LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Reynolds number: 50,000 Max Cl/Cd: 29.4 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5b-il-50000-n5.txt Download as CSV file: xf-c5b-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5609 0.09654 0.08871 -0.0463 1.0000 0.0576
-10.250 -0.5746 0.09012 0.08234 -0.0494 1.0000 0.0571
-10.000 -0.5951 0.08396 0.07621 -0.0521 1.0000 0.0564
-9.750 -0.6211 0.07873 0.07100 -0.0532 1.0000 0.0556
-9.500 -0.6506 0.07475 0.06700 -0.0518 1.0000 0.0550
-9.250 -0.6776 0.07121 0.06341 -0.0489 1.0000 0.0546
-9.000 -0.6978 0.06763 0.05970 -0.0462 1.0000 0.0544
-8.750 -0.7131 0.06419 0.05607 -0.0434 1.0000 0.0545
-8.500 -0.7237 0.06083 0.05249 -0.0405 1.0000 0.0547
-8.250 -0.7300 0.05755 0.04893 -0.0378 1.0000 0.0551
-8.000 -0.7324 0.05434 0.04541 -0.0352 1.0000 0.0556
-7.750 -0.7310 0.05122 0.04192 -0.0327 1.0000 0.0562
-7.500 -0.7259 0.04821 0.03851 -0.0303 1.0000 0.0566
-7.250 -0.7173 0.04535 0.03524 -0.0282 1.0000 0.0571
-7.000 -0.7055 0.04269 0.03213 -0.0262 1.0000 0.0578
-6.750 -0.6910 0.04031 0.02928 -0.0244 1.0000 0.0591
-6.500 -0.6745 0.03829 0.02704 -0.0230 1.0000 0.0611
-6.250 -0.6567 0.03674 0.02539 -0.0218 1.0000 0.0637
-6.000 -0.6373 0.03514 0.02358 -0.0205 1.0000 0.0663
-5.750 -0.6159 0.03354 0.02169 -0.0193 1.0000 0.0687
-5.500 -0.5942 0.03214 0.02008 -0.0181 1.0000 0.0723
-5.250 -0.5741 0.03103 0.01901 -0.0170 1.0000 0.0772
-5.000 -0.5522 0.02996 0.01777 -0.0158 1.0000 0.0826
-4.750 -0.5314 0.02892 0.01671 -0.0145 1.0000 0.0884
-4.500 -0.5106 0.02806 0.01576 -0.0133 1.0000 0.0983
-4.250 -0.4901 0.02716 0.01480 -0.0122 1.0000 0.1110
-4.000 -0.4700 0.02609 0.01388 -0.0112 1.0000 0.1321
-3.750 -0.4495 0.02483 0.01289 -0.0105 1.0000 0.1764
-3.500 -0.4313 0.02335 0.01209 -0.0098 1.0000 0.2765
-3.250 -0.4169 0.02188 0.01184 -0.0077 1.0000 0.4733
-3.000 -0.4056 0.02158 0.01239 -0.0027 1.0000 0.6601
-2.750 -0.3933 0.02178 0.01275 0.0022 1.0000 0.7577
-2.500 -0.3761 0.02196 0.01288 0.0056 1.0000 0.8093
-2.250 -0.3549 0.02210 0.01287 0.0077 1.0000 0.8457
-2.000 -0.3287 0.02232 0.01293 0.0089 1.0000 0.8842
-1.750 -0.2828 0.02284 0.01326 0.0065 1.0000 0.9315
-1.500 -0.2077 0.02350 0.01358 -0.0024 1.0000 0.9683
-1.250 -0.1483 0.02372 0.01356 -0.0094 1.0000 0.9884
-1.000 -0.1151 0.02366 0.01336 -0.0119 1.0000 1.0000
-0.750 -0.1139 0.02337 0.01299 -0.0085 1.0000 1.0000
-0.500 -0.1113 0.02313 0.01267 -0.0052 1.0000 1.0000
-0.250 -0.1065 0.02297 0.01243 -0.0023 1.0000 1.0000
0.000 -0.0873 0.02303 0.01239 -0.0020 0.9971 1.0000
0.250 -0.0538 0.02332 0.01256 -0.0043 0.9901 1.0000
0.500 -0.0199 0.02366 0.01279 -0.0067 0.9833 1.0000
