P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il) Reynolds number: 100,000 Max Cl/Cd: 35.45 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51dtip-il-100000-n5.txt Download as CSV file: xf-p51dtip-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5127 0.09605 0.09161 -0.0349 1.0000 0.0238
-10.250 -0.5148 0.09054 0.08614 -0.0389 0.9596 0.0237
-10.000 -0.5153 0.08292 0.07849 -0.0465 0.9356 0.0236
-9.750 -0.5212 0.07599 0.07147 -0.0529 0.9198 0.0233
-9.500 -0.5332 0.07028 0.06563 -0.0570 0.9071 0.0232
-9.250 -0.5461 0.06588 0.06110 -0.0587 0.8967 0.0230
-8.750 -0.5711 0.05815 0.05294 -0.0580 0.8806 0.0232
-8.500 -0.5773 0.05412 0.04859 -0.0571 0.8748 0.0234
-8.250 -0.5790 0.05000 0.04410 -0.0560 0.8696 0.0236
-8.000 -0.5764 0.04598 0.03965 -0.0548 0.8650 0.0238
-7.750 -0.5704 0.04202 0.03514 -0.0532 0.8612 0.0243
-7.500 -0.5598 0.03834 0.03080 -0.0517 0.8576 0.0249
-7.250 -0.5447 0.03533 0.02744 -0.0509 0.8539 0.0260
-7.000 -0.5253 0.03402 0.02600 -0.0506 0.8505 0.0286
-6.750 -0.5055 0.03192 0.02333 -0.0496 0.8475 0.0321
-6.500 -0.4835 0.02956 0.02056 -0.0489 0.8448 0.0342
-6.250 -0.4595 0.02811 0.01896 -0.0488 0.8417 0.0370
-6.000 -0.4350 0.02708 0.01758 -0.0484 0.8389 0.0424
-5.750 -0.4097 0.02536 0.01580 -0.0483 0.8366 0.0449
-5.500 -0.3838 0.02414 0.01444 -0.0480 0.8345 0.0477
-5.250 -0.3586 0.02313 0.01320 -0.0475 0.8326 0.0508
-5.000 -0.3336 0.02236 0.01227 -0.0472 0.8301 0.0534
-4.750 -0.3109 0.02157 0.01156 -0.0469 0.8274 0.0587
-4.500 -0.2873 0.02105 0.01094 -0.0465 0.8247 0.0638
-4.250 -0.2643 0.02050 0.01027 -0.0458 0.8224 0.0660
-4.000 -0.2418 0.01993 0.00966 -0.0451 0.8204 0.0698
-3.750 -0.2182 0.01953 0.00916 -0.0445 0.8187 0.0763
-3.500 -0.1951 0.01907 0.00870 -0.0441 0.8166 0.0918
-3.250 -0.1773 0.01809 0.00834 -0.0432 0.8142 0.2019
-3.000 -0.1752 0.01669 0.00900 -0.0383 0.8115 0.6154
-2.750 -0.1535 0.01713 0.00929 -0.0368 0.8093 0.7059
-2.500 -0.1348 0.01805 0.01024 -0.0331 0.8074 0.7562
-2.250 -0.1193 0.01910 0.01131 -0.0276 0.8058 0.8020
-2.000 -0.0974 0.01954 0.01169 -0.0248 0.8045 0.8232
-1.750 -0.0741 0.01961 0.01165 -0.0244 0.8023 0.8301
-1.500 -0.0497 0.01963 0.01156 -0.0244 0.8003 0.8338
-1.250 -0.0242 0.01965 0.01147 -0.0245 0.7984 0.8362
-1.000 0.0012 0.01966 0.01139 -0.0247 0.7966 0.8382
-0.750 0.0267 0.01967 0.01132 -0.0249 0.7948 0.8402
-0.500 0.0526 0.01967 0.01124 -0.0251 0.7932 0.8420
-0.250 0.0787 0.01970 0.01120 -0.0254 0.7918 0.8437
0.000 0.1046 0.01976 0.01121 -0.0258 0.7905 0.8456
0.250 0.1282 0.01995 0.01141 -0.0259 0.7883 0.8475
