P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Reynolds number: 50,000 Max Cl/Cd: 23.88 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51droot-il-50000-n5.txt Download as CSV file: xf-p51droot-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5359 0.10731 0.09928 -0.0482 1.0000 0.0815
-13.000 -0.5721 0.09549 0.08745 -0.0551 1.0000 0.0811
-12.750 -0.6201 0.08426 0.07613 -0.0618 1.0000 0.0803
-12.500 -0.6624 0.07602 0.06773 -0.0659 1.0000 0.0796
-12.250 -0.6961 0.07004 0.06157 -0.0678 1.0000 0.0795
-12.000 -0.7225 0.06548 0.05683 -0.0683 1.0000 0.0797
-11.750 -0.7441 0.06188 0.05304 -0.0677 1.0000 0.0802
-11.500 -0.7631 0.05893 0.04990 -0.0660 1.0000 0.0808
-11.250 -0.7815 0.05654 0.04732 -0.0631 1.0000 0.0815
-11.000 -0.8001 0.05463 0.04522 -0.0590 1.0000 0.0822
-10.750 -0.8147 0.05276 0.04311 -0.0549 1.0000 0.0830
-10.500 -0.8260 0.05088 0.04095 -0.0509 1.0000 0.0840
-10.250 -0.8203 0.04918 0.03921 -0.0486 1.0000 0.0853
-10.000 -0.8133 0.04764 0.03761 -0.0464 1.0000 0.0868
-9.750 -0.8067 0.04618 0.03605 -0.0440 1.0000 0.0884
-9.500 -0.8002 0.04477 0.03451 -0.0415 1.0000 0.0906
-9.250 -0.7934 0.04338 0.03292 -0.0390 1.0000 0.0933
-9.000 -0.7847 0.04197 0.03119 -0.0366 1.0000 0.0961
-8.750 -0.7666 0.04081 0.03015 -0.0353 1.0000 0.0989
-8.500 -0.7506 0.03977 0.02908 -0.0337 1.0000 0.1019
-8.250 -0.7359 0.03880 0.02798 -0.0319 1.0000 0.1062
-8.000 -0.7191 0.03789 0.02700 -0.0302 1.0000 0.1105
-7.750 -0.7042 0.03711 0.02628 -0.0283 1.0000 0.1150
-7.500 -0.6896 0.03638 0.02546 -0.0263 1.0000 0.1204
-7.250 -0.6788 0.03563 0.02475 -0.0239 1.0000 0.1259
-7.000 -0.6602 0.03481 0.02393 -0.0232 0.9971 0.1341
-6.750 -0.6267 0.03375 0.02292 -0.0252 0.9882 0.1463
-6.500 -0.5960 0.03259 0.02182 -0.0272 0.9789 0.1635
-6.250 -0.5678 0.03125 0.02062 -0.0290 0.9690 0.1877
-6.000 -0.5473 0.02963 0.01934 -0.0300 0.9572 0.2219
-5.750 -0.5307 0.02794 0.01831 -0.0303 0.9448 0.2902
-5.500 -0.5062 0.02778 0.01922 -0.0289 0.9341 0.4192
-5.250 -0.4655 0.02885 0.02037 -0.0296 0.9259 0.5098
-5.000 -0.4396 0.02944 0.02077 -0.0289 0.9129 0.5571
-4.750 -0.4120 0.03042 0.02161 -0.0276 0.9005 0.5917
-4.500 -0.3859 0.03099 0.02201 -0.0264 0.8884 0.6173
-4.000 -0.3259 0.03187 0.02259 -0.0250 0.8666 0.6520
-3.750 -0.3032 0.03210 0.02270 -0.0234 0.8536 0.6677
-3.500 -0.2668 0.03258 0.02306 -0.0231 0.8450 0.6811
-3.000 -0.2240 0.03250 0.02276 -0.0202 0.8207 0.7045
-2.750 -0.1952 0.03241 0.02255 -0.0200 0.8115 0.7121
-2.500 -0.1768 0.03190 0.02190 -0.0191 0.8015 0.7207
-2.250 -0.1522 0.03181 0.02172 -0.0184 0.7913 0.7264
-2.000 -0.1271 0.03134 0.02111 -0.0183 0.7846 0.7345
-1.750 -0.1078 0.03121 0.02089 -0.0171 0.7745 0.7406
-1.500 -0.0770 0.03093 0.02051 -0.0176 0.7691 0.7465
-1.250 -0.0660 0.03066 0.02015 -0.0158 0.7599 0.7544
-1.000 -0.0349 0.03050 0.01991 -0.0163 0.7546 0.7586
-0.750 -0.0110 0.03035 0.01969 -0.0160 0.7484 0.7639
-0.500 0.0055 0.03014 0.01940 -0.0149 0.7411 0.7705
-0.250 0.0361 0.02991 0.01910 -0.0155 0.7369 0.7746
0.000 0.0558 0.02999 0.01915 -0.0147 0.7301 0.7793
0.250 0.0767 0.02994 0.01905 -0.0142 0.7245 0.7846
0.500 0.1023 0.02975 0.01880 -0.0145 0.7207 0.7898
