P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Reynolds number: 200,000 Max Cl/Cd: 57.62 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51droot-il-200000-n5.txt Download as CSV file: xf-p51droot-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: P-51D ROOT (BL17.5) 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8276 0.09130 0.08664 -0.0532 1.0000 0.0320
-16.500 -0.8636 0.08140 0.07645 -0.0593 1.0000 0.0321
-16.250 -0.8884 0.07421 0.06901 -0.0633 1.0000 0.0323
-16.000 -0.9076 0.06840 0.06297 -0.0661 1.0000 0.0325
-15.750 -0.9230 0.06351 0.05785 -0.0681 1.0000 0.0328
-15.500 -0.9354 0.05930 0.05340 -0.0695 1.0000 0.0331
-15.250 -0.9458 0.05559 0.04945 -0.0705 1.0000 0.0335
-15.000 -0.9427 0.05329 0.04709 -0.0708 1.0000 0.0338
-14.750 -0.9381 0.05132 0.04509 -0.0711 1.0000 0.0343
-14.500 -0.9344 0.04926 0.04297 -0.0712 1.0000 0.0347
-14.250 -0.9306 0.04727 0.04088 -0.0713 1.0000 0.0351
-14.000 -0.9266 0.04534 0.03886 -0.0712 1.0000 0.0357
-13.750 -0.9219 0.04346 0.03687 -0.0710 1.0000 0.0362
-13.500 -0.9163 0.04167 0.03494 -0.0707 1.0000 0.0368
-13.250 -0.9099 0.03996 0.03310 -0.0702 1.0000 0.0374
-13.000 -0.9024 0.03839 0.03137 -0.0696 1.0000 0.0380
-12.750 -0.8948 0.03691 0.02972 -0.0689 1.0000 0.0387
-12.500 -0.8853 0.03561 0.02834 -0.0680 1.0000 0.0394
-12.250 -0.8753 0.03454 0.02728 -0.0670 1.0000 0.0401
-12.000 -0.8672 0.03355 0.02627 -0.0656 1.0000 0.0407
-11.750 -0.8627 0.03268 0.02537 -0.0635 1.0000 0.0413
-11.250 -0.8258 0.03053 0.02307 -0.0640 0.9873 0.0432
-11.000 -0.8009 0.02945 0.02187 -0.0651 0.9824 0.0443
-10.750 -0.7764 0.02847 0.02076 -0.0662 0.9775 0.0455
-10.500 -0.7518 0.02737 0.01966 -0.0673 0.9731 0.0468
-10.250 -0.7258 0.02638 0.01865 -0.0687 0.9692 0.0481
-10.000 -0.7026 0.02550 0.01773 -0.0694 0.9640 0.0496
-9.750 -0.6783 0.02464 0.01680 -0.0701 0.9589 0.0511
-9.500 -0.6525 0.02381 0.01588 -0.0711 0.9545 0.0527
-9.250 -0.6351 0.02302 0.01505 -0.0705 0.9481 0.0541
-9.000 -0.6174 0.02218 0.01421 -0.0701 0.9420 0.0560
-8.750 -0.6033 0.02153 0.01353 -0.0688 0.9349 0.0578
-8.500 -0.5892 0.02095 0.01289 -0.0672 0.9278 0.0597
-8.250 -0.5773 0.02049 0.01236 -0.0650 0.9210 0.0615
-8.000 -0.5660 0.01999 0.01182 -0.0626 0.9145 0.0633
-7.750 -0.5534 0.01943 0.01126 -0.0606 0.9085 0.0657
-7.500 -0.5390 0.01897 0.01078 -0.0586 0.9014 0.0687
-7.250 -0.5223 0.01854 0.01027 -0.0569 0.8957 0.0720
-7.000 -0.5073 0.01804 0.00980 -0.0551 0.8880 0.0759
-6.750 -0.4901 0.01757 0.00932 -0.0535 0.8815 0.0810
-6.500 -0.4725 0.01711 0.00888 -0.0520 0.8741 0.0877
-6.250 -0.4543 0.01663 0.00844 -0.0505 0.8665 0.0983
