BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.22 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v43015-il-1000000.txt Download as CSV file: xf-v43015-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4478 0.08335 0.08160 -0.0421 1.0000 0.0235
-11.000 -0.4962 0.07054 0.06872 -0.0529 1.0000 0.0235
-10.750 -0.5316 0.06532 0.06342 -0.0542 1.0000 0.0235
-10.500 -0.5619 0.06231 0.06035 -0.0517 1.0000 0.0236
-10.250 -0.5987 0.06043 0.05840 -0.0455 1.0000 0.0236
-10.000 -0.6033 0.05837 0.05628 -0.0440 0.9980 0.0238
-9.750 -0.5928 0.05389 0.05165 -0.0467 0.9937 0.0241
-9.500 -0.5819 0.05039 0.04799 -0.0476 0.9885 0.0248
-9.250 -0.6201 0.03487 0.03137 -0.0441 0.9818 0.0264
-9.000 -0.6011 0.03289 0.02930 -0.0438 0.9752 0.0265
-8.750 -0.5781 0.02998 0.02618 -0.0443 0.9715 0.0266
-8.500 -0.5488 0.02838 0.02449 -0.0455 0.9694 0.0268
-8.250 -0.5435 0.02086 0.01621 -0.0425 0.9619 0.0252
-8.000 -0.5144 0.01920 0.01427 -0.0429 0.9576 0.0259
-7.750 -0.4816 0.01841 0.01330 -0.0438 0.9530 0.0261
-7.500 -0.4559 0.01646 0.01119 -0.0436 0.9446 0.0264
-7.250 -0.4223 0.01539 0.01007 -0.0448 0.9385 0.0267
-7.000 -0.3963 0.01477 0.00942 -0.0443 0.9280 0.0270
-6.750 -0.3676 0.01424 0.00885 -0.0444 0.9160 0.0273
-6.500 -0.3405 0.01378 0.00833 -0.0440 0.9007 0.0277
-6.250 -0.3154 0.01333 0.00780 -0.0432 0.8803 0.0280
-6.000 -0.2913 0.01291 0.00729 -0.0421 0.8589 0.0284
-5.750 -0.2681 0.01257 0.00685 -0.0409 0.8372 0.0288
-5.500 -0.2458 0.01230 0.00646 -0.0394 0.8130 0.0293
-5.250 -0.2243 0.01206 0.00609 -0.0378 0.7866 0.0296
-5.000 -0.2025 0.01189 0.00579 -0.0362 0.7603 0.0299
-4.750 -0.1816 0.01163 0.00542 -0.0345 0.7351 0.0300
-4.500 -0.1639 0.01109 0.00479 -0.0323 0.7105 0.0305
-4.250 -0.1437 0.01086 0.00448 -0.0306 0.6857 0.0309
-4.000 -0.1228 0.01068 0.00422 -0.0289 0.6620 0.0314
-3.750 -0.1015 0.01055 0.00400 -0.0273 0.6388 0.0318
-3.500 -0.0796 0.01044 0.00380 -0.0259 0.6158 0.0324
-3.250 -0.0577 0.01032 0.00359 -0.0244 0.5919 0.0329
-3.000 -0.0355 0.01024 0.00342 -0.0230 0.5662 0.0335
-2.750 -0.0127 0.01023 0.00329 -0.0217 0.5409 0.0341
-2.500 0.0082 0.01004 0.00301 -0.0201 0.5163 0.0350
-2.250 0.0308 0.00997 0.00286 -0.0188 0.4924 0.0358
-2.000 0.0540 0.00994 0.00275 -0.0176 0.4699 0.0368
-1.750 0.0776 0.00993 0.00265 -0.0165 0.4492 0.0377
-1.500 0.1017 0.00993 0.00256 -0.0155 0.4306 0.0386
-1.250 0.1251 0.00985 0.00244 -0.0144 0.4139 0.0405
-1.000 0.1495 0.00984 0.00238 -0.0135 0.3983 0.0425
-0.750 0.1739 0.00983 0.00232 -0.0126 0.3837 0.0454
-0.500 0.1981 0.00983 0.00228 -0.0116 0.3700 0.0509
-0.250 0.2225 0.00980 0.00228 -0.0107 0.3579 0.0659
0.000 0.2473 0.00978 0.00227 -0.0099 0.3473 0.0833
0.250 0.2713 0.00978 0.00226 -0.0090 0.3358 0.1008
0.500 0.2785 0.00862 0.00206 -0.0051 0.3290 0.4325
0.750 0.2924 0.00813 0.00204 -0.0022 0.3195 0.5811
1.000 0.3085 0.00785 0.00207 0.0004 0.3108 0.6796
1.250 0.3270 0.00777 0.00212 0.0026 0.3000 0.7369
1.500 0.3474 0.00769 0.00217 0.0044 0.2905 0.7812
1.750 0.3674 0.00766 0.00225 0.0063 0.2800 0.8293
2.000 0.3909 0.00767 0.00238 0.0075 0.2684 0.8810
2.250 0.4220 0.00780 0.00254 0.0071 0.2585 0.9126
2.500 0.4550 0.00802 0.00272 0.0061 0.2486 0.9323
2.750 0.4872 0.00817 0.00284 0.0054 0.2428 0.9420
3.000 0.5198 0.00839 0.00300 0.0045 0.2360 0.9501
3.250 0.5537 0.00860 0.00318 0.0033 0.2306 0.9570
3.500 0.5910 0.00880 0.00335 0.0013 0.2262 0.9600
