.5571 0.01037 0.00389 -0.0137 0.2457 0.9735
3.000 0.6094 0.01063 0.00412 -0.0186 0.2405 0.9818
3.250 0.6580 0.01086 0.00428 -0.0229 0.2347 0.9864
3.500 0.6996 0.01115 0.00447 -0.0260 0.2294 0.9906
3.750 0.7438 0.01127 0.00458 -0.0294 0.2259 0.9949
4.000 0.7868 0.01135 0.00465 -0.0327 0.2219 0.9983
4.250 0.8191 0.01148 0.00474 -0.0338 0.2183 1.0000
4.500 0.8388 0.01166 0.00487 -0.0324 0.2152 1.0000
4.750 0.8587 0.01183 0.00504 -0.0309 0.2124 1.0000
5.000 0.8795 0.01193 0.00516 -0.0296 0.2100 1.0000
5.250 0.8999 0.01205 0.00529 -0.0282 0.2073 1.0000
5.500 0.9199 0.01219 0.00544 -0.0267 0.2044 1.0000
5.750 0.9393 0.01240 0.00561 -0.0251 0.2014 1.0000
6.000 0.9575 0.01272 0.00589 -0.0234 0.1980 1.0000
6.250 0.9781 0.01283 0.00605 -0.0220 0.1960 1.0000
6.500 0.9984 0.01299 0.00624 -0.0206 0.1932 1.0000
6.750 1.0182 0.01317 0.00644 -0.0191 0.1902 1.0000
7.000 1.0373 0.01341 0.00666 -0.0175 0.1871 1.0000
7.250 1.0546 0.01384 0.00704 -0.0157 0.1832 1.0000
7.500 1.0754 0.01396 0.00724 -0.0144 0.1810 1.0000
7.750 1.0957 0.01414 0.00746 -0.0130 0.1780 1.0000
8.000 1.1155 0.01435 0.00769 -0.0116 0.1747 1.0000
8.250 1.1339 0.01466 0.00798 -0.0099 0.1711 1.0000
8.500 1.1523 0.01502 0.00835 -0.0083 0.1677 1.0000
8.750 1.1727 0.01521 0.00860 -0.0070 0.1648 1.0000
9.000 1.1925 0.01545 0.00888 -0.0056 0.1618 1.0000
9.250 1.2113 0.01574 0.00918 -0.0041 0.1590 1.0000
9.500 1.2281 0.01619 0.00961 -0.0024 0.1560 1.0000
9.750 1.2466 0.01656 0.01002 -0.0008 0.1537 1.0000
10.000 1.2657 0.01686 0.01040 0.0006 0.1517 1.0000
10.250 1.2843 0.01718 0.01078 0.0020 0.1496 1.0000
10.500 1.3025 0.01745 0.01108 0.0035 0.1472 1.0000
10.750 1.3190 0.01780 0.01142 0.0052 0.1443 1.0000
11.000 1.3335 0.01833 0.01195 0.0072 0.1416 1.0000
11.250 1.3494 0.01862 0.01234 0.0091 0.1401 1.0000
11.500 1.3643 0.01895 0.01275 0.0111 0.1384 1.0000
11.750 1.3789 0.01929 0.01315 0.0131 0.1363 1.0000
12.000 1.3930 0.01970 0.01360 0.0151 0.1345 1.0000
12.250 1.4062 0.02018 0.01411 0.0170 0.1327 1.0000
12.500 1.4176 0.02083 0.01477 0.0191 0.1305 1.0000
12.750 1.4306 0.02145 0.01546 0.0208 0.1289 1.0000
13.000 1.4454 0.02191 0.01603 0.0223 0.1273 1.0000
13.250 1.4595 0.02242 0.01664 0.0237 0.1253 1.0000
13.500 1.4726 0.02299 0.01727 0.0251 0.1229 1.0000
13.750 1.4831 0.02375 0.01806 0.0267 0.1203 1.0000
14.000 1.4904 0.02482 0.01914 0.0283 0.1178 1.0000
14.250 1.5034 0.02555 0.02000 0.0294 0.1161 1.0000
14.500 1.5155 0.02636 0.02094 0.0303 0.1139 1.0000
14.750 1.5258 0.02735 0.02201 0.0312 0.1114 1.0000
15.000 1.5328 0.02863 0.02334 0.0322 0.1089 1.0000
15.250 1.5360 0.03031 0.02504 0.0331 0.1065 1.0000
15.500 1.5461 0.03155 0.02644 0.0335 0.1042 1.0000
15.750 1.5551 0.03294 0.02795 0.0337 0.1009 1.0000
16.000 1.5585 0.03491 0.02999 0.0338 0.0978 1.0000
16.250 1.5567 0.03751 0.03263 0.0336 0.0947 1.0000
16.500 1.5657 0.03916 0.03444 0.0334 0.0907 1.0000
16.750 1.5619 0.04226 0.03759 0.0327 0.0854 1.0000
17.000 1.5613 0.04511 0.04055 0.0319 0.0790 1.0000
17.250 1.5487 0.04950 0.04499 0.0305 0.0715 1.0000
17.500 1.5254 0.05544 0.05098 0.0282 0.0650 1.0000
17.750 1.4988 0.06206 0.05770 0.0256 0.0608 1.0000
18.000 1.4679 0.06965 0.06540 0.0223 0.0586 1.0000
18.250 1.4357 0.07754 0.07343 0.0189 0.0570 1.0000
18.500 1.4018 0.08590 0.08192 0.0153 0.0557 1.0000
18.750 1.3686 0.09430 0.09045 0.0116 0.0549 1.0000
19.000 1.3336 0.10316 0.09941 0.0075 0.0536 1.0000
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