0.500 0.1521 0.02014 0.01161 -0.0260 0.7863 0.8494
0.750 0.1764 0.02032 0.01180 -0.0261 0.7843 0.8512
1.000 0.2014 0.02048 0.01198 -0.0263 0.7824 0.8531
1.250 0.2268 0.02065 0.01217 -0.0265 0.7807 0.8551
1.500 0.2524 0.02085 0.01240 -0.0268 0.7795 0.8573
1.750 0.2783 0.02106 0.01265 -0.0272 0.7783 0.8598
2.000 0.3047 0.02127 0.01293 -0.0274 0.7773 0.8618
2.250 0.3243 0.02171 0.01348 -0.0271 0.7743 0.8646
2.500 0.3449 0.02213 0.01400 -0.0268 0.7716 0.8674
2.750 0.3676 0.02247 0.01444 -0.0267 0.7691 0.8702
3.000 0.3942 0.02265 0.01472 -0.0269 0.7663 0.8728
3.250 0.4244 0.02268 0.01489 -0.0273 0.7638 0.8749
3.500 0.4412 0.02308 0.01544 -0.0263 0.7571 0.8786
3.750 0.4783 0.02244 0.01494 -0.0265 0.7500 0.8806
4.000 0.5105 0.02148 0.01411 -0.0255 0.7358 0.8833
4.250 0.5369 0.02057 0.01340 -0.0239 0.7174 0.8867
4.500 0.5666 0.01878 0.01172 -0.0215 0.6873 0.8893
4.750 0.5882 0.01764 0.01074 -0.0191 0.6450 0.8933
5.000 0.6040 0.01761 0.01091 -0.0173 0.5936 0.8991
5.250 0.6169 0.01740 0.00907 -0.0121 0.3133 0.9034
5.500 0.6215 0.01878 0.00987 -0.0093 0.1981 0.9110
5.750 0.6345 0.01988 0.01054 -0.0076 0.1175 0.9189
6.000 0.6530 0.02085 0.01141 -0.0066 0.0838 0.9280
6.250 0.6762 0.02172 0.01228 -0.0064 0.0673 0.9383
6.500 0.7014 0.02272 0.01334 -0.0068 0.0572 0.9525
6.750 0.7261 0.02392 0.01456 -0.0074 0.0479 1.0000
7.000 0.7452 0.02492 0.01558 -0.0068 0.0399 1.0000
7.250 0.7652 0.02636 0.01710 -0.0061 0.0353 1.0000
7.500 0.7866 0.02776 0.01847 -0.0058 0.0301 1.0000
7.750 0.8119 0.02924 0.02011 -0.0057 0.0264 1.0000
8.000 0.8382 0.03125 0.02214 -0.0059 0.0242 1.0000
8.250 0.8679 0.03388 0.02506 -0.0062 0.0228 1.0000
8.500 0.8922 0.03653 0.02819 -0.0057 0.0209 1.0000
8.750 0.9106 0.03907 0.03115 -0.0048 0.0190 1.0000
9.000 0.9247 0.04181 0.03426 -0.0036 0.0178 1.0000
9.250 0.9343 0.04501 0.03801 -0.0020 0.0173 1.0000
9.500 0.9388 0.04832 0.04170 -0.0001 0.0170 1.0000
9.750 0.9382 0.05171 0.04544 0.0021 0.0168 1.0000
10.000 0.9312 0.05502 0.04906 0.0047 0.0167 1.0000
10.250 0.9197 0.05849 0.05280 0.0072 0.0167 1.0000
10.500 0.9051 0.06222 0.05678 0.0090 0.0167 1.0000
10.750 0.8879 0.06644 0.06124 0.0101 0.0169 1.0000
11.000 0.8686 0.07110 0.06610 0.0103 0.0169 1.0000
11.250 0.8472 0.07647 0.07165 0.0094 0.0172 1.0000
11.500 0.8237 0.08279 0.07813 0.0072 0.0174 1.0000
11.750 0.7997 0.09041 0.08587 0.0033 0.0177 1.0000
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Polar data table (+)
Polar graphs
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