BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Reynolds number: 200,000 Max Cl/Cd: 50.53 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v43012-il-200000.txt Download as CSV file: xf-v43012-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3956 0.08514 0.08162 -0.0284 1.0000 0.0431
-8.750 -0.4037 0.08095 0.07748 -0.0312 1.0000 0.0438
-8.500 -0.4186 0.07707 0.07362 -0.0330 1.0000 0.0441
-8.250 -0.4365 0.07428 0.07084 -0.0315 1.0000 0.0445
-8.000 -0.4491 0.07138 0.06790 -0.0302 1.0000 0.0452
-7.750 -0.4738 0.06954 0.06581 -0.0274 1.0000 0.0463
-7.500 -0.4975 0.06903 0.06490 -0.0223 1.0000 0.0466
-7.250 -0.4879 0.06376 0.05983 -0.0216 1.0000 0.0470
-7.000 -0.4831 0.06060 0.05676 -0.0198 1.0000 0.0475
-6.750 -0.4813 0.05818 0.05436 -0.0173 1.0000 0.0481
-6.500 -0.4808 0.05603 0.05219 -0.0145 1.0000 0.0488
-6.250 -0.4808 0.05405 0.05015 -0.0115 1.0000 0.0500
-6.000 -0.4807 0.05224 0.04824 -0.0083 1.0000 0.0514
-5.750 -0.4463 0.04898 0.04440 -0.0113 0.9925 0.0549
-5.500 -0.4133 0.04505 0.04052 -0.0147 0.9862 0.0566
-5.250 -0.3709 0.04654 0.04119 -0.0162 0.9759 0.0628
-5.000 -0.3381 0.03960 0.03443 -0.0201 0.9712 0.0643
-4.750 -0.3068 0.03662 0.03143 -0.0220 0.9618 0.0666
-4.250 -0.2334 0.03217 0.02643 -0.0256 0.9449 0.0756
-4.000 -0.1971 0.03019 0.02434 -0.0273 0.9344 0.0814
-3.750 -0.1295 0.01206 0.00633 -0.0329 0.8968 0.0912
-3.500 -0.1022 0.01067 0.00464 -0.0323 0.8780 0.1003
-3.250 -0.0754 0.00954 0.00339 -0.0320 0.8584 0.1075
-3.000 -0.0520 0.00829 0.00198 -0.0312 0.8370 0.1190
-2.750 -0.0291 0.00735 0.00087 -0.0302 0.8140 0.1355
-2.500 -0.0068 0.01969 0.01282 -0.0304 0.8283 0.1496
-2.250 0.0197 0.01848 0.01143 -0.0296 0.8022 0.1629
-2.000 0.0494 0.01750 0.01027 -0.0289 0.7764 0.1646
-1.750 0.0964 0.01749 0.00956 -0.0272 0.7511 0.0667
-1.500 0.1242 0.01706 0.00883 -0.0259 0.7242 0.0623
-1.250 0.1501 0.01626 0.00794 -0.0250 0.6959 0.0617
-1.000 0.1748 0.01596 0.00744 -0.0237 0.6676 0.0631
-0.750 0.1987 0.01532 0.00671 -0.0225 0.6387 0.0635
-0.500 0.2211 0.01481 0.00613 -0.0210 0.6090 0.0639
-0.250 0.2423 0.01443 0.00566 -0.0194 0.5789 0.0651
0.000 0.2629 0.01420 0.00530 -0.0176 0.5470 0.0671
0.250 0.2832 0.01404 0.00501 -0.0159 0.5119 0.0697
0.500 0.3034 0.01394 0.00472 -0.0141 0.4712 0.0742
0.750 0.3232 0.01393 0.00447 -0.0123 0.4342 0.0823
1.000 0.3434 0.01392 0.00421 -0.0106 0.4068 0.0998
1.250 0.4381 0.01272 0.00530 -0.0221 0.3671 0.9698
1.500 0.5492 0.01333 0.00552 -0.0388 0.3377 0.9967
1.750 0.5821 0.01352 0.00551 -0.0401 0.3265 1.0000
2.000 0.6022 0.01367 0.00559 -0.0387 0.3177 1.0000
2.250 0.6219 0.01391 0.00569 -0.0373 0.3101 1.0000
2.500 0.6421 0.01406 0.00579 -0.0360 0.3020 1.0000
2.750 0.6620 0.01437 0.00592 -0.0346 0.2952 1.0000
3.000 0.6824 0.01451 0.00607 -0.0333 0.2885 1.0000
3.250 0.7026 0.01475 0.00622 -0.0319 0.2824 1.0000
3.500 0.7233 0.01511 0.00648 -0.0307 0.2778 1.0000
