BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Reynolds number: 200,000 Max Cl/Cd: 53.55 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v43015-il-200000-n5.txt Download as CSV file: xf-v43015-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4139 0.08968 0.08576 -0.0436 1.0000 0.0322
-11.000 -0.4164 0.08575 0.08186 -0.0448 1.0000 0.0320
-10.750 -0.4282 0.07995 0.07608 -0.0483 1.0000 0.0316
-10.500 -0.4485 0.07438 0.07049 -0.0513 1.0000 0.0310
-10.250 -0.4807 0.06930 0.06534 -0.0525 1.0000 0.0308
-10.000 -0.5105 0.06601 0.06199 -0.0503 1.0000 0.0304
-9.750 -0.5426 0.06382 0.05975 -0.0452 1.0000 0.0302
-9.500 -0.5732 0.06202 0.05790 -0.0389 1.0000 0.0301
-9.250 -0.5950 0.05925 0.05500 -0.0343 0.9992 0.0298
-9.000 -0.5881 0.05468 0.05015 -0.0356 0.9920 0.0298
-8.750 -0.5773 0.05075 0.04596 -0.0361 0.9849 0.0300
-8.500 -0.5634 0.04746 0.04242 -0.0362 0.9779 0.0303
-8.250 -0.5465 0.04402 0.03866 -0.0364 0.9714 0.0313
-8.000 -0.5324 0.04067 0.03496 -0.0354 0.9631 0.0316
-7.750 -0.5108 0.03717 0.03108 -0.0355 0.9572 0.0318
-7.500 -0.4929 0.03399 0.02750 -0.0342 0.9480 0.0320
-7.250 -0.4641 0.03141 0.02460 -0.0349 0.9417 0.0327
-7.000 -0.4369 0.03040 0.02354 -0.0351 0.9316 0.0332
-6.750 -0.4046 0.02891 0.02190 -0.0362 0.9238 0.0339
-6.500 -0.3805 0.02729 0.02007 -0.0354 0.9123 0.0343
-6.250 -0.3473 0.02543 0.01796 -0.0363 0.9047 0.0347
-6.000 -0.3213 0.02395 0.01629 -0.0357 0.8926 0.0351
-5.750 -0.2883 0.02243 0.01454 -0.0363 0.8830 0.0358
-5.500 -0.2572 0.02118 0.01305 -0.0365 0.8706 0.0367
-5.250 -0.2268 0.02040 0.01228 -0.0369 0.8565 0.0374
-5.000 -0.1956 0.01965 0.01148 -0.0373 0.8418 0.0380
-4.750 -0.1645 0.01884 0.01058 -0.0376 0.8244 0.0386
-4.500 -0.1351 0.01811 0.00974 -0.0374 0.8023 0.0392
-4.250 -0.1074 0.01746 0.00897 -0.0370 0.7775 0.0399
-4.000 -0.0817 0.01692 0.00826 -0.0361 0.7498 0.0406
-3.750 -0.0587 0.01647 0.00766 -0.0348 0.7196 0.0414
-3.500 -0.0367 0.01618 0.00728 -0.0333 0.6919 0.0424
-3.250 -0.0152 0.01592 0.00693 -0.0318 0.6662 0.0436
-3.000 0.0057 0.01565 0.00655 -0.0302 0.6428 0.0448
-2.750 0.0260 0.01539 0.00616 -0.0284 0.6190 0.0459
-2.500 0.0456 0.01516 0.00583 -0.0265 0.5951 0.0469
-2.250 0.0655 0.01499 0.00558 -0.0247 0.5710 0.0482
-2.000 0.0856 0.01486 0.00533 -0.0229 0.5467 0.0498
-1.750 0.1061 0.01476 0.00510 -0.0213 0.5238 0.0521
-1.500 0.1270 0.01470 0.00495 -0.0197 0.5026 0.0549
-1.250 0.1484 0.01466 0.00479 -0.0182 0.4826 0.0586
-1.000 0.1700 0.01462 0.00466 -0.0167 0.4636 0.0635
-0.750 0.1917 0.01459 0.00454 -0.0153 0.4456 0.0703
-0.500 0.2135 0.01457 0.00443 -0.0139 0.4286 0.0814
-0.250 0.2348 0.01451 0.00432 -0.0125 0.4134 0.0996
0.000 0.2387 0.01318 0.00408 -0.0083 0.4022 0.4337
0.250 0.2466 0.01248 0.00413 -0.0041 0.3916 0.6237
0.500 0.2642 0.01227 0.00428 -0.0015 0.3802 0.7356
0.750 0.3042 0.01235 0.00466 -0.0031 0.3659 0.8370
1.000 0.3521 0.01273 0.00502 -0.0067 0.3514 0.8818
1.250 0.3888 0.01304 0.00522 -0.0082 0.3389 0.8988
1.500 0.4235 0.01333 0.00540 -0.0094 0.3271 0.9116
1.750 0.4554 0.01360 0.00559 -0.0100 0.3173 0.9249
2.000 0.4937 0.01395 0.00582 -0.0119 0.3071 0.9343
2.250 0.5278 0.01423 0.00604 -0.0130 0.2976 0.9435
2.500 0.5626 0.01454 0.00623 -0.0145 0.2886 0.9499
2.750 0.5920 0.01476 0.00640 -0.0148 0.2810 0.9572
3.000 0.6279 0.01503 0.00658 -0.0165 0.2734 0.9614
