BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Reynolds number: 500,000 Max Cl/Cd: 74.59 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v43015-il-500000.txt Download as CSV file: xf-v43015-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.3979 0.13194 0.12933 -0.0219 1.0000 0.0278
-13.250 -0.3953 0.12827 0.12567 -0.0232 1.0000 0.0286
-13.000 -0.4238 0.11686 0.11426 -0.0326 1.0000 0.0300
-12.750 -0.4167 0.11444 0.11186 -0.0316 1.0000 0.0302
-12.500 -0.4101 0.11199 0.10943 -0.0313 1.0000 0.0303
-12.250 -0.4034 0.10965 0.10710 -0.0312 1.0000 0.0305
-12.000 -0.3989 0.10686 0.10433 -0.0315 1.0000 0.0308
-11.750 -0.3972 0.10350 0.10099 -0.0325 1.0000 0.0311
-11.500 -0.3730 0.07934 0.07696 -0.0508 1.0000 0.0342
-11.250 -0.3546 0.07971 0.07740 -0.0467 1.0000 0.0344
-11.000 -0.3669 0.07384 0.07153 -0.0491 1.0000 0.0345
-10.750 -0.3949 0.06675 0.06439 -0.0527 1.0000 0.0346
-10.500 -0.4351 0.06058 0.05813 -0.0546 1.0000 0.0345
-10.250 -0.4724 0.05662 0.05409 -0.0531 1.0000 0.0345
-10.000 -0.5006 0.05429 0.05172 -0.0494 1.0000 0.0346
-9.750 -0.5417 0.05294 0.05031 -0.0421 1.0000 0.0345
-9.500 -0.5541 0.05081 0.04815 -0.0389 0.9984 0.0346
-9.250 -0.5383 0.04705 0.04433 -0.0410 0.9946 0.0349
-9.000 -0.5233 0.04353 0.04073 -0.0427 0.9899 0.0352
-8.750 -0.5063 0.03999 0.03708 -0.0443 0.9850 0.0358
-8.500 -0.5180 0.03373 0.03008 -0.0419 0.9758 0.0389
-8.250 -0.4914 0.03055 0.02695 -0.0439 0.9724 0.0393
-8.000 -0.4641 0.02799 0.02437 -0.0457 0.9699 0.0397
-7.750 -0.4431 0.02587 0.02218 -0.0459 0.9642 0.0404
-7.500 -0.4304 0.02266 0.01830 -0.0437 0.9572 0.0440
-7.250 -0.4021 0.01996 0.01566 -0.0454 0.9544 0.0445
-7.000 -0.3824 0.01840 0.01407 -0.0447 0.9448 0.0449
-6.750 -0.3555 0.01676 0.01236 -0.0452 0.9386 0.0457
-6.500 -0.3441 0.01543 0.01050 -0.0414 0.9245 0.0497
-6.250 -0.3203 0.01375 0.00887 -0.0415 0.9155 0.0504
-6.000 -0.3180 0.02121 0.01519 -0.0376 0.9241 0.0389
-5.750 -0.2874 0.01953 0.01348 -0.0380 0.9134 0.0383
-5.500 -0.2548 0.01793 0.01173 -0.0385 0.9010 0.0381
-5.250 -0.2261 0.01698 0.01060 -0.0382 0.8849 0.0385
-5.000 -0.1977 0.01609 0.00956 -0.0378 0.8661 0.0388
-4.750 -0.1687 0.01502 0.00840 -0.0377 0.8455 0.0390
-4.500 -0.1421 0.01419 0.00753 -0.0372 0.8238 0.0394
-4.250 -0.1176 0.01370 0.00698 -0.0362 0.8014 0.0399
-4.000 -0.0945 0.01329 0.00648 -0.0349 0.7767 0.0404
-3.500 -0.0509 0.01270 0.00568 -0.0318 0.7261 0.0419
