P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il) Reynolds number: 1,000,000 Max Cl/Cd: 68.41 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51dtip-il-1000000-n5.txt Download as CSV file: xf-p51dtip-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: P-51D TIP (BL215) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5626 0.14396 0.14152 -0.0031 0.7670 0.0028
-12.750 -0.9697 0.04115 0.03825 -0.0504 0.7663 0.0023
-12.250 -1.0066 0.03415 0.03077 -0.0447 0.7606 0.0023
-12.000 -1.0123 0.03177 0.02818 -0.0417 0.7580 0.0023
-11.750 -1.0083 0.02961 0.02580 -0.0398 0.7557 0.0024
-11.500 -0.9980 0.02797 0.02399 -0.0384 0.7534 0.0025
-11.250 -0.9853 0.02646 0.02229 -0.0372 0.7513 0.0025
-10.750 -0.9543 0.02371 0.01920 -0.0353 0.7475 0.0027
-10.500 -0.9374 0.02229 0.01758 -0.0344 0.7455 0.0028
-10.250 -0.9181 0.02119 0.01632 -0.0337 0.7434 0.0029
-10.000 -0.8975 0.02023 0.01522 -0.0331 0.7413 0.0030
-9.750 -0.8773 0.01910 0.01391 -0.0325 0.7393 0.0031
-9.500 -0.8554 0.01826 0.01290 -0.0320 0.7374 0.0033
-9.250 -0.8328 0.01749 0.01201 -0.0316 0.7357 0.0034
-9.000 -0.8099 0.01673 0.01113 -0.0312 0.7342 0.0035
-8.750 -0.7863 0.01607 0.01036 -0.0309 0.7326 0.0036
-8.500 -0.7623 0.01546 0.00966 -0.0306 0.7309 0.0037
-8.250 -0.7398 0.01456 0.00861 -0.0301 0.7292 0.0040
-8.000 -0.7161 0.01388 0.00782 -0.0297 0.7275 0.0044
-7.750 -0.6917 0.01335 0.00722 -0.0294 0.7258 0.0048
-7.500 -0.6666 0.01294 0.00677 -0.0293 0.7241 0.0054
-7.250 -0.6412 0.01256 0.00630 -0.0291 0.7224 0.0060
-7.000 -0.6156 0.01221 0.00588 -0.0290 0.7209 0.0065
-6.750 -0.5898 0.01185 0.00547 -0.0289 0.7194 0.0068
-6.500 -0.5642 0.01141 0.00500 -0.0287 0.7179 0.0096
-6.250 -0.5378 0.01115 0.00476 -0.0287 0.7163 0.0123
-6.000 -0.5111 0.01092 0.00452 -0.0288 0.7148 0.0142
-5.750 -0.4843 0.01068 0.00424 -0.0288 0.7133 0.0156
-5.500 -0.4573 0.01050 0.00408 -0.0289 0.7119 0.0189
-5.250 -0.4299 0.01036 0.00392 -0.0290 0.7105 0.0213
-5.000 -0.4026 0.01021 0.00374 -0.0292 0.7092 0.0231
-4.750 -0.3750 0.01011 0.00358 -0.0293 0.7079 0.0242
-4.500 -0.3471 0.01004 0.00350 -0.0296 0.7067 0.0248
-4.250 -0.3193 0.00993 0.00339 -0.0298 0.7054 0.0251
-4.000 -0.2924 0.00965 0.00307 -0.0298 0.7039 0.0257
-3.750 -0.2652 0.00940 0.00278 -0.0299 0.7025 0.0263
-3.500 -0.2379 0.00919 0.00255 -0.0300 0.7010 0.0269
-3.250 -0.2103 0.00901 0.00233 -0.0301 0.6997 0.0274
-3.000 -0.1826 0.00885 0.00215 -0.0303 0.6984 0.0281
-2.750 -0.1548 0.00870 0.00199 -0.0305 0.6972 0.0292
-2.500 -0.1270 0.00857 0.00186 -0.0306 0.6960 0.0304
-2.250 -0.0991 0.00846 0.00172 -0.0308 0.6949 0.0315
-1.750 -0.0434 0.00815 0.00151 -0.0312 0.6928 0.0570
-1.500 -0.0164 0.00781 0.00139 -0.0314 0.6917 0.1205
-1.250 0.0085 0.00711 0.00121 -0.0315 0.6906 0.2816
-1.000 0.0290 0.00567 0.00094 -0.0311 0.6894 0.6264
-0.750 0.0573 0.00565 0.00098 -0.0313 0.6882 0.6616
-0.500 0.0860 0.00566 0.00101 -0.0316 0.6871 0.6759
-0.250 0.1148 0.00566 0.00103 -0.0318 0.6859 0.6827
0.000 0.1436 0.00568 0.00104 -0.0321 0.6843 0.6888
0.250 0.1724 0.00570 0.00104 -0.0324 0.6826 0.6936
0.500 0.2010 0.00571 0.00107 -0.0327 0.6809 0.6981
