P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.22 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-p51dtip-il-1000000.txt Download as CSV file: xf-p51dtip-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4688 0.09276 0.09057 -0.0231 0.7723 0.0086
-10.750 -0.4818 0.08474 0.08257 -0.0267 0.7716 0.0084
-9.750 -0.8314 0.02802 0.02411 -0.0381 0.7710 0.0061
-9.500 -0.8209 0.02530 0.02105 -0.0366 0.7688 0.0063
-9.250 -0.8044 0.02350 0.01900 -0.0357 0.7665 0.0064
-9.000 -0.7861 0.02191 0.01714 -0.0348 0.7645 0.0065
-8.750 -0.7735 0.01870 0.01345 -0.0332 0.7626 0.0068
-8.500 -0.7546 0.01698 0.01147 -0.0323 0.7606 0.0072
-8.250 -0.7316 0.01616 0.01055 -0.0318 0.7588 0.0076
-8.000 -0.7075 0.01553 0.00985 -0.0316 0.7572 0.0080
-7.750 -0.6828 0.01502 0.00927 -0.0314 0.7554 0.0086
-7.500 -0.6575 0.01460 0.00879 -0.0312 0.7535 0.0092
-7.250 -0.6312 0.01436 0.00850 -0.0312 0.7517 0.0098
-7.000 -0.6102 0.01312 0.00710 -0.0303 0.7500 0.0110
-6.750 -0.5836 0.01294 0.00693 -0.0304 0.7482 0.0122
-6.500 -0.5571 0.01274 0.00668 -0.0304 0.7463 0.0134
-6.250 -0.5293 0.01270 0.00662 -0.0305 0.7448 0.0143
-6.000 -0.5053 0.01201 0.00591 -0.0302 0.7433 0.0168
-5.750 -0.4775 0.01195 0.00586 -0.0304 0.7418 0.0186
-5.500 -0.4490 0.01201 0.00590 -0.0307 0.7402 0.0202
-5.250 -0.4236 0.01154 0.00538 -0.0306 0.7387 0.0218
-5.000 -0.3987 0.01098 0.00479 -0.0303 0.7372 0.0241
-4.750 -0.3718 0.01077 0.00457 -0.0304 0.7357 0.0259
-4.500 -0.3449 0.01055 0.00430 -0.0305 0.7344 0.0276
-4.250 -0.3179 0.01035 0.00406 -0.0305 0.7329 0.0290
-4.000 -0.2905 0.01023 0.00392 -0.0306 0.7314 0.0298
-3.750 -0.2647 0.00975 0.00337 -0.0305 0.7302 0.0316
-3.500 -0.2379 0.00941 0.00300 -0.0305 0.7288 0.0343
-3.250 -0.2105 0.00919 0.00275 -0.0306 0.7273 0.0360
-3.000 -0.1829 0.00900 0.00255 -0.0307 0.7259 0.0380
-2.750 -0.1552 0.00884 0.00237 -0.0309 0.7246 0.0405
-2.500 -0.1279 0.00859 0.00217 -0.0309 0.7234 0.0585
-2.250 -0.1045 0.00769 0.00190 -0.0308 0.7221 0.2357
-2.000 -0.0839 0.00630 0.00149 -0.0305 0.7209 0.5145
-1.750 -0.0586 0.00593 0.00153 -0.0303 0.7197 0.6606
-1.500 -0.0302 0.00598 0.00158 -0.0304 0.7185 0.6800
-1.250 -0.0017 0.00607 0.00167 -0.0306 0.7173 0.6954
-1.000 0.0269 0.00611 0.00172 -0.0308 0.7164 0.7053
-0.750 0.0557 0.00618 0.00179 -0.0311 0.7154 0.7134
-0.500 0.0841 0.00623 0.00187 -0.0312 0.7143 0.7223
-0.250 0.1128 0.00633 0.00196 -0.0314 0.7131 0.7296
0.000 0.1413 0.00632 0.00198 -0.0317 0.7117 0.7340
0.250 0.1701 0.00633 0.00199 -0.0320 0.7101 0.7366
0.500 0.1990 0.00634 0.00200 -0.0323 0.7085 0.7388
0.750 0.2279 0.00635 0.00200 -0.0326 0.7071 0.7402
1.000 0.2569 0.00637 0.00201 -0.0330 0.7057 0.7414
