LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Reynolds number: 500,000 Max Cl/Cd: 61.19 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5b-il-500000-n5.txt Download as CSV file: xf-c5b-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL488.2 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8387 0.06674 0.06359 -0.0642 1.0000 0.0132
-13.750 -0.8686 0.05805 0.05470 -0.0700 1.0000 0.0132
-13.500 -0.8934 0.05192 0.04838 -0.0728 1.0000 0.0132
-13.250 -0.9149 0.04733 0.04361 -0.0735 1.0000 0.0132
-13.000 -0.9343 0.04379 0.03990 -0.0725 1.0000 0.0132
-12.750 -0.9528 0.04102 0.03696 -0.0700 1.0000 0.0132
-12.500 -0.9712 0.03887 0.03467 -0.0661 1.0000 0.0132
-12.250 -0.9908 0.03727 0.03293 -0.0609 1.0000 0.0132
-12.000 -0.9968 0.03528 0.03074 -0.0581 0.9982 0.0133
-11.750 -0.9876 0.03307 0.02828 -0.0578 0.9957 0.0134
-11.500 -0.9724 0.03107 0.02604 -0.0579 0.9938 0.0134
-11.250 -0.9582 0.02944 0.02419 -0.0572 0.9912 0.0135
-11.000 -0.9413 0.02777 0.02233 -0.0570 0.9890 0.0136
-10.750 -0.9225 0.02609 0.02047 -0.0569 0.9872 0.0137
-10.500 -0.9008 0.02475 0.01899 -0.0572 0.9859 0.0139
-10.250 -0.8768 0.02362 0.01773 -0.0576 0.9849 0.0140
-10.000 -0.8583 0.02271 0.01673 -0.0567 0.9818 0.0142
-9.750 -0.8359 0.02184 0.01576 -0.0565 0.9797 0.0143
-9.500 -0.8115 0.02101 0.01484 -0.0566 0.9780 0.0145
-9.250 -0.7856 0.02020 0.01396 -0.0570 0.9767 0.0147
-9.000 -0.7586 0.01943 0.01309 -0.0576 0.9756 0.0149
-8.750 -0.7310 0.01869 0.01227 -0.0582 0.9748 0.0151
-8.500 -0.7081 0.01804 0.01155 -0.0578 0.9726 0.0153
-8.250 -0.6867 0.01745 0.01089 -0.0569 0.9696 0.0156
-8.000 -0.6608 0.01686 0.01023 -0.0570 0.9677 0.0160
-7.750 -0.6331 0.01631 0.00962 -0.0575 0.9663 0.0164
-7.500 -0.6048 0.01578 0.00902 -0.0580 0.9651 0.0168
-7.250 -0.5763 0.01523 0.00841 -0.0586 0.9642 0.0172
-7.000 -0.5478 0.01462 0.00777 -0.0593 0.9632 0.0178
-6.750 -0.5182 0.01416 0.00729 -0.0600 0.9624 0.0185
-6.500 -0.4996 0.01385 0.00696 -0.0583 0.9579 0.0192
-6.250 -0.4734 0.01348 0.00655 -0.0582 0.9556 0.0201
-6.000 -0.4452 0.01314 0.00617 -0.0585 0.9539 0.0212
-5.750 -0.4167 0.01272 0.00575 -0.0590 0.9524 0.0227
-5.500 -0.3871 0.01240 0.00542 -0.0596 0.9511 0.0246
-5.250 -0.3568 0.01212 0.00510 -0.0603 0.9499 0.0264
-5.000 -0.3298 0.01181 0.00481 -0.0604 0.9478 0.0289
-4.750 -0.3072 0.01160 0.00459 -0.0594 0.9438 0.0314
-4.500 -0.2800 0.01136 0.00434 -0.0594 0.9412 0.0345