0.750 0.2299 0.00573 0.00109 -0.0330 0.6766 0.7051
1.000 0.2585 0.00571 0.00109 -0.0332 0.6707 0.7079
1.250 0.2870 0.00572 0.00109 -0.0335 0.6660 0.7105
1.500 0.3158 0.00570 0.00110 -0.0338 0.6583 0.7120
1.750 0.3443 0.00571 0.00110 -0.0340 0.6469 0.7135
2.000 0.3726 0.00574 0.00109 -0.0342 0.6297 0.7149
2.250 0.4002 0.00585 0.00110 -0.0343 0.5965 0.7160
2.500 0.4173 0.00725 0.00163 -0.0331 0.3730 0.7172
2.750 0.4422 0.00772 0.00186 -0.0330 0.3044 0.7184
3.000 0.4655 0.00835 0.00214 -0.0327 0.2171 0.7195
3.250 0.4896 0.00884 0.00239 -0.0324 0.1532 0.7205
3.500 0.5142 0.00923 0.00262 -0.0322 0.1084 0.7217
3.750 0.5389 0.00962 0.00286 -0.0320 0.0711 0.7228
4.000 0.5633 0.01001 0.00313 -0.0317 0.0388 0.7240
4.250 0.5892 0.01024 0.00335 -0.0316 0.0337 0.7252
4.500 0.6152 0.01046 0.00358 -0.0315 0.0303 0.7265
4.750 0.6410 0.01068 0.00380 -0.0314 0.0273 0.7279
5.000 0.6665 0.01093 0.00405 -0.0312 0.0250 0.7293
5.250 0.6920 0.01117 0.00431 -0.0311 0.0235 0.7307
5.500 0.7181 0.01135 0.00454 -0.0310 0.0228 0.7321
5.750 0.7437 0.01155 0.00476 -0.0309 0.0197 0.7335
6.000 0.7680 0.01185 0.00503 -0.0306 0.0130 0.7351
6.250 0.7919 0.01218 0.00534 -0.0302 0.0095 0.7368
6.500 0.8151 0.01257 0.00578 -0.0296 0.0068 0.7387
6.750 0.8387 0.01290 0.00616 -0.0291 0.0064 0.7406
7.000 0.8619 0.01326 0.00656 -0.0286 0.0059 0.7425
7.250 0.8846 0.01364 0.00698 -0.0280 0.0053 0.7445
7.500 0.9067 0.01406 0.00743 -0.0274 0.0048 0.7465
8.000 0.9479 0.01511 0.00859 -0.0256 0.0039 0.7506
8.250 0.9650 0.01592 0.00957 -0.0241 0.0036 0.7531
8.500 0.9854 0.01641 0.01013 -0.0232 0.0035 0.7557
8.750 1.0045 0.01700 0.01080 -0.0221 0.0034 0.7584
9.000 1.0226 0.01766 0.01154 -0.0209 0.0033 0.7611
9.250 1.0401 0.01816 0.01211 -0.0195 0.0031 0.7639
9.500 1.0551 0.01885 0.01291 -0.0177 0.0031 0.7672
9.750 1.0702 0.01958 0.01373 -0.0161 0.0029 0.7709
10.000 1.0851 0.02035 0.01460 -0.0145 0.0028 0.7748
10.250 1.0998 0.02118 0.01554 -0.0130 0.0027 0.7788
10.500 1.1152 0.02190 0.01634 -0.0116 0.0025 0.7836
10.750 1.1288 0.02288 0.01745 -0.0101 0.0025 0.7885
11.000 1.1415 0.02396 0.01869 -0.0086 0.0024 0.7934
11.250 1.1546 0.02492 0.01977 -0.0072 0.0024 0.7993
11.500 1.1688 0.02568 0.02060 -0.0061 0.0023 0.8053
11.750 1.1806 0.02670 0.02173 -0.0047 0.0022 0.8126
12.000 1.1912 0.02785 0.02300 -0.0033 0.0021 0.8204
12.250 1.1966 0.02954 0.02488 -0.0015 0.0020 0.8301
12.500 1.1987 0.03150 0.02706 0.0005 0.0020 0.8417
12.750 1.1948 0.03405 0.02989 0.0028 0.0019 0.8570
13.000 1.1902 0.03648 0.03262 0.0050 0.0019 0.8841
13.250 1.1960 0.03933 0.03588 0.0042 0.0018 1.0000
13.500 1.1956 0.04170 0.03840 0.0053 0.0018 1.0000
13.750 1.1920 0.04444 0.04130 0.0063 0.0018 1.0000
14.000 1.1895 0.04711 0.04411 0.0070 0.0018 1.0000
14.250 1.1676 0.05220 0.04945 0.0076 0.0018 1.0000
14.500 1.1512 0.05691 0.05434 0.0074 0.0018 1.0000
14.750 1.1473 0.06025 0.05779 0.0069 0.0018 1.0000
15.000 1.1187 0.06759 0.06536 0.0047 0.0018 1.0000
15.250 1.0951 0.07522 0.07316 0.0012 0.0018 1.0000
15.500 1.0541 0.08900 0.08718 -0.0074 0.0018 1.0000
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