BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Reynolds number: 500,000 Max Cl/Cd: 76.68 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v43015-il-500000-n5.txt Download as CSV file: xf-v43015-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4647 0.08710 0.08451 -0.0428 1.0000 0.0190
-11.750 -0.5568 0.06583 0.06307 -0.0591 1.0000 0.0189
-11.500 -0.5989 0.06011 0.05721 -0.0597 1.0000 0.0190
-11.250 -0.6325 0.05661 0.05360 -0.0567 1.0000 0.0190
-11.000 -0.6490 0.05536 0.05231 -0.0525 1.0000 0.0191
-10.750 -0.6704 0.05381 0.05070 -0.0472 0.9992 0.0191
-10.250 -0.7339 0.03041 0.02552 -0.0432 0.9814 0.0217
-10.000 -0.7141 0.02904 0.02405 -0.0426 0.9763 0.0219
-9.750 -0.6875 0.02822 0.02318 -0.0430 0.9729 0.0220
-9.500 -0.6588 0.02743 0.02233 -0.0438 0.9704 0.0222
-9.250 -0.6370 0.02649 0.02131 -0.0430 0.9644 0.0224
-9.000 -0.6097 0.02549 0.02020 -0.0434 0.9601 0.0227
-8.750 -0.5794 0.02389 0.01842 -0.0444 0.9569 0.0231
-8.500 -0.5544 0.02233 0.01666 -0.0442 0.9485 0.0235
-8.250 -0.5191 0.02063 0.01471 -0.0459 0.9407 0.0240
-8.000 -0.4899 0.01931 0.01318 -0.0462 0.9284 0.0245
-7.750 -0.4584 0.01837 0.01202 -0.0469 0.9177 0.0250
-7.500 -0.4287 0.01755 0.01118 -0.0474 0.9065 0.0253
-7.250 -0.4009 0.01694 0.01051 -0.0473 0.8928 0.0255
-7.000 -0.3734 0.01639 0.00991 -0.0471 0.8783 0.0257
-6.750 -0.3469 0.01589 0.00932 -0.0467 0.8617 0.0260
-6.500 -0.3217 0.01543 0.00878 -0.0459 0.8446 0.0263
-6.250 -0.2976 0.01500 0.00825 -0.0450 0.8248 0.0266
-6.000 -0.2748 0.01462 0.00773 -0.0437 0.7994 0.0269
-5.750 -0.2533 0.01431 0.00727 -0.0421 0.7710 0.0274
-5.500 -0.2323 0.01401 0.00683 -0.0405 0.7431 0.0277
-5.250 -0.2119 0.01377 0.00643 -0.0387 0.7144 0.0281
-5.000 -0.1910 0.01359 0.00610 -0.0370 0.6877 0.0284
-4.750 -0.1715 0.01331 0.00571 -0.0352 0.6596 0.0288
-4.500 -0.1515 0.01312 0.00542 -0.0334 0.6339 0.0292
-4.250 -0.1308 0.01294 0.00516 -0.0318 0.6094 0.0296
-4.000 -0.1099 0.01278 0.00490 -0.0301 0.5851 0.0299
-3.750 -0.0888 0.01265 0.00467 -0.0286 0.5606 0.0304
-3.500 -0.0675 0.01252 0.00444 -0.0270 0.5378 0.0308
-3.250 -0.0460 0.01241 0.00422 -0.0255 0.5160 0.0313
-3.000 -0.0240 0.01231 0.00403 -0.0242 0.4946 0.0319
-2.750 -0.0017 0.01223 0.00384 -0.0228 0.4743 0.0324
-2.500 0.0202 0.01212 0.00367 -0.0214 0.4546 0.0330
-2.250 0.0428 0.01206 0.00354 -0.0202 0.4356 0.0339
-2.000 0.0658 0.01202 0.00343 -0.0190 0.4183 0.0350
-1.750 0.0892 0.01199 0.00332 -0.0179 0.4019 0.0360
-1.500 0.1129 0.01193 0.00322 -0.0169 0.3889 0.0371
-1.250 0.1365 0.01190 0.00313 -0.0158 0.3769 0.0385
-1.000 0.1605 0.01187 0.00306 -0.0148 0.3649 0.0404
-0.750 0.1847 0.01184 0.00301 -0.0139 0.3546 0.0429
-0.250 0.2329 0.01182 0.00296 -0.0120 0.3337 0.0561
0.000 0.2568 0.01184 0.00297 -0.0111 0.3234 0.0710
0.250 0.2814 0.01185 0.00296 -0.0103 0.3137 0.0824
0.500 0.3052 0.01186 0.00296 -0.0093 0.3049 0.0960
0.750 0.3193 0.01110 0.00282 -0.0068 0.2979 0.3356
1.000 0.3307 0.01041 0.00278 -0.0036 0.2905 0.5318
1.250 0.3455 0.01008 0.00283 -0.0008 0.2837 0.6406
1.500 0.3613 0.00987 0.00290 0.0019 0.2753 0.7255
1.750 0.3792 0.00973 0.00301 0.0043 0.2676 0.8001
2.000 0.4058 0.00973 0.00318 0.0049 0.2592 0.8551
2.250 0.4377 0.00989 0.00334 0.0043 0.2515 0.8850
2.500 0.4718 0.01008 0.00351 0.0031 0.2431 0.9040
2.750 0.5087 0.01034 0.00371 0.0012 0.2353 0.9201
3.000 0.5468 0.01056 0.00390 -0.0009 0.2296 0.9306
