P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Reynolds number: 200,000 Max Cl/Cd: 62.43 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-p51droot-il-200000.txt Download as CSV file: xf-p51droot-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6451 0.09650 0.09246 -0.0553 1.0000 0.0584
-14.250 -0.6650 0.08862 0.08453 -0.0591 1.0000 0.0575
-14.000 -0.7125 0.07795 0.07372 -0.0653 1.0000 0.0563
-13.750 -0.7587 0.06937 0.06492 -0.0696 1.0000 0.0555
-13.500 -0.7989 0.06257 0.05788 -0.0719 1.0000 0.0547
-13.250 -0.8318 0.05724 0.05229 -0.0727 1.0000 0.0543
-13.000 -0.8584 0.05298 0.04778 -0.0724 1.0000 0.0541
-12.750 -0.8760 0.04985 0.04444 -0.0712 1.0000 0.0542
-12.500 -0.8917 0.04725 0.04163 -0.0690 1.0000 0.0543
-12.250 -0.9080 0.04546 0.03969 -0.0653 1.0000 0.0545
-12.000 -0.9301 0.04450 0.03861 -0.0594 1.0000 0.0547
-11.750 -0.9524 0.04362 0.03761 -0.0529 1.0000 0.0549
-11.500 -0.9652 0.04234 0.03619 -0.0479 1.0000 0.0554
-11.250 -0.9738 0.04096 0.03462 -0.0435 1.0000 0.0561
-11.000 -0.9786 0.03949 0.03294 -0.0395 1.0000 0.0567
-10.750 -0.9802 0.03804 0.03127 -0.0358 1.0000 0.0573
-10.500 -0.9789 0.03665 0.02963 -0.0324 1.0000 0.0580
-10.250 -0.9750 0.03544 0.02818 -0.0293 1.0000 0.0585
-10.000 -0.9632 0.03331 0.02591 -0.0275 1.0000 0.0596
-9.750 -0.9475 0.03195 0.02457 -0.0262 1.0000 0.0609
-9.500 -0.9151 0.03075 0.02332 -0.0281 0.9969 0.0628
-9.250 -0.8798 0.02949 0.02193 -0.0303 0.9936 0.0648
-9.000 -0.8471 0.02832 0.02059 -0.0319 0.9896 0.0666
-8.750 -0.8109 0.02698 0.01911 -0.0341 0.9857 0.0688
-8.500 -0.7710 0.02572 0.01795 -0.0370 0.9827 0.0717
-8.250 -0.7364 0.02484 0.01705 -0.0389 0.9782 0.0746
-8.000 -0.7003 0.02401 0.01612 -0.0409 0.9734 0.0775
-7.750 -0.6616 0.02278 0.01498 -0.0437 0.9701 0.0816
-7.500 -0.6287 0.02203 0.01425 -0.0453 0.9648 0.0859
-7.250 -0.5931 0.02120 0.01338 -0.0474 0.9595 0.0906
-7.000 -0.5516 0.02021 0.01249 -0.0509 0.9559 0.0978
-6.750 -0.5215 0.01941 0.01173 -0.0520 0.9491 0.1057
-6.500 -0.4852 0.01858 0.01095 -0.0543 0.9435 0.1178
-6.250 -0.4582 0.01773 0.01025 -0.0549 0.9362 0.1365
-6.000 -0.4355 0.01673 0.00947 -0.0546 0.9279 0.1741
-5.750 -0.4239 0.01564 0.00872 -0.0524 0.9166 0.2304
-5.500 -0.4170 0.01422 0.00804 -0.0493 0.9056 0.3670
-5.250 -0.4006 0.01370 0.00814 -0.0468 0.8960 0.4932
-5.000 -0.3787 0.01380 0.00828 -0.0449 0.8839 0.5368
-4.750 -0.3538 0.01390 0.00830 -0.0436 0.8732 0.5621
-4.500 -0.3273 0.01398 0.00830 -0.0425 0.8634 0.5797