0.750 0.0136 0.02399 0.01305 -0.0088 0.9759 1.0000
1.000 0.0457 0.02430 0.01330 -0.0107 0.9677 1.0000
1.250 0.0803 0.02467 0.01363 -0.0129 0.9603 1.0000
1.500 0.1136 0.02501 0.01395 -0.0148 0.9516 1.0000
1.750 0.1452 0.02531 0.01426 -0.0163 0.9421 1.0000
2.000 0.1843 0.02571 0.01467 -0.0192 0.9346 1.0000
2.250 0.2133 0.02596 0.01496 -0.0201 0.9232 1.0000
2.500 0.2451 0.02623 0.01530 -0.0214 0.9126 1.0000
2.750 0.2845 0.02651 0.01566 -0.0241 0.9037 1.0000
3.000 0.3153 0.02670 0.01596 -0.0250 0.8911 1.0000
3.250 0.3479 0.02680 0.01617 -0.0261 0.8773 1.0000
3.500 0.3841 0.02673 0.01624 -0.0275 0.8618 1.0000
3.750 0.4249 0.02639 0.01609 -0.0292 0.8446 1.0000
4.000 0.4575 0.02581 0.01567 -0.0290 0.8194 1.0000
4.250 0.4959 0.02476 0.01482 -0.0289 0.7900 1.0000
4.500 0.5277 0.02392 0.01415 -0.0278 0.7597 1.0000
4.750 0.5565 0.02340 0.01381 -0.0267 0.7290 1.0000
5.000 0.5894 0.02277 0.01336 -0.0260 0.6878 1.0000
5.250 0.6332 0.02188 0.01230 -0.0260 0.5906 1.0000
5.500 0.6601 0.02245 0.01178 -0.0240 0.4087 1.0000
5.750 0.6671 0.02386 0.01240 -0.0205 0.3006 1.0000
6.000 0.6780 0.02520 0.01331 -0.0180 0.2370 1.0000
6.250 0.6922 0.02647 0.01426 -0.0162 0.1958 1.0000
6.500 0.7090 0.02771 0.01531 -0.0147 0.1699 1.0000
6.750 0.7293 0.02890 0.01645 -0.0136 0.1516 1.0000
7.000 0.7525 0.03008 0.01763 -0.0130 0.1374 1.0000
7.250 0.7789 0.03127 0.01883 -0.0129 0.1256 1.0000
7.500 0.8083 0.03258 0.02011 -0.0133 0.1173 1.0000
7.750 0.8411 0.03402 0.02176 -0.0140 0.1100 1.0000
8.000 0.8685 0.03543 0.02318 -0.0141 0.1033 1.0000
8.250 0.8981 0.03718 0.02515 -0.0145 0.0981 1.0000
8.500 0.9233 0.03892 0.02714 -0.0142 0.0931 1.0000
8.750 0.9461 0.04058 0.02882 -0.0138 0.0886 1.0000
9.000 0.9660 0.04275 0.03140 -0.0128 0.0849 1.0000
9.250 0.9825 0.04486 0.03387 -0.0114 0.0810 1.0000
9.500 0.9984 0.04672 0.03589 -0.0101 0.0775 1.0000
9.750 1.0146 0.04902 0.03830 -0.0090 0.0749 1.0000
10.000 1.0182 0.05197 0.04184 -0.0061 0.0727 1.0000
10.250 1.0196 0.05484 0.04516 -0.0032 0.0703 1.0000
10.500 1.0204 0.05758 0.04822 -0.0006 0.0683 1.0000
10.750 1.0198 0.06042 0.05132 0.0020 0.0669 1.0000
11.000 1.0165 0.06339 0.05453 0.0047 0.0659 1.0000
11.250 1.0094 0.06633 0.05766 0.0075 0.0651 1.0000
11.500 1.0036 0.06931 0.06078 0.0099 0.0642 1.0000
11.750 0.9881 0.07291 0.06456 0.0124 0.0637 1.0000
12.000 0.9635 0.07720 0.06909 0.0143 0.0636 1.0000
12.250 0.9377 0.08210 0.07421 0.0149 0.0636 1.0000
12.500 0.9114 0.08777 0.08004 0.0140 0.0637 1.0000
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Polar data table (+)
Polar graphs
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