3.750 0.6264 0.00903 0.00352 -0.0002 0.2217 0.9635
4.000 0.6556 0.00931 0.00375 -0.0004 0.2168 0.9697
4.250 0.6941 0.00949 0.00393 -0.0027 0.2143 0.9709
4.500 0.7306 0.00966 0.00409 -0.0045 0.2114 0.9722
4.750 0.7662 0.00987 0.00426 -0.0062 0.2081 0.9739
5.000 0.8003 0.01010 0.00445 -0.0076 0.2044 0.9761
5.250 0.8303 0.01037 0.00469 -0.0081 0.2006 0.9797
5.500 0.8613 0.01050 0.00484 -0.0088 0.1988 0.9826
5.750 0.8980 0.01065 0.00498 -0.0108 0.1962 0.9836
6.000 0.9334 0.01083 0.00514 -0.0125 0.1931 0.9848
6.250 0.9676 0.01105 0.00532 -0.0141 0.1896 0.9864
6.500 1.0000 0.01133 0.00558 -0.0153 0.1856 0.9884
6.750 1.0329 0.01145 0.00572 -0.0165 0.1839 0.9904
7.000 1.0640 0.01161 0.00589 -0.0173 0.1815 0.9926
7.250 1.0968 0.01178 0.00605 -0.0185 0.1784 0.9940
7.500 1.1303 0.01199 0.00624 -0.0200 0.1748 0.9953
7.750 1.1628 0.01225 0.00647 -0.0214 0.1712 0.9969
8.000 1.1963 0.01237 0.00663 -0.0228 0.1690 0.9983
8.250 1.2293 0.01254 0.00680 -0.0241 0.1659 0.9996
8.500 1.2513 0.01274 0.00699 -0.0233 0.1628 1.0000
8.750 1.2651 0.01301 0.00724 -0.0208 0.1593 1.0000
9.000 1.2807 0.01319 0.00744 -0.0185 0.1571 1.0000
9.250 1.2964 0.01335 0.00764 -0.0163 0.1551 1.0000
9.500 1.3108 0.01355 0.00785 -0.0139 0.1527 1.0000
9.750 1.3236 0.01379 0.00809 -0.0112 0.1503 1.0000
10.000 1.3338 0.01407 0.00836 -0.0080 0.1476 1.0000
10.250 1.3390 0.01431 0.00862 -0.0038 0.1451 1.0000
10.500 1.3493 0.01446 0.00880 -0.0006 0.1434 1.0000
10.750 1.3599 0.01467 0.00903 0.0024 0.1413 1.0000
11.000 1.3708 0.01493 0.00931 0.0053 0.1393 1.0000
11.250 1.3814 0.01527 0.00965 0.0081 0.1365 1.0000
11.500 1.3907 0.01571 0.01009 0.0111 0.1341 1.0000
11.750 1.4050 0.01601 0.01044 0.0131 0.1326 1.0000
12.000 1.4203 0.01632 0.01078 0.0149 0.1309 1.0000
12.250 1.4343 0.01670 0.01120 0.0168 0.1293 1.0000
12.500 1.4479 0.01714 0.01165 0.0187 0.1272 1.0000
12.750 1.4601 0.01768 0.01220 0.0206 0.1251 1.0000
13.000 1.4696 0.01837 0.01290 0.0227 0.1228 1.0000
13.250 1.4839 0.01888 0.01346 0.0242 0.1217 1.0000
13.500 1.4988 0.01938 0.01402 0.0255 0.1207 1.0000
13.750 1.5135 0.01993 0.01462 0.0268 0.1191 1.0000
14.000 1.5266 0.02057 0.01531 0.0281 0.1176 1.0000
14.250 1.5384 0.02133 0.01610 0.0294 0.1161 1.0000
14.500 1.5488 0.02221 0.01701 0.0307 0.1146 1.0000
14.750 1.5565 0.02329 0.01813 0.0321 0.1128 1.0000
15.000 1.5655 0.02437 0.01926 0.0333 0.1113 1.0000
15.250 1.5788 0.02519 0.02015 0.0340 0.1103 1.0000
15.500 1.5907 0.02614 0.02117 0.0348 0.1091 1.0000
15.750 1.6011 0.02724 0.02233 0.0355 0.1076 1.0000
16.000 1.6097 0.02852 0.02365 0.0361 0.1060 1.0000
16.250 1.6154 0.03008 0.02526 0.0367 0.1042 1.0000
16.500 1.6163 0.03211 0.02733 0.0373 0.1021 1.0000
16.750 1.6242 0.03362 0.02892 0.0376 0.1008 1.0000
17.000 1.6335 0.03507 0.03045 0.0377 0.0993 1.0000
17.250 1.6393 0.03686 0.03231 0.0378 0.0974 1.0000
17.500 1.6416 0.03905 0.03455 0.0377 0.0955 1.0000
17.750 1.6390 0.04182 0.03738 0.0375 0.0935 1.0000
18.000 1.6373 0.04461 0.04024 0.0370 0.0915 1.0000
18.250 1.6398 0.04698 0.04269 0.0366 0.0892 1.0000
18.500 1.6355 0.05016 0.04595 0.0359 0.0871 1.0000
18.750 1.6246 0.05421 0.05006 0.0348 0.0845 1.0000
19.000 1.6138 0.05837 0.05430 0.0336 0.0820 1.0000
19.250 1.6025 0.06264 0.05866 0.0322 0.0798 1.0000
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Polar data table (+)
Polar graphs
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