0.750 0.1258 0.02989 0.01893 -0.0142 0.7157 0.7938
1.000 0.1427 0.03011 0.01916 -0.0132 0.7095 0.7990
1.250 0.1668 0.03007 0.01908 -0.0132 0.7054 0.8042
1.500 0.1967 0.02997 0.01897 -0.0139 0.7024 0.8086
1.750 0.2058 0.03059 0.01964 -0.0120 0.6957 0.8139
2.000 0.2240 0.03090 0.01997 -0.0113 0.6911 0.8198
2.250 0.2495 0.03100 0.02008 -0.0115 0.6877 0.8250
2.500 0.2807 0.03105 0.02016 -0.0122 0.6851 0.8294
2.750 0.2814 0.03201 0.02118 -0.0096 0.6775 0.8368
3.000 0.2998 0.03248 0.02171 -0.0091 0.6733 0.8432
3.250 0.3266 0.03274 0.02204 -0.0094 0.6701 0.8491
3.500 0.3573 0.03284 0.02218 -0.0101 0.6676 0.8556
3.750 0.3508 0.03430 0.02376 -0.0070 0.6590 0.8645
4.000 0.3748 0.03465 0.02418 -0.0071 0.6545 0.8730
4.250 0.4151 0.03441 0.02404 -0.0086 0.6508 0.8795
4.500 0.4154 0.03555 0.02530 -0.0062 0.6405 0.8918
4.750 0.4604 0.03511 0.02497 -0.0082 0.6350 0.8989
5.000 0.4793 0.03565 0.02564 -0.0078 0.6247 0.9108
5.250 0.5251 0.03515 0.02528 -0.0099 0.6179 0.9202
5.500 0.5549 0.03549 0.02577 -0.0110 0.6071 0.9330
5.750 0.6205 0.03373 0.02413 -0.0143 0.5979 0.9395
6.000 0.6559 0.03358 0.02415 -0.0158 0.5828 0.9539
6.250 0.6940 0.03346 0.02420 -0.0178 0.5686 0.9717
6.500 0.7358 0.03317 0.02408 -0.0202 0.5565 0.9999
6.750 0.7572 0.03270 0.02366 -0.0188 0.5460 1.0000
7.000 0.7554 0.03335 0.02435 -0.0153 0.5322 1.0000
7.250 0.7671 0.03359 0.02466 -0.0133 0.5180 1.0000
7.500 0.7800 0.03370 0.02483 -0.0111 0.5026 1.0000
7.750 0.7872 0.03399 0.02519 -0.0084 0.4848 1.0000
8.000 0.7926 0.03442 0.02570 -0.0057 0.4647 1.0000
8.250 0.7990 0.03485 0.02622 -0.0032 0.4417 1.0000
8.500 0.7975 0.03596 0.02740 -0.0006 0.4122 1.0000
8.750 0.8057 0.03648 0.02793 0.0014 0.3763 1.0000
9.000 0.8355 0.03520 0.02627 0.0033 0.3318 1.0000
9.250 0.8497 0.03558 0.02615 0.0054 0.2956 1.0000
9.500 0.8557 0.03694 0.02713 0.0073 0.2703 1.0000
9.750 0.8610 0.03857 0.02856 0.0088 0.2498 1.0000
10.000 0.8666 0.04027 0.03018 0.0101 0.2313 1.0000
10.250 0.8729 0.04198 0.03183 0.0112 0.2149 1.0000
10.500 0.8793 0.04371 0.03352 0.0121 0.1999 1.0000
10.750 0.8863 0.04544 0.03517 0.0130 0.1865 1.0000
11.000 0.8938 0.04719 0.03689 0.0138 0.1739 1.0000
11.250 0.9024 0.04896 0.03865 0.0145 0.1617 1.0000
11.500 0.9124 0.05067 0.04034 0.0151 0.1510 1.0000
11.750 0.9250 0.05218 0.04169 0.0158 0.1416 1.0000
12.000 0.9356 0.05408 0.04378 0.0163 0.1320 1.0000
12.250 0.9492 0.05568 0.04534 0.0169 0.1242 1.0000
12.500 0.9608 0.05759 0.04742 0.0173 0.1171 1.0000
12.750 0.9759 0.05914 0.04892 0.0178 0.1113 1.0000
13.000 0.9851 0.06146 0.05150 0.0180 0.1060 1.0000
13.250 0.9978 0.06331 0.05341 0.0183 0.1016 1.0000
13.500 1.0082 0.06554 0.05574 0.0185 0.0979 1.0000
13.750 1.0086 0.06879 0.05928 0.0184 0.0944 1.0000
14.000 1.0114 0.07168 0.06232 0.0182 0.0914 1.0000
14.250 1.0209 0.07386 0.06452 0.0182 0.0888 1.0000
14.500 1.0211 0.07738 0.06820 0.0178 0.0869 1.0000
14.750 1.0053 0.08278 0.07395 0.0164 0.0857 1.0000
15.000 0.9837 0.08920 0.08066 0.0142 0.0847 1.0000
15.250 0.9539 0.09726 0.08900 0.0107 0.0842 1.0000
15.500 0.9059 0.10932 0.10134 0.0043 0.0843 1.0000
15.750 0.8270 0.13090 0.12310 -0.0083 0.0849 1.0000
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