-3.250 -0.0299 0.01246 0.00532 -0.0301 0.7009 0.0428
-3.000 -0.0089 0.01230 0.00502 -0.0283 0.6763 0.0436
-2.750 0.0101 0.01196 0.00459 -0.0263 0.6521 0.0444
-2.500 0.0297 0.01173 0.00429 -0.0244 0.6274 0.0452
-2.250 0.0502 0.01162 0.00407 -0.0227 0.6018 0.0464
-2.000 0.0711 0.01153 0.00387 -0.0210 0.5762 0.0479
-1.750 0.0924 0.01147 0.00369 -0.0194 0.5492 0.0492
-1.500 0.1127 0.01136 0.00348 -0.0177 0.5241 0.0512
-1.250 0.1349 0.01135 0.00339 -0.0163 0.5000 0.0542
-1.000 0.1568 0.01129 0.00325 -0.0149 0.4775 0.0575
-0.750 0.1795 0.01130 0.00317 -0.0136 0.4566 0.0624
-0.500 0.2018 0.01125 0.00309 -0.0123 0.4380 0.0721
-0.250 0.2237 0.01117 0.00298 -0.0109 0.4211 0.0930
0.000 0.2304 0.01004 0.00271 -0.0070 0.4082 0.3965
0.250 0.2344 0.00916 0.00267 -0.0022 0.3962 0.6272
0.500 0.2474 0.00888 0.00273 0.0012 0.3840 0.7317
0.750 0.2660 0.00881 0.00282 0.0035 0.3714 0.7935
1.000 0.2909 0.00881 0.00296 0.0046 0.3588 0.8456
1.250 0.3231 0.00896 0.00316 0.0041 0.3459 0.8870
1.500 0.3618 0.00928 0.00344 0.0022 0.3323 0.9178
1.750 0.3977 0.00964 0.00371 0.0009 0.3188 0.9359
2.000 0.4355 0.00991 0.00391 -0.0009 0.3063 0.9426
2.250 0.4744 0.01021 0.00411 -0.0031 0.2945 0.9474
2.750 0.5474 0.01080 0.00453 -0.0065 0.2731 0.9575
3.000 0.5875 0.01114 0.00477 -0.0090 0.2645 0.9607
3.250 0.6237 0.01139 0.00498 -0.0106 0.2582 0.9666
3.500 0.6581 0.01166 0.00517 -0.0120 0.2518 0.9705
3.750 0.6965 0.01189 0.00536 -0.0143 0.2461 0.9726
4.000 0.7339 0.01210 0.00554 -0.0163 0.2410 0.9756
4.250 0.7665 0.01237 0.00575 -0.0174 0.2360 0.9803
4.500 0.8015 0.01265 0.00597 -0.0190 0.2315 0.9833
4.750 0.8402 0.01279 0.00613 -0.0214 0.2279 0.9855
5.000 0.8768 0.01298 0.00630 -0.0234 0.2239 0.9884
5.250 0.9106 0.01324 0.00650 -0.0249 0.2200 0.9918
5.500 0.9449 0.01355 0.00677 -0.0265 0.2158 0.9945
5.750 0.9820 0.01364 0.00690 -0.0286 0.2129 0.9969
6.000 1.0181 0.01379 0.00705 -0.0306 0.2093 0.9993
6.250 1.0414 0.01398 0.00722 -0.0300 0.2061 1.0000
6.500 1.0563 0.01425 0.00746 -0.0277 0.2029 1.0000
6.750 1.0717 0.01453 0.00773 -0.0255 0.1999 1.0000
7.000 1.0888 0.01466 0.00791 -0.0236 0.1977 1.0000
7.250 1.1053 0.01483 0.00811 -0.0215 0.1951 1.0000
7.500 1.1211 0.01503 0.00832 -0.0194 0.1925 1.0000
7.750 1.1356 0.01528 0.00856 -0.0170 0.1898 1.0000
8.000 1.1482 0.01566 0.00891 -0.0143 0.1867 1.0000
8.250 1.1628 0.01591 0.00920 -0.0119 0.1845 1.0000
