P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il) Reynolds number: 200,000 Max Cl/Cd: 49.38 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51dtip-il-200000-n5.txt Download as CSV file: xf-p51dtip-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5279 0.09016 0.08643 -0.0347 0.8345 0.0124
-10.250 -0.5350 0.08407 0.08035 -0.0385 0.8311 0.0122
-10.000 -0.5478 0.07636 0.07265 -0.0445 0.8271 0.0121
-9.750 -0.5645 0.06982 0.06605 -0.0488 0.8231 0.0119
-9.500 -0.5842 0.06451 0.06062 -0.0508 0.8193 0.0118
-9.250 -0.6025 0.06028 0.05627 -0.0509 0.8154 0.0117
-9.000 -0.6191 0.05609 0.05191 -0.0497 0.8117 0.0117
-8.750 -0.6289 0.05145 0.04700 -0.0485 0.8086 0.0117
-8.500 -0.6348 0.04650 0.04171 -0.0469 0.8060 0.0118
-8.250 -0.6367 0.04124 0.03601 -0.0451 0.8034 0.0120
-8.000 -0.6333 0.03600 0.03023 -0.0432 0.8005 0.0123
-7.750 -0.6238 0.03139 0.02499 -0.0414 0.7977 0.0131
-7.500 -0.6064 0.02844 0.02152 -0.0403 0.7953 0.0142
-7.250 -0.5864 0.02630 0.01899 -0.0395 0.7931 0.0154
-7.000 -0.5653 0.02504 0.01756 -0.0391 0.7913 0.0169
-6.750 -0.5418 0.02379 0.01610 -0.0387 0.7893 0.0185
-6.500 -0.5173 0.02237 0.01443 -0.0383 0.7871 0.0211
-6.250 -0.4919 0.02141 0.01318 -0.0380 0.7850 0.0242
-6.000 -0.4674 0.02054 0.01220 -0.0378 0.7830 0.0269
-5.750 -0.4427 0.01981 0.01139 -0.0376 0.7811 0.0294
-5.500 -0.4171 0.01939 0.01078 -0.0374 0.7794 0.0329
-5.250 -0.3937 0.01831 0.00968 -0.0369 0.7778 0.0352
-5.000 -0.3692 0.01768 0.00896 -0.0366 0.7759 0.0374
-4.750 -0.3444 0.01712 0.00834 -0.0364 0.7737 0.0394
-4.500 -0.3194 0.01665 0.00778 -0.0362 0.7718 0.0410
-4.250 -0.2949 0.01614 0.00722 -0.0359 0.7700 0.0426
-4.000 -0.2706 0.01566 0.00672 -0.0357 0.7683 0.0462
-3.750 -0.2452 0.01531 0.00632 -0.0355 0.7668 0.0489
-3.500 -0.2196 0.01499 0.00587 -0.0354 0.7654 0.0510
-3.250 -0.1937 0.01470 0.00550 -0.0352 0.7641 0.0545
-3.000 -0.1681 0.01437 0.00518 -0.0351 0.7629 0.0657
-2.750 -0.1445 0.01370 0.00487 -0.0350 0.7609 0.1395
-2.500 -0.1272 0.01227 0.00447 -0.0344 0.7588 0.3930
-2.250 -0.1107 0.01169 0.00494 -0.0321 0.7569 0.6709
-2.000 -0.0845 0.01194 0.00518 -0.0315 0.7554 0.7080
-1.750 -0.0590 0.01226 0.00550 -0.0306 0.7540 0.7350
-1.500 -0.0335 0.01254 0.00579 -0.0297 0.7528 0.7520
-1.250 -0.0078 0.01278 0.00600 -0.0290 0.7516 0.7658
-1.000 0.0189 0.01293 0.00609 -0.0287 0.7506 0.7760
-0.750 0.0463 0.01297 0.00610 -0.0286 0.7497 0.7788
-0.500 0.0744 0.01300 0.00610 -0.0290 0.7484 0.7806
-0.250 0.1026 0.01304 0.00613 -0.0294 0.7467 0.7819
0.000 0.1308 0.01308 0.00616 -0.0299 0.7450 0.7833
0.250 0.1590 0.01312 0.00620 -0.0303 0.7434 0.7848
