P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Reynolds number: 100,000 Max Cl/Cd: 43.38 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51droot-il-100000-n5.txt Download as CSV file: xf-p51droot-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6512 0.09419 0.08835 -0.0541 1.0000 0.0502
-14.250 -0.7370 0.07694 0.07073 -0.0651 1.0000 0.0490
-14.000 -0.7719 0.06980 0.06334 -0.0685 1.0000 0.0491
-13.750 -0.7953 0.06465 0.05797 -0.0703 1.0000 0.0493
-13.500 -0.8131 0.06045 0.05356 -0.0713 1.0000 0.0496
-13.250 -0.8276 0.05682 0.04971 -0.0716 1.0000 0.0501
-13.000 -0.8389 0.05364 0.04631 -0.0714 1.0000 0.0505
-12.750 -0.8480 0.05080 0.04324 -0.0707 1.0000 0.0511
-12.500 -0.8543 0.04831 0.04052 -0.0696 1.0000 0.0516
-12.250 -0.8592 0.04610 0.03807 -0.0680 1.0000 0.0522
-12.000 -0.8639 0.04423 0.03596 -0.0659 1.0000 0.0528
-11.750 -0.8712 0.04278 0.03428 -0.0627 1.0000 0.0534
-11.500 -0.8644 0.04144 0.03296 -0.0607 1.0000 0.0544
-11.250 -0.8640 0.04050 0.03201 -0.0576 1.0000 0.0552
-11.000 -0.8669 0.03964 0.03110 -0.0539 1.0000 0.0560
-10.750 -0.8709 0.03884 0.03024 -0.0498 1.0000 0.0569
-10.500 -0.8714 0.03793 0.02924 -0.0462 1.0000 0.0578
-10.250 -0.8674 0.03692 0.02811 -0.0432 1.0000 0.0588
-10.000 -0.8613 0.03589 0.02694 -0.0404 1.0000 0.0600
-9.750 -0.8371 0.03456 0.02541 -0.0408 0.9966 0.0616
-9.500 -0.8049 0.03318 0.02398 -0.0426 0.9919 0.0638
-9.250 -0.7759 0.03205 0.02288 -0.0440 0.9869 0.0661
-9.000 -0.7448 0.03097 0.02173 -0.0456 0.9827 0.0689
-8.750 -0.7152 0.02995 0.02061 -0.0467 0.9781 0.0715
-8.500 -0.6859 0.02892 0.01956 -0.0479 0.9732 0.0743
-8.250 -0.6537 0.02794 0.01861 -0.0499 0.9690 0.0782
-8.000 -0.6270 0.02712 0.01774 -0.0505 0.9631 0.0823
-7.750 -0.5968 0.02617 0.01681 -0.0520 0.9580 0.0865
-7.500 -0.5672 0.02535 0.01599 -0.0534 0.9527 0.0925
-7.250 -0.5436 0.02460 0.01526 -0.0535 0.9452 0.0989
-7.000 -0.5140 0.02385 0.01450 -0.0547 0.9396 0.1084
-6.750 -0.4955 0.02317 0.01391 -0.0537 0.9305 0.1190
-6.500 -0.4719 0.02247 0.01325 -0.0537 0.9232 0.1355
-6.250 -0.4531 0.02178 0.01264 -0.0527 0.9141 0.1561
-6.000 -0.4370 0.02106 0.01204 -0.0512 0.9041 0.1822
-5.500 -0.4121 0.01909 0.01072 -0.0473 0.8829 0.2917
-5.250 -0.4025 0.01824 0.01037 -0.0444 0.8706 0.3822
-5.000 -0.3828 0.01814 0.01076 -0.0422 0.8606 0.4706
-4.750 -0.3605 0.01816 0.01076 -0.0407 0.8489 0.5152