8.500 1.1779 0.01609 0.00943 -0.0096 0.1822 1.0000
8.750 1.1919 0.01630 0.00968 -0.0072 0.1797 1.0000
9.000 1.2050 0.01654 0.00994 -0.0046 0.1773 1.0000
9.250 1.2144 0.01682 0.01021 -0.0013 0.1750 1.0000
9.500 1.2205 0.01725 0.01060 0.0026 0.1721 1.0000
9.750 1.2311 0.01748 0.01089 0.0056 0.1702 1.0000
10.000 1.2430 0.01772 0.01119 0.0083 0.1682 1.0000
10.250 1.2552 0.01800 0.01152 0.0109 0.1661 1.0000
10.500 1.2676 0.01834 0.01188 0.0133 0.1640 1.0000
10.750 1.2795 0.01873 0.01228 0.0157 0.1619 1.0000
11.000 1.2907 0.01926 0.01280 0.0181 0.1597 1.0000
11.250 1.3031 0.01978 0.01335 0.0202 0.1574 1.0000
11.500 1.3173 0.02018 0.01382 0.0220 0.1557 1.0000
11.750 1.3312 0.02060 0.01430 0.0237 0.1534 1.0000
12.000 1.3446 0.02108 0.01483 0.0255 0.1514 1.0000
12.250 1.3571 0.02165 0.01543 0.0272 0.1495 1.0000
12.500 1.3684 0.02236 0.01613 0.0289 0.1477 1.0000
12.750 1.3789 0.02320 0.01698 0.0306 0.1454 1.0000
13.000 1.3922 0.02379 0.01767 0.0319 0.1437 1.0000
13.250 1.4048 0.02445 0.01842 0.0331 0.1418 1.0000
13.500 1.4168 0.02520 0.01923 0.0344 0.1398 1.0000
13.750 1.4275 0.02606 0.02013 0.0355 0.1377 1.0000
14.000 1.4365 0.02709 0.02117 0.0367 0.1358 1.0000
14.250 1.4439 0.02833 0.02240 0.0380 0.1336 1.0000
14.500 1.4545 0.02934 0.02354 0.0388 0.1324 1.0000
14.750 1.4643 0.03047 0.02477 0.0395 0.1310 1.0000
15.000 1.4732 0.03170 0.02609 0.0402 0.1293 1.0000
15.250 1.4810 0.03306 0.02752 0.0408 0.1276 1.0000
15.500 1.4876 0.03457 0.02909 0.0412 0.1259 1.0000
15.750 1.4917 0.03634 0.03087 0.0417 0.1240 1.0000
16.000 1.4953 0.03818 0.03273 0.0421 0.1221 1.0000
16.250 1.5005 0.04002 0.03472 0.0421 0.1209 1.0000
16.500 1.5045 0.04205 0.03686 0.0420 0.1193 1.0000
16.750 1.5077 0.04422 0.03913 0.0418 0.1176 1.0000
17.000 1.5090 0.04662 0.04161 0.0414 0.1159 1.0000
17.250 1.5085 0.04926 0.04430 0.0410 0.1142 1.0000
17.500 1.5062 0.05206 0.04711 0.0405 0.1122 1.0000
17.750 1.5039 0.05510 0.05027 0.0397 0.1106 1.0000
18.000 1.5006 0.05840 0.05371 0.0386 0.1089 1.0000
18.250 1.4957 0.06193 0.05737 0.0373 0.1071 1.0000
18.500 1.4887 0.06579 0.06130 0.0359 0.1050 1.0000
18.750 1.4805 0.06977 0.06532 0.0344 0.1032 1.0000
19.000 1.4721 0.07374 0.06934 0.0330 0.1011 1.0000
19.250 1.4598 0.07864 0.07441 0.0309 0.0994 1.0000
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Polar data table (+)
Polar graphs
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