-4.250 -0.2515 0.01109 0.00410 -0.0597 0.9391 0.0397
-4.000 -0.2222 0.01080 0.00383 -0.0602 0.9374 0.0485
-3.750 -0.1931 0.01036 0.00355 -0.0607 0.9356 0.0783
-3.500 -0.1687 0.01001 0.00337 -0.0602 0.9317 0.1174
-3.250 -0.1433 0.00978 0.00320 -0.0597 0.9272 0.1366
-3.000 -0.1155 0.00945 0.00300 -0.0599 0.9241 0.1714
-2.750 -0.0877 0.00902 0.00280 -0.0602 0.9217 0.2296
-2.500 -0.0596 0.00856 0.00260 -0.0606 0.9197 0.3016
-2.250 -0.0395 0.00803 0.00248 -0.0593 0.9146 0.4087
-2.000 -0.0164 0.00749 0.00237 -0.0586 0.9106 0.5209
-1.750 0.0096 0.00713 0.00230 -0.0583 0.9074 0.6015
-1.500 0.0388 0.00696 0.00224 -0.0585 0.9049 0.6399
-1.250 0.0646 0.00689 0.00225 -0.0580 0.9004 0.6653
-1.000 0.0916 0.00684 0.00223 -0.0578 0.8959 0.6837
-0.750 0.1207 0.00676 0.00217 -0.0580 0.8917 0.6992
-0.500 0.1486 0.00668 0.00212 -0.0579 0.8852 0.7133
-0.250 0.1767 0.00658 0.00203 -0.0577 0.8757 0.7268
0.000 0.2032 0.00651 0.00199 -0.0573 0.8641 0.7419
0.250 0.2304 0.00644 0.00195 -0.0569 0.8528 0.7597
0.500 0.2579 0.00638 0.00190 -0.0566 0.8382 0.7752
0.750 0.2857 0.00635 0.00183 -0.0564 0.8179 0.7863
1.000 0.3122 0.00638 0.00176 -0.0558 0.7844 0.7957
1.250 0.3356 0.00654 0.00172 -0.0546 0.7315 0.8060
1.500 0.3570 0.00679 0.00176 -0.0531 0.6781 0.8164
1.750 0.3784 0.00704 0.00185 -0.0516 0.6318 0.8260
2.000 0.3992 0.00736 0.00197 -0.0501 0.5801 0.8347
2.250 0.4194 0.00771 0.00211 -0.0485 0.5208 0.8437
2.500 0.4382 0.00818 0.00230 -0.0467 0.4463 0.8532
2.750 0.4568 0.00874 0.00253 -0.0450 0.3631 0.8637
3.000 0.4757 0.00933 0.00278 -0.0433 0.2792 0.8744
3.250 0.4966 0.00980 0.00301 -0.0421 0.2156 0.8857
4.000 0.5651 0.01073 0.00363 -0.0392 0.1254 0.9224
4.250 0.5897 0.01097 0.00384 -0.0386 0.1119 0.9351
4.500 0.6157 0.01123 0.00407 -0.0383 0.0992 0.9479
4.750 0.6434 0.01151 0.00430 -0.0384 0.0834 0.9603
5.000 0.6726 0.01189 0.00456 -0.0389 0.0650 0.9711
5.250 0.7035 0.01222 0.00484 -0.0399 0.0577 0.9807
5.500 0.7348 0.01256 0.00516 -0.0409 0.0530 0.9897
5.750 0.7667 0.01285 0.00547 -0.0421 0.0507 0.9975
6.000 0.7908 0.01313 0.00576 -0.0415 0.0487 1.0000
6.250 0.8113 0.01344 0.00606 -0.0402 0.0466 1.0000
6.500 0.8320 0.01380 0.00641 -0.0389 0.0444 1.0000
6.750 0.8535 0.01413 0.00676 -0.0378 0.0432 1.0000
7.000 0.8759 0.01441 0.00709 -0.0369 0.0422 1.0000
7.250 0.8982 0.01471 0.00742 -0.0360 0.0408 1.0000
7.500 0.9203 0.01504 0.00778 -0.0350 0.0394 1.0000
7.750 0.9421 0.01540 0.00815 -0.0340 0.0380 1.0000