-6.000 -0.4359 0.01614 0.00803 -0.0491 0.8583 0.1145
-5.750 -0.4165 0.01566 0.00761 -0.0478 0.8493 0.1356
-5.500 -0.3970 0.01517 0.00720 -0.0466 0.8379 0.1577
-5.250 -0.3773 0.01466 0.00677 -0.0454 0.8253 0.1822
-5.000 -0.3587 0.01403 0.00629 -0.0441 0.8095 0.2160
-4.750 -0.3439 0.01308 0.00572 -0.0423 0.7901 0.3016
-4.500 -0.3269 0.01226 0.00522 -0.0405 0.7683 0.3827
-4.250 -0.3074 0.01180 0.00506 -0.0388 0.7440 0.4663
-4.000 -0.2830 0.01175 0.00498 -0.0377 0.7213 0.5124
-3.500 -0.2314 0.01196 0.00493 -0.0364 0.6863 0.5586
-3.250 -0.2049 0.01212 0.00496 -0.0360 0.6734 0.5737
-3.000 -0.1782 0.01227 0.00500 -0.0356 0.6626 0.5864
-2.750 -0.1514 0.01242 0.00500 -0.0353 0.6530 0.5976
-2.500 -0.1241 0.01253 0.00505 -0.0350 0.6449 0.6042
-2.250 -0.0966 0.01260 0.00502 -0.0349 0.6374 0.6101
-2.000 -0.0692 0.01267 0.00493 -0.0348 0.6313 0.6162
-1.750 -0.0414 0.01273 0.00499 -0.0347 0.6256 0.6210
-1.500 -0.0138 0.01283 0.00503 -0.0346 0.6203 0.6281
-1.250 0.0136 0.01293 0.00504 -0.0345 0.6159 0.6354
-1.000 0.0414 0.01300 0.00512 -0.0344 0.6117 0.6406
-0.750 0.0694 0.01303 0.00511 -0.0344 0.6074 0.6450
-0.500 0.0974 0.01305 0.00506 -0.0346 0.6035 0.6483
-0.250 0.1256 0.01308 0.00499 -0.0347 0.5999 0.6510
0.000 0.1538 0.01311 0.00499 -0.0348 0.5967 0.6531
0.250 0.1819 0.01311 0.00501 -0.0350 0.5930 0.6554
0.500 0.2101 0.01313 0.00503 -0.0351 0.5894 0.6575
0.750 0.2383 0.01316 0.00505 -0.0352 0.5864 0.6601
1.000 0.2666 0.01321 0.00507 -0.0354 0.5836 0.6629
1.250 0.2950 0.01328 0.00508 -0.0356 0.5804 0.6656
1.750 0.3508 0.01335 0.00518 -0.0358 0.5725 0.6699
2.000 0.3786 0.01338 0.00525 -0.0359 0.5685 0.6721
2.250 0.4064 0.01345 0.00530 -0.0359 0.5643 0.6746
2.500 0.4340 0.01351 0.00537 -0.0359 0.5595 0.6774
2.750 0.4611 0.01354 0.00545 -0.0359 0.5536 0.6801
3.000 0.4887 0.01359 0.00550 -0.0359 0.5487 0.6827
3.250 0.5167 0.01369 0.00557 -0.0360 0.5450 0.6853
3.500 0.5436 0.01372 0.00570 -0.0359 0.5402 0.6874
3.750 0.5706 0.01376 0.00582 -0.0358 0.5351 0.6900
4.000 0.5977 0.01382 0.00593 -0.0357 0.5304 0.6931
4.250 0.6244 0.01389 0.00602 -0.0355 0.5246 0.6964
4.500 0.6505 0.01393 0.00614 -0.0352 0.5171 0.6997
4.750 0.6771 0.01399 0.00622 -0.0351 0.5109 0.7027
5.000 0.7030 0.01404 0.00640 -0.0348 0.5047 0.7054
5.250 0.7287 0.01408 0.00654 -0.0344 0.4973 0.7086
5.500 0.7541 0.01414 0.00667 -0.0340 0.4892 0.7121
5.750 0.7784 0.01419 0.00677 -0.0334 0.4775 0.7162
6.000 0.8012 0.01423 0.00687 -0.0325 0.4606 0.7204
6.250 0.8221 0.01428 0.00699 -0.0312 0.4331 0.7246
6.500 0.8366 0.01452 0.00704 -0.0290 0.3702 0.7294
6.750 0.8373 0.01546 0.00748 -0.0247 0.2917 0.7347