-4.250 -0.3038 0.01402 0.00825 -0.0410 0.8491 0.5943
-4.000 -0.2783 0.01412 0.00834 -0.0396 0.8345 0.6059
-3.750 -0.2525 0.01419 0.00838 -0.0385 0.8191 0.6173
-3.500 -0.2269 0.01426 0.00836 -0.0373 0.8029 0.6302
-3.250 -0.1995 0.01442 0.00850 -0.0363 0.7870 0.6413
-3.000 -0.1725 0.01451 0.00852 -0.0353 0.7718 0.6513
-2.750 -0.1457 0.01455 0.00842 -0.0347 0.7574 0.6609
-2.500 -0.1183 0.01449 0.00824 -0.0342 0.7446 0.6668
-2.250 -0.0908 0.01453 0.00816 -0.0338 0.7328 0.6726
-2.000 -0.0644 0.01452 0.00800 -0.0336 0.7215 0.6800
-1.750 -0.0368 0.01455 0.00795 -0.0332 0.7129 0.6851
-1.500 -0.0098 0.01466 0.00802 -0.0328 0.7042 0.6919
-1.250 0.0174 0.01468 0.00787 -0.0328 0.6978 0.6990
-1.000 0.0446 0.01469 0.00789 -0.0326 0.6908 0.7030
-0.750 0.0722 0.01472 0.00787 -0.0325 0.6849 0.7077
-0.500 0.1002 0.01477 0.00779 -0.0327 0.6802 0.7135
-0.250 0.1272 0.01471 0.00773 -0.0328 0.6748 0.7174
0.000 0.1548 0.01470 0.00771 -0.0328 0.6698 0.7204
0.250 0.1830 0.01471 0.00768 -0.0330 0.6654 0.7235
0.500 0.2114 0.01475 0.00766 -0.0333 0.6616 0.7268
0.750 0.2390 0.01475 0.00767 -0.0337 0.6576 0.7304
1.000 0.2670 0.01476 0.00764 -0.0341 0.6537 0.7335
1.250 0.2950 0.01476 0.00765 -0.0342 0.6498 0.7358
1.500 0.3236 0.01484 0.00769 -0.0344 0.6462 0.7386
1.750 0.3508 0.01491 0.00781 -0.0346 0.6422 0.7419
2.000 0.3780 0.01494 0.00788 -0.0347 0.6372 0.7450
2.250 0.4062 0.01497 0.00786 -0.0349 0.6317 0.7482
2.500 0.4350 0.01507 0.00789 -0.0353 0.6269 0.7512
2.750 0.4609 0.01509 0.00803 -0.0351 0.6219 0.7541
3.000 0.4879 0.01514 0.00814 -0.0350 0.6169 0.7574
3.250 0.5164 0.01521 0.00818 -0.0352 0.6121 0.7607
3.500 0.5439 0.01532 0.00832 -0.0353 0.6073 0.7643
3.750 0.5703 0.01538 0.00844 -0.0353 0.6016 0.7680
4.000 0.5979 0.01538 0.00847 -0.0353 0.5956 0.7711
4.250 0.6256 0.01548 0.00860 -0.0352 0.5905 0.7748
4.500 0.6506 0.01553 0.00877 -0.0348 0.5841 0.7792
4.750 0.6783 0.01557 0.00883 -0.0349 0.5782 0.7838
5.000 0.7057 0.01562 0.00891 -0.0348 0.5720 0.7879
5.250 0.7301 0.01561 0.00903 -0.0342 0.5641 0.7920
5.500 0.7585 0.01561 0.00904 -0.0342 0.5578 0.7969
5.750 0.7823 0.01562 0.00919 -0.0335 0.5493 0.8027
6.000 0.8090 0.01547 0.00902 -0.0330 0.5387 0.8080
6.250 0.8303 0.01528 0.00895 -0.0316 0.5249 0.8146
6.500 0.8523 0.01512 0.00888 -0.0305 0.5104 0.8222
6.750 0.8729 0.01496 0.00884 -0.0289 0.4950 0.8292
7.000 0.8927 0.01483 0.00878 -0.0274 0.4755 0.8388
7.250 0.9090 0.01471 0.00876 -0.0251 0.4485 0.8486
7.500 0.9202 0.01474 0.00873 -0.0220 0.3932 0.8618