1.250 0.2857 0.00642 0.00205 -0.0333 0.7033 0.7428
1.500 0.3145 0.00635 0.00200 -0.0336 0.6994 0.7441
1.750 0.3429 0.00619 0.00182 -0.0337 0.6909 0.7456
2.000 0.3713 0.00605 0.00170 -0.0338 0.6809 0.7468
2.250 0.3998 0.00600 0.00167 -0.0340 0.6732 0.7479
2.500 0.4286 0.00597 0.00168 -0.0343 0.6678 0.7490
2.750 0.4570 0.00596 0.00168 -0.0345 0.6607 0.7502
3.000 0.4856 0.00594 0.00170 -0.0348 0.6505 0.7515
3.250 0.5137 0.00595 0.00170 -0.0349 0.6334 0.7528
3.500 0.5407 0.00606 0.00171 -0.0349 0.5879 0.7541
3.750 0.5527 0.00792 0.00246 -0.0330 0.3197 0.7556
4.000 0.5723 0.00887 0.00290 -0.0322 0.1962 0.7570
4.250 0.5929 0.00967 0.00330 -0.0315 0.1051 0.7582
4.500 0.6138 0.01035 0.00369 -0.0307 0.0426 0.7600
4.750 0.6391 0.01061 0.00396 -0.0305 0.0365 0.7615
5.000 0.6639 0.01092 0.00427 -0.0302 0.0318 0.7631
5.250 0.6886 0.01123 0.00464 -0.0299 0.0289 0.7648
5.500 0.7142 0.01143 0.00488 -0.0297 0.0271 0.7666
5.750 0.7390 0.01171 0.00515 -0.0295 0.0235 0.7686
6.000 0.7626 0.01209 0.00555 -0.0290 0.0193 0.7706
6.250 0.7876 0.01233 0.00576 -0.0288 0.0159 0.7725
6.500 0.8092 0.01283 0.00632 -0.0279 0.0130 0.7748
6.750 0.8326 0.01316 0.00669 -0.0274 0.0116 0.7770
7.000 0.8546 0.01361 0.00716 -0.0267 0.0103 0.7794
7.250 0.8706 0.01459 0.00826 -0.0250 0.0092 0.7821
7.500 0.8927 0.01502 0.00873 -0.0242 0.0088 0.7847
7.750 0.9140 0.01549 0.00925 -0.0234 0.0081 0.7874
8.000 0.9342 0.01600 0.00984 -0.0225 0.0076 0.7904
8.250 0.9535 0.01660 0.01051 -0.0214 0.0071 0.7938
8.500 0.9723 0.01726 0.01122 -0.0203 0.0068 0.7973
8.750 0.9886 0.01820 0.01225 -0.0188 0.0065 0.8010
9.000 1.0015 0.01982 0.01405 -0.0168 0.0062 0.8051
9.250 1.0182 0.02165 0.01610 -0.0155 0.0060 0.8095
9.500 1.0360 0.02275 0.01734 -0.0143 0.0059 0.8144
9.750 1.0519 0.02331 0.01803 -0.0127 0.0057 0.8200
10.000 1.0670 0.02471 0.01963 -0.0112 0.0056 0.8263
10.250 1.0801 0.02568 0.02077 -0.0094 0.0053 0.8334
10.500 1.0905 0.02746 0.02278 -0.0074 0.0052 0.8420
10.750 1.0972 0.02931 0.02489 -0.0050 0.0050 0.8532
11.000 1.0990 0.03150 0.02737 -0.0022 0.0049 0.8693
11.250 1.0969 0.03326 0.02953 0.0012 0.0047 0.9197
11.500 1.0691 0.04091 0.03792 0.0041 0.0049 1.0000
11.750 1.0234 0.04866 0.04614 0.0081 0.0051 1.0000
12.000 0.9871 0.05527 0.05303 0.0099 0.0053 1.0000
12.250 0.9553 0.06157 0.05955 0.0102 0.0054 1.0000
12.500 0.9251 0.06836 0.06652 0.0089 0.0055 1.0000
12.750 0.8954 0.07604 0.07435 0.0060 0.0055 1.0000
13.000 0.8708 0.08433 0.08276 0.0010 0.0056 1.0000
13.250 0.8043 0.08376 0.08233 -0.0021 0.0054 1.0000
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Polar data table (+)
Polar graphs
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