3.750 0.7438 0.01533 0.00672 -0.0293 0.2731 1.0000
4.000 0.7644 0.01560 0.00697 -0.0280 0.2687 1.0000
4.250 0.7852 0.01597 0.00725 -0.0268 0.2645 1.0000
4.500 0.8062 0.01638 0.00762 -0.0256 0.2605 1.0000
4.750 0.8265 0.01664 0.00794 -0.0242 0.2562 1.0000
5.000 0.8471 0.01694 0.00823 -0.0229 0.2519 1.0000
5.250 0.8680 0.01733 0.00855 -0.0217 0.2479 1.0000
5.500 0.8890 0.01782 0.00902 -0.0205 0.2439 1.0000
5.750 0.9089 0.01810 0.00940 -0.0190 0.2398 1.0000
6.000 0.9293 0.01843 0.00974 -0.0177 0.2358 1.0000
6.250 0.9504 0.01881 0.01009 -0.0166 0.2321 1.0000
6.500 0.9722 0.01944 0.01067 -0.0156 0.2284 1.0000
6.750 0.9911 0.01973 0.01110 -0.0140 0.2245 1.0000
7.000 1.0111 0.02009 0.01151 -0.0127 0.2205 1.0000
7.250 1.0320 0.02046 0.01186 -0.0115 0.2169 1.0000
7.500 1.0546 0.02119 0.01250 -0.0108 0.2133 1.0000
7.750 1.0725 0.02156 0.01305 -0.0091 0.2098 1.0000
8.000 1.0918 0.02199 0.01358 -0.0077 0.2059 1.0000
8.250 1.1124 0.02243 0.01403 -0.0065 0.2026 1.0000
8.500 1.1346 0.02302 0.01456 -0.0058 0.1996 1.0000
8.750 1.1540 0.02380 0.01544 -0.0046 0.1965 1.0000
9.000 1.1712 0.02436 0.01615 -0.0029 0.1932 1.0000
9.250 1.1900 0.02493 0.01683 -0.0016 0.1902 1.0000
9.500 1.2102 0.02552 0.01745 -0.0005 0.1877 1.0000
9.750 1.2318 0.02619 0.01811 0.0003 0.1855 1.0000
10.000 1.2543 0.02747 0.01939 0.0006 0.1831 1.0000
10.250 1.2689 0.02824 0.02039 0.0025 0.1814 1.0000
10.500 1.2839 0.02915 0.02150 0.0042 0.1795 1.0000
10.750 1.2993 0.03012 0.02264 0.0058 0.1776 1.0000
11.000 1.3146 0.03108 0.02376 0.0073 0.1757 1.0000
11.250 1.3307 0.03193 0.02473 0.0087 0.1739 1.0000
11.500 1.3496 0.03254 0.02537 0.0097 0.1719 1.0000
11.750 1.3739 0.03328 0.02603 0.0097 0.1694 1.0000
12.000 1.3815 0.03432 0.02728 0.0122 0.1672 1.0000
12.250 1.3866 0.03509 0.02828 0.0150 0.1646 1.0000
12.500 1.3949 0.03575 0.02909 0.0173 0.1620 1.0000
12.750 1.4061 0.03626 0.02969 0.0193 0.1597 1.0000
13.000 1.4266 0.03627 0.02965 0.0201 0.1572 1.0000
13.250 1.4496 0.03717 0.03049 0.0201 0.1548 1.0000
13.500 1.4410 0.03827 0.03185 0.0245 0.1535 1.0000
13.750 1.4325 0.03958 0.03339 0.0285 0.1518 1.0000
14.000 1.4258 0.04099 0.03499 0.0315 0.1500 1.0000
14.250 1.4226 0.04237 0.03653 0.0338 0.1482 1.0000
14.500 1.4284 0.04310 0.03734 0.0353 0.1460 1.0000
14.750 1.4578 0.04244 0.03654 0.0354 0.1432 1.0000
15.000 1.4579 0.04399 0.03820 0.0368 0.1411 1.0000
15.250 1.4364 0.04689 0.04138 0.0386 0.1396 1.0000
15.500 1.4142 0.05043 0.04517 0.0393 0.1379 1.0000
15.750 1.3946 0.05425 0.04918 0.0390 0.1361 1.0000
16.000 1.4060 0.05486 0.04980 0.0390 0.1331 1.0000
16.250 1.4431 0.05290 0.04764 0.0398 0.1290 1.0000
16.500 1.4094 0.05877 0.05381 0.0382 0.1278 1.0000
16.750 1.3652 0.06682 0.06215 0.0349 0.1268 1.0000
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Polar data table (+)
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