0.500 0.1873 0.01317 0.00624 -0.0308 0.7421 0.7863
0.750 0.2156 0.01323 0.00630 -0.0312 0.7409 0.7876
1.000 0.2440 0.01329 0.00638 -0.0317 0.7398 0.7890
1.250 0.2723 0.01337 0.00647 -0.0322 0.7388 0.7903
1.500 0.3003 0.01344 0.00659 -0.0325 0.7378 0.7914
1.750 0.3283 0.01353 0.00673 -0.0328 0.7370 0.7925
2.000 0.3563 0.01361 0.00687 -0.0330 0.7360 0.7940
2.250 0.3838 0.01372 0.00707 -0.0333 0.7337 0.7956
2.500 0.4108 0.01384 0.00729 -0.0336 0.7303 0.7974
2.750 0.4386 0.01371 0.00724 -0.0335 0.7253 0.7991
3.000 0.4659 0.01322 0.00677 -0.0328 0.7133 0.8008
3.250 0.4936 0.01245 0.00597 -0.0319 0.6951 0.8026
3.500 0.5203 0.01205 0.00563 -0.0314 0.6753 0.8044
3.750 0.5470 0.01181 0.00552 -0.0310 0.6560 0.8059
4.000 0.5733 0.01161 0.00539 -0.0305 0.6260 0.8076
4.250 0.5852 0.01218 0.00494 -0.0273 0.4060 0.8099
4.500 0.5966 0.01347 0.00566 -0.0253 0.2771 0.8127
4.750 0.6113 0.01450 0.00627 -0.0238 0.1842 0.8158
5.000 0.6278 0.01539 0.00684 -0.0226 0.1143 0.8187
5.250 0.6450 0.01615 0.00742 -0.0213 0.0724 0.8211
5.500 0.6644 0.01676 0.00799 -0.0202 0.0561 0.8238
5.750 0.6839 0.01737 0.00867 -0.0192 0.0481 0.8269
6.000 0.7044 0.01789 0.00927 -0.0184 0.0425 0.8303
6.250 0.7232 0.01851 0.00992 -0.0173 0.0363 0.8335
6.500 0.7400 0.01925 0.01069 -0.0160 0.0313 0.8369
6.750 0.7597 0.01978 0.01132 -0.0150 0.0256 0.8409
7.000 0.7760 0.02067 0.01227 -0.0136 0.0223 0.8456
7.250 0.7926 0.02152 0.01328 -0.0120 0.0194 0.8500
7.500 0.8099 0.02240 0.01424 -0.0106 0.0168 0.8554
7.750 0.8269 0.02345 0.01535 -0.0094 0.0149 0.8611
8.000 0.8468 0.02454 0.01657 -0.0084 0.0135 0.8670
8.250 0.8703 0.02602 0.01824 -0.0080 0.0126 0.8732
8.500 0.8956 0.02784 0.02031 -0.0077 0.0117 0.8795
8.750 0.9197 0.03000 0.02288 -0.0073 0.0111 0.8874
9.000 0.9405 0.03250 0.02579 -0.0065 0.0106 0.8978
9.500 0.9757 0.03702 0.03110 -0.0053 0.0092 1.0000
9.750 0.9855 0.03876 0.03306 -0.0039 0.0086 1.0000
10.000 0.9898 0.04083 0.03535 -0.0018 0.0082 1.0000
10.250 0.9887 0.04345 0.03825 0.0006 0.0080 1.0000
10.500 0.9829 0.04638 0.04144 0.0031 0.0078 1.0000
10.750 0.9733 0.04990 0.04526 0.0053 0.0078 1.0000
11.000 0.9598 0.05371 0.04933 0.0071 0.0078 1.0000
11.250 0.9436 0.05796 0.05384 0.0084 0.0078 1.0000
11.500 0.9252 0.06253 0.05863 0.0090 0.0078 1.0000
11.750 0.9049 0.06765 0.06395 0.0086 0.0078 1.0000
12.000 0.8764 0.07498 0.07151 0.0069 0.0080 1.0000
12.250 0.8465 0.08362 0.08035 0.0031 0.0081 1.0000
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Polar data table (+)
Polar graphs
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