3.250 0.5758 0.01077 0.00406 -0.0010 0.2247 0.9407
3.500 0.6163 0.01106 0.00429 -0.0037 0.2198 0.9468
3.750 0.6445 0.01124 0.00446 -0.0037 0.2164 0.9562
4.000 0.6805 0.01147 0.00465 -0.0054 0.2126 0.9588
4.250 0.7137 0.01171 0.00485 -0.0066 0.2091 0.9621
4.500 0.7429 0.01195 0.00506 -0.0070 0.2059 0.9671
4.750 0.7723 0.01217 0.00526 -0.0074 0.2032 0.9712
5.000 0.8065 0.01236 0.00545 -0.0088 0.2007 0.9734
5.250 0.8389 0.01256 0.00565 -0.0098 0.1978 0.9761
5.500 0.8685 0.01279 0.00585 -0.0104 0.1949 0.9797
5.750 0.8972 0.01303 0.00608 -0.0107 0.1920 0.9831
6.000 0.9295 0.01331 0.00633 -0.0119 0.1888 0.9851
6.250 0.9620 0.01350 0.00653 -0.0131 0.1865 0.9873
6.500 0.9931 0.01370 0.00674 -0.0140 0.1836 0.9898
6.750 1.0227 0.01394 0.00698 -0.0146 0.1805 0.9925
7.000 1.0532 0.01419 0.00722 -0.0155 0.1775 0.9946
7.250 1.0839 0.01449 0.00749 -0.0165 0.1745 0.9968
7.500 1.1156 0.01471 0.00774 -0.0176 0.1722 0.9987
7.750 1.1448 0.01493 0.00799 -0.0182 0.1696 1.0000
8.000 1.1595 0.01514 0.00821 -0.0158 0.1672 1.0000
8.250 1.1732 0.01537 0.00845 -0.0133 0.1647 1.0000
8.500 1.1858 0.01563 0.00870 -0.0106 0.1624 1.0000
8.750 1.1968 0.01590 0.00897 -0.0075 0.1602 1.0000
9.000 1.2070 0.01609 0.00921 -0.0043 0.1586 1.0000
9.250 1.2172 0.01630 0.00945 -0.0011 0.1566 1.0000
9.500 1.2281 0.01654 0.00972 0.0018 0.1544 1.0000
9.750 1.2392 0.01683 0.01002 0.0047 0.1520 1.0000
10.000 1.2503 0.01717 0.01037 0.0074 0.1497 1.0000
10.250 1.2616 0.01756 0.01076 0.0100 0.1475 1.0000
10.500 1.2756 0.01790 0.01115 0.0120 0.1459 1.0000
10.750 1.2895 0.01827 0.01157 0.0141 0.1440 1.0000
11.000 1.3030 0.01869 0.01202 0.0160 0.1421 1.0000
11.250 1.3161 0.01916 0.01252 0.0180 0.1401 1.0000
11.500 1.3281 0.01971 0.01308 0.0199 0.1377 1.0000
11.750 1.3394 0.02033 0.01371 0.0219 0.1356 1.0000
12.000 1.3539 0.02083 0.01428 0.0233 0.1337 1.0000
12.250 1.3673 0.02142 0.01492 0.0248 0.1319 1.0000
12.500 1.3797 0.02208 0.01562 0.0263 0.1300 1.0000
12.750 1.3912 0.02283 0.01641 0.0278 0.1283 1.0000
13.000 1.4016 0.02368 0.01729 0.0293 0.1264 1.0000
13.250 1.4101 0.02469 0.01832 0.0307 0.1245 1.0000
13.500 1.4225 0.02551 0.01923 0.0318 0.1233 1.0000
13.750 1.4338 0.02644 0.02022 0.0328 0.1215 1.0000
14.000 1.4439 0.02749 0.02133 0.0337 0.1193 1.0000
14.250 1.4523 0.02871 0.02259 0.0346 0.1174 1.0000
14.500 1.4585 0.03015 0.02408 0.0355 0.1156 1.0000
14.750 1.4627 0.03182 0.02578 0.0363 0.1139 1.0000
15.000 1.4716 0.03316 0.02722 0.0367 0.1129 1.0000
15.250 1.4795 0.03465 0.02880 0.0371 0.1116 1.0000
15.500 1.4860 0.03631 0.03055 0.0374 0.1104 1.0000
15.750 1.4910 0.03816 0.03248 0.0376 0.1090 1.0000
16.000 1.4934 0.04033 0.03472 0.0376 0.1074 1.0000
16.250 1.4945 0.04270 0.03716 0.0375 0.1062 1.0000
16.500 1.4925 0.04549 0.04001 0.0372 0.1047 1.0000
16.750 1.4903 0.04834 0.04295 0.0368 0.1035 1.0000
17.000 1.4927 0.05081 0.04553 0.0363 0.1021 1.0000
17.250 1.4923 0.05362 0.04845 0.0356 0.1007 1.0000
17.500 1.4894 0.05680 0.05172 0.0348 0.0992 1.0000
17.750 1.4842 0.06031 0.05532 0.0337 0.0977 1.0000
18.000 1.4750 0.06441 0.05950 0.0324 0.0962 1.0000
18.250 1.4629 0.06895 0.06413 0.0308 0.0948 1.0000
18.500 1.4547 0.07303 0.06831 0.0294 0.0934 1.0000
18.750 1.4467 0.07716 0.07256 0.0279 0.0918 1.0000
19.000 1.4354 0.08181 0.07732 0.0261 0.0900 1.0000
19.250 1.4205 0.08701 0.08260 0.0240 0.0881 1.0000
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