8.000 0.9630 0.01583 0.00860 -0.0329 0.0365 1.0000
8.250 0.9831 0.01633 0.00913 -0.0317 0.0351 1.0000
8.500 1.0051 0.01665 0.00951 -0.0308 0.0342 1.0000
8.750 1.0262 0.01701 0.00991 -0.0297 0.0329 1.0000
9.000 1.0469 0.01736 0.01031 -0.0286 0.0314 1.0000
9.250 1.0673 0.01774 0.01070 -0.0274 0.0299 1.0000
9.500 1.0867 0.01819 0.01116 -0.0261 0.0284 1.0000
9.750 1.1072 0.01857 0.01160 -0.0250 0.0269 1.0000
10.000 1.1274 0.01896 0.01203 -0.0238 0.0254 1.0000
10.250 1.1470 0.01940 0.01248 -0.0227 0.0241 1.0000
10.500 1.1655 0.01992 0.01304 -0.0213 0.0230 1.0000
10.750 1.1840 0.02044 0.01362 -0.0200 0.0218 1.0000
11.000 1.2024 0.02096 0.01419 -0.0187 0.0207 1.0000
11.250 1.2200 0.02153 0.01480 -0.0173 0.0197 1.0000
11.500 1.2366 0.02219 0.01550 -0.0158 0.0189 1.0000
11.750 1.2528 0.02286 0.01626 -0.0143 0.0182 1.0000
12.000 1.2685 0.02355 0.01703 -0.0128 0.0175 1.0000
12.250 1.2839 0.02428 0.01782 -0.0112 0.0168 1.0000
12.500 1.2982 0.02507 0.01866 -0.0096 0.0160 1.0000
12.750 1.3110 0.02599 0.01965 -0.0079 0.0153 1.0000
13.000 1.3243 0.02685 0.02062 -0.0062 0.0147 1.0000
13.250 1.3369 0.02777 0.02164 -0.0046 0.0141 1.0000
13.500 1.3486 0.02877 0.02273 -0.0029 0.0134 1.0000
13.750 1.3589 0.02988 0.02391 -0.0012 0.0128 1.0000
14.000 1.3665 0.03121 0.02533 0.0006 0.0123 1.0000
14.250 1.3755 0.03245 0.02668 0.0023 0.0119 1.0000
14.500 1.3833 0.03379 0.02817 0.0040 0.0114 1.0000
14.750 1.3899 0.03527 0.02977 0.0055 0.0109 1.0000
15.000 1.3954 0.03689 0.03150 0.0070 0.0105 1.0000
15.250 1.3993 0.03868 0.03340 0.0085 0.0101 1.0000
15.500 1.4010 0.04074 0.03557 0.0097 0.0098 1.0000
15.750 1.4007 0.04309 0.03803 0.0109 0.0095 1.0000
16.000 1.4003 0.04552 0.04062 0.0118 0.0092 1.0000
16.250 1.3981 0.04830 0.04354 0.0124 0.0090 1.0000
16.500 1.3940 0.05143 0.04683 0.0126 0.0087 1.0000
16.750 1.3878 0.05502 0.05057 0.0124 0.0085 1.0000
17.000 1.3795 0.05915 0.05487 0.0116 0.0084 1.0000
17.250 1.3690 0.06388 0.05976 0.0102 0.0082 1.0000
17.500 1.3547 0.06951 0.06556 0.0079 0.0081 1.0000
17.750 1.3359 0.07632 0.07255 0.0047 0.0081 1.0000
18.000 1.3110 0.08475 0.08118 0.0003 0.0081 1.0000
18.250 1.2758 0.09568 0.09233 -0.0059 0.0081 1.0000
18.500 1.2248 0.11043 0.10733 -0.0141 0.0084 1.0000
18.750 1.1553 0.12942 0.12657 -0.0244 0.0089 1.0000
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Polar data table (+)
Polar graphs
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