7.750 0.9125 0.01547 0.00898 -0.0161 0.3113 0.8819
8.000 0.9085 0.01633 0.00964 -0.0111 0.2728 0.9128
8.250 0.9317 0.01748 0.01070 -0.0120 0.2375 0.9673
8.500 0.9444 0.01836 0.01142 -0.0110 0.2153 1.0000
8.750 0.9538 0.01922 0.01215 -0.0090 0.1974 1.0000
9.000 0.9628 0.02012 0.01295 -0.0070 0.1822 1.0000
9.250 0.9712 0.02108 0.01383 -0.0050 0.1684 1.0000
9.500 0.9790 0.02212 0.01481 -0.0030 0.1554 1.0000
9.750 0.9857 0.02326 0.01590 -0.0009 0.1427 1.0000
10.000 0.9913 0.02453 0.01710 0.0011 0.1307 1.0000
10.250 0.9961 0.02590 0.01838 0.0031 0.1195 1.0000
10.500 1.0045 0.02710 0.01957 0.0046 0.1090 1.0000
10.750 1.0130 0.02836 0.02084 0.0060 0.1003 1.0000
11.000 1.0185 0.02988 0.02225 0.0075 0.0937 1.0000
11.250 1.0291 0.03110 0.02353 0.0086 0.0878 1.0000
11.500 1.0356 0.03268 0.02501 0.0098 0.0833 1.0000
11.750 1.0468 0.03397 0.02638 0.0108 0.0793 1.0000
12.000 1.0570 0.03534 0.02776 0.0117 0.0758 1.0000
12.250 1.0679 0.03682 0.02911 0.0127 0.0724 1.0000
12.500 1.0801 0.03812 0.03054 0.0134 0.0700 1.0000
12.750 1.0927 0.03944 0.03192 0.0141 0.0675 1.0000
13.000 1.1053 0.04078 0.03325 0.0148 0.0652 1.0000
13.250 1.1251 0.04196 0.03432 0.0155 0.0627 1.0000
13.500 1.1364 0.04344 0.03595 0.0161 0.0611 1.0000
13.750 1.1480 0.04496 0.03758 0.0167 0.0593 1.0000
14.000 1.1613 0.04641 0.03909 0.0172 0.0577 1.0000
14.250 1.1761 0.04779 0.04046 0.0176 0.0560 1.0000
14.500 1.1983 0.04928 0.04193 0.0180 0.0541 1.0000
14.750 1.2031 0.05134 0.04420 0.0186 0.0532 1.0000
15.000 1.2076 0.05352 0.04656 0.0190 0.0520 1.0000
15.250 1.2136 0.05569 0.04888 0.0193 0.0509 1.0000
15.500 1.2185 0.05793 0.05123 0.0195 0.0498 1.0000
15.750 1.2265 0.05996 0.05332 0.0196 0.0487 1.0000
16.000 1.2496 0.06168 0.05496 0.0198 0.0471 1.0000
16.250 1.2420 0.06509 0.05862 0.0198 0.0466 1.0000
16.500 1.2305 0.06888 0.06267 0.0194 0.0462 1.0000
16.750 1.2190 0.07299 0.06703 0.0187 0.0457 1.0000
17.000 1.2049 0.07763 0.07192 0.0175 0.0452 1.0000
17.250 1.1901 0.08260 0.07713 0.0160 0.0448 1.0000
17.500 1.1716 0.08830 0.08306 0.0139 0.0445 1.0000
17.750 1.1499 0.09476 0.08977 0.0112 0.0443 1.0000
18.000 1.1232 0.10231 0.09757 0.0075 0.0442 1.0000
18.250 1.0852 0.11242 0.10797 0.0019 0.0444 1.0000
18.500 1.0280 0.12746 0.12334 -0.0072 0.0453 1.0000
18.750 0.9290 0.15556 0.15174 -0.0248 0.0471 1.0000
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Polar data table (+)
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