-4.500 -0.3395 0.01823 0.01078 -0.0390 0.8351 0.5422
-4.250 -0.3181 0.01836 0.01084 -0.0374 0.8206 0.5680
-4.000 -0.2952 0.01866 0.01109 -0.0357 0.8057 0.5905
-3.750 -0.2706 0.01887 0.01123 -0.0344 0.7911 0.6073
-3.500 -0.2448 0.01886 0.01110 -0.0335 0.7774 0.6195
-3.250 -0.2171 0.01881 0.01093 -0.0330 0.7651 0.6286
-3.000 -0.1895 0.01869 0.01067 -0.0325 0.7530 0.6369
-2.750 -0.1620 0.01867 0.01054 -0.0320 0.7411 0.6450
-2.500 -0.1347 0.01859 0.01032 -0.0315 0.7309 0.6538
-2.250 -0.1068 0.01860 0.01023 -0.0310 0.7213 0.6618
-2.000 -0.0805 0.01848 0.00997 -0.0308 0.7119 0.6695
-1.750 -0.0521 0.01844 0.00983 -0.0305 0.7038 0.6741
-1.500 -0.0254 0.01838 0.00966 -0.0303 0.6955 0.6799
-1.250 0.0013 0.01825 0.00938 -0.0303 0.6882 0.6857
-1.000 0.0293 0.01821 0.00927 -0.0302 0.6817 0.6889
-0.750 0.0564 0.01817 0.00919 -0.0301 0.6751 0.6925
-0.500 0.0843 0.01811 0.00902 -0.0303 0.6699 0.6964
-0.250 0.1120 0.01804 0.00885 -0.0306 0.6650 0.7004
0.000 0.1389 0.01802 0.00880 -0.0306 0.6598 0.7037
0.250 0.1667 0.01802 0.00879 -0.0307 0.6552 0.7065
0.500 0.1951 0.01802 0.00873 -0.0309 0.6513 0.7094
0.750 0.2224 0.01805 0.00873 -0.0310 0.6470 0.7128
1.000 0.2492 0.01808 0.00875 -0.0312 0.6424 0.7167
1.250 0.2767 0.01812 0.00877 -0.0314 0.6384 0.7200
1.500 0.3049 0.01817 0.00882 -0.0315 0.6351 0.7225
1.750 0.3336 0.01825 0.00889 -0.0318 0.6324 0.7254
2.000 0.3596 0.01837 0.00908 -0.0318 0.6289 0.7290
2.250 0.3859 0.01849 0.00924 -0.0318 0.6253 0.7329
2.750 0.4410 0.01868 0.00946 -0.0320 0.6169 0.7394
3.000 0.4678 0.01881 0.00964 -0.0320 0.6126 0.7425
3.250 0.4924 0.01896 0.00989 -0.0316 0.6071 0.7463
3.500 0.5194 0.01904 0.00999 -0.0316 0.6011 0.7507
3.750 0.5469 0.01912 0.01008 -0.0316 0.5950 0.7549
4.000 0.5704 0.01925 0.01034 -0.0309 0.5875 0.7586
4.250 0.5983 0.01928 0.01039 -0.0308 0.5810 0.7626
4.500 0.6215 0.01941 0.01062 -0.0302 0.5731 0.7672
4.750 0.6477 0.01946 0.01072 -0.0299 0.5653 0.7722
5.000 0.6718 0.01954 0.01091 -0.0292 0.5574 0.7768
5.250 0.6959 0.01961 0.01108 -0.0285 0.5489 0.7826
5.500 0.7209 0.01968 0.01123 -0.0280 0.5408 0.7891
5.750 0.7434 0.01973 0.01143 -0.0270 0.5313 0.7947
6.000 0.7663 0.01981 0.01163 -0.0261 0.5222 0.8017
6.250 0.7893 0.01984 0.01179 -0.0252 0.5123 0.8091
6.500 0.8088 0.01993 0.01207 -0.0238 0.5008 0.8180
6.750 0.8285 0.01995 0.01223 -0.0223 0.4871 0.8285
7.000 0.8449 0.01996 0.01239 -0.0203 0.4676 0.8416