3.250 0.6590 0.01528 0.00677 -0.0173 0.2663 0.9679
3.500 0.6926 0.01552 0.00694 -0.0186 0.2585 0.9726
3.750 0.7263 0.01581 0.00713 -0.0200 0.2522 0.9773
4.000 0.7577 0.01604 0.00735 -0.0209 0.2465 0.9828
4.250 0.7931 0.01629 0.00754 -0.0227 0.2413 0.9864
4.500 0.8256 0.01660 0.00777 -0.0240 0.2370 0.9907
4.750 0.8594 0.01683 0.00801 -0.0255 0.2327 0.9945
5.000 0.8936 0.01706 0.00824 -0.0271 0.2279 0.9981
5.250 0.9200 0.01734 0.00847 -0.0272 0.2240 1.0000
5.500 0.9348 0.01764 0.00871 -0.0249 0.2209 1.0000
5.750 0.9512 0.01787 0.00897 -0.0229 0.2182 1.0000
6.000 0.9677 0.01811 0.00924 -0.0209 0.2153 1.0000
6.250 0.9837 0.01837 0.00951 -0.0188 0.2124 1.0000
6.500 0.9991 0.01866 0.00979 -0.0166 0.2096 1.0000
6.750 1.0138 0.01898 0.01010 -0.0144 0.2070 1.0000
7.000 1.0280 0.01937 0.01044 -0.0121 0.2044 1.0000
7.250 1.0439 0.01966 0.01078 -0.0100 0.2020 1.0000
7.500 1.0594 0.01995 0.01113 -0.0079 0.1993 1.0000
7.750 1.0742 0.02027 0.01148 -0.0057 0.1965 1.0000
8.000 1.0882 0.02061 0.01184 -0.0033 0.1938 1.0000
8.250 1.1013 0.02099 0.01220 -0.0009 0.1912 1.0000
8.500 1.1138 0.02143 0.01261 0.0016 0.1888 1.0000
8.750 1.1263 0.02176 0.01301 0.0041 0.1866 1.0000
9.000 1.1383 0.02211 0.01343 0.0068 0.1842 1.0000
9.250 1.1500 0.02249 0.01386 0.0094 0.1818 1.0000
9.500 1.1616 0.02289 0.01431 0.0119 0.1796 1.0000
9.750 1.1730 0.02333 0.01476 0.0143 0.1774 1.0000
10.000 1.1849 0.02384 0.01526 0.0166 0.1755 1.0000
10.250 1.1975 0.02440 0.01583 0.0186 0.1735 1.0000
10.500 1.2103 0.02492 0.01647 0.0206 0.1714 1.0000
10.750 1.2225 0.02548 0.01711 0.0225 0.1691 1.0000
11.000 1.2343 0.02607 0.01777 0.0245 0.1668 1.0000
11.250 1.2457 0.02670 0.01846 0.0263 0.1648 1.0000
11.500 1.2567 0.02738 0.01916 0.0281 0.1629 1.0000
11.750 1.2680 0.02812 0.01991 0.0297 0.1613 1.0000
12.000 1.2793 0.02893 0.02078 0.0313 0.1596 1.0000
12.250 1.2897 0.02979 0.02177 0.0328 0.1578 1.0000
12.500 1.2993 0.03070 0.02278 0.0343 0.1558 1.0000
12.750 1.3083 0.03167 0.02384 0.0357 0.1538 1.0000
13.000 1.3166 0.03267 0.02492 0.0370 0.1519 1.0000
13.250 1.3243 0.03375 0.02604 0.0382 0.1500 1.0000
13.500 1.3326 0.03487 0.02716 0.0392 0.1483 1.0000
13.750 1.3386 0.03623 0.02863 0.0402 0.1465 1.0000
14.000 1.3435 0.03774 0.03029 0.0411 0.1446 1.0000
14.250 1.3484 0.03931 0.03198 0.0418 0.1429 1.0000
14.500 1.3529 0.04097 0.03374 0.0424 0.1412 1.0000
14.750 1.3567 0.04272 0.03558 0.0429 0.1397 1.0000
15.000 1.3603 0.04454 0.03746 0.0432 0.1382 1.0000
15.250 1.3649 0.04631 0.03926 0.0434 0.1367 1.0000
15.500 1.3668 0.04842 0.04146 0.0435 0.1352 1.0000
15.750 1.3620 0.05137 0.04459 0.0432 0.1334 1.0000
16.000 1.3566 0.05448 0.04786 0.0426 0.1314 1.0000
16.250 1.3518 0.05765 0.05116 0.0418 0.1294 1.0000
16.500 1.3473 0.06087 0.05446 0.0408 0.1274 1.0000
16.750 1.3469 0.06362 0.05723 0.0401 0.1255 1.0000
17.000 1.3409 0.06719 0.06088 0.0389 0.1238 1.0000
17.250 1.3230 0.07261 0.06652 0.0367 0.1221 1.0000
17.500 1.3022 0.07862 0.07272 0.0341 0.1201 1.0000
17.750 1.2829 0.08455 0.07880 0.0315 0.1183 1.0000
18.000 1.2686 0.08985 0.08419 0.0292 0.1164 1.0000
18.250 1.2705 0.09261 0.08695 0.0281 0.1148 1.0000
18.500 1.2456 0.09969 0.09417 0.0248 0.1128 1.0000
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Polar data table (+)
Polar graphs
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