7.000 0.8456 0.01621 0.00808 -0.0218 0.2591 0.7398
7.250 0.8558 0.01683 0.00865 -0.0192 0.2355 0.7460
7.500 0.8662 0.01735 0.00914 -0.0165 0.2124 0.7533
7.750 0.8748 0.01793 0.00970 -0.0136 0.1910 0.7617
8.250 0.8936 0.01921 0.01098 -0.0085 0.1621 0.7869
8.500 0.9043 0.01985 0.01169 -0.0063 0.1521 0.8060
8.750 0.9147 0.02052 0.01243 -0.0041 0.1434 0.8336
9.000 0.9280 0.02111 0.01314 -0.0023 0.1349 0.8698
9.250 0.9471 0.02189 0.01401 -0.0021 0.1254 0.9208
9.500 0.9679 0.02263 0.01481 -0.0024 0.1147 1.0000
9.750 0.9805 0.02346 0.01563 -0.0011 0.1053 1.0000
10.000 0.9914 0.02441 0.01654 0.0003 0.0956 1.0000
10.250 1.0014 0.02545 0.01754 0.0018 0.0871 1.0000
10.500 1.0111 0.02656 0.01862 0.0031 0.0794 1.0000
10.750 1.0199 0.02776 0.01982 0.0044 0.0738 1.0000
11.000 1.0282 0.02905 0.02110 0.0057 0.0688 1.0000
11.250 1.0359 0.03043 0.02249 0.0068 0.0647 1.0000
11.500 1.0447 0.03179 0.02389 0.0078 0.0615 1.0000
11.750 1.0515 0.03336 0.02546 0.0088 0.0587 1.0000
12.000 1.0583 0.03498 0.02711 0.0096 0.0565 1.0000
12.250 1.0669 0.03651 0.02871 0.0103 0.0544 1.0000
12.500 1.0747 0.03814 0.03040 0.0109 0.0525 1.0000
12.750 1.0812 0.03992 0.03221 0.0115 0.0509 1.0000
13.000 1.0857 0.04192 0.03422 0.0120 0.0494 1.0000
13.250 1.0942 0.04362 0.03600 0.0123 0.0480 1.0000
13.500 1.1021 0.04540 0.03787 0.0127 0.0466 1.0000
13.750 1.1094 0.04726 0.03979 0.0129 0.0452 1.0000
14.000 1.1162 0.04921 0.04180 0.0131 0.0442 1.0000
14.250 1.1217 0.05131 0.04393 0.0132 0.0432 1.0000
14.500 1.1259 0.05355 0.04618 0.0133 0.0422 1.0000
14.750 1.1335 0.05552 0.04825 0.0134 0.0414 1.0000
15.000 1.1405 0.05759 0.05043 0.0134 0.0404 1.0000
15.250 1.1467 0.05976 0.05270 0.0133 0.0395 1.0000
15.500 1.1521 0.06205 0.05506 0.0131 0.0385 1.0000
15.750 1.1570 0.06444 0.05752 0.0128 0.0377 1.0000
16.000 1.1614 0.06691 0.06005 0.0124 0.0371 1.0000
16.250 1.1653 0.06946 0.06262 0.0120 0.0364 1.0000
16.500 1.1694 0.07205 0.06530 0.0116 0.0357 1.0000
16.750 1.1725 0.07486 0.06826 0.0110 0.0351 1.0000
17.000 1.1747 0.07784 0.07138 0.0102 0.0344 1.0000
17.250 1.1758 0.08102 0.07468 0.0093 0.0336 1.0000
17.500 1.1768 0.08426 0.07802 0.0083 0.0330 1.0000
17.750 1.1773 0.08761 0.08147 0.0071 0.0324 1.0000
18.000 1.1773 0.09107 0.08501 0.0058 0.0319 1.0000
18.250 1.1776 0.09452 0.08853 0.0045 0.0314 1.0000
18.500 1.1785 0.09787 0.09192 0.0032 0.0309 1.0000
18.750 1.1739 0.10233 0.09654 0.0012 0.0304 1.0000
19.000 1.1667 0.10733 0.10174 -0.0012 0.0300 1.0000
19.250 1.1584 0.11267 0.10727 -0.0039 0.0295 1.0000
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