7.250 0.8587 0.01997 0.01251 -0.0178 0.4411 0.8574
7.500 0.8697 0.02005 0.01265 -0.0149 0.3950 0.8772
7.750 0.8744 0.02044 0.01258 -0.0112 0.3201 0.9055
8.000 0.8833 0.02165 0.01344 -0.0097 0.2745 0.9556
8.250 0.8868 0.02276 0.01436 -0.0072 0.2511 1.0000
8.500 0.8923 0.02380 0.01532 -0.0049 0.2302 1.0000
8.750 0.8988 0.02486 0.01630 -0.0028 0.2112 1.0000
9.000 0.9053 0.02597 0.01734 -0.0008 0.1943 1.0000
9.250 0.9119 0.02714 0.01842 0.0010 0.1801 1.0000
9.500 0.9183 0.02837 0.01958 0.0027 0.1676 1.0000
9.750 0.9241 0.02970 0.02080 0.0043 0.1570 1.0000
10.000 0.9331 0.03091 0.02203 0.0057 0.1460 1.0000
10.250 0.9415 0.03221 0.02331 0.0069 0.1363 1.0000
10.500 0.9487 0.03363 0.02469 0.0081 0.1272 1.0000
10.750 0.9592 0.03489 0.02600 0.0090 0.1175 1.0000
11.000 0.9677 0.03634 0.02743 0.0100 0.1096 1.0000
11.250 0.9763 0.03782 0.02893 0.0108 0.1017 1.0000
11.500 0.9856 0.03929 0.03043 0.0116 0.0952 1.0000
11.750 0.9933 0.04093 0.03205 0.0122 0.0895 1.0000
12.000 1.0021 0.04252 0.03366 0.0129 0.0845 1.0000
12.250 1.0105 0.04419 0.03535 0.0134 0.0800 1.0000
12.500 1.0170 0.04603 0.03716 0.0140 0.0770 1.0000
12.750 1.0278 0.04759 0.03882 0.0145 0.0736 1.0000
13.000 1.0368 0.04931 0.04060 0.0149 0.0707 1.0000
13.250 1.0438 0.05122 0.04251 0.0152 0.0681 1.0000
13.500 1.0522 0.05306 0.04436 0.0156 0.0659 1.0000
13.750 1.0618 0.05489 0.04633 0.0159 0.0635 1.0000
14.000 1.0707 0.05678 0.04832 0.0162 0.0616 1.0000
14.250 1.0789 0.05876 0.05035 0.0163 0.0599 1.0000
14.500 1.0869 0.06075 0.05235 0.0164 0.0584 1.0000
14.750 1.0958 0.06277 0.05441 0.0166 0.0570 1.0000
15.000 1.1006 0.06531 0.05717 0.0165 0.0554 1.0000
15.250 1.1047 0.06794 0.05997 0.0163 0.0540 1.0000
15.500 1.1083 0.07063 0.06281 0.0160 0.0527 1.0000
15.750 1.1120 0.07336 0.06564 0.0156 0.0516 1.0000
16.000 1.1160 0.07605 0.06840 0.0151 0.0506 1.0000
16.250 1.1228 0.07843 0.07078 0.0148 0.0496 1.0000
16.500 1.1208 0.08207 0.07459 0.0140 0.0488 1.0000
16.750 1.1105 0.08687 0.07968 0.0123 0.0480 1.0000
17.000 1.0988 0.09207 0.08513 0.0103 0.0473 1.0000
17.250 1.0848 0.09782 0.09113 0.0078 0.0467 1.0000
17.500 1.0679 0.10428 0.09783 0.0046 0.0462 1.0000
17.750 1.0457 0.11202 0.10582 0.0005 0.0458 1.0000
18.000 1.0118 0.12267 0.11675 -0.0058 0.0457 1.0000
|
Polar data table (+)
Polar graphs
<< Back to P-51D ROOT (BL17.5) AIRFOIL (p51droot-il)