LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Reynolds number: 1,000,000 Max Cl/Cd: 68.87 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5a-il-1000000.txt Download as CSV file: xf-c5a-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL0 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7849 0.08115 0.07900 -0.0559 1.0000 0.0145
-14.000 -0.8185 0.07244 0.07014 -0.0606 1.0000 0.0144
-13.750 -0.9890 0.04827 0.04495 -0.0647 1.0000 0.0128
-13.500 -1.0096 0.04471 0.04120 -0.0626 1.0000 0.0128
-13.250 -1.0282 0.04166 0.03796 -0.0596 1.0000 0.0127
-13.000 -1.0415 0.03940 0.03555 -0.0564 1.0000 0.0127
-12.750 -1.0528 0.03752 0.03355 -0.0526 1.0000 0.0128
-12.500 -1.0645 0.03580 0.03169 -0.0484 1.0000 0.0128
-12.250 -1.0762 0.03433 0.03009 -0.0436 1.0000 0.0128
-12.000 -1.0890 0.03317 0.02883 -0.0380 1.0000 0.0128
-11.750 -1.1036 0.03228 0.02784 -0.0316 1.0000 0.0129
-11.500 -1.1019 0.03090 0.02634 -0.0283 0.9997 0.0129
-11.250 -1.0834 0.02926 0.02455 -0.0283 0.9985 0.0130
-11.000 -1.0633 0.02775 0.02291 -0.0284 0.9972 0.0131
-10.750 -1.0417 0.02637 0.02140 -0.0286 0.9961 0.0133
-10.500 -1.0183 0.02509 0.02001 -0.0290 0.9952 0.0134
-10.250 -0.9933 0.02394 0.01876 -0.0296 0.9944 0.0136
-10.000 -0.9722 0.02288 0.01761 -0.0292 0.9926 0.0138
-9.750 -0.9490 0.02200 0.01666 -0.0291 0.9910 0.0141
-9.500 -0.9240 0.02117 0.01575 -0.0294 0.9897 0.0144
-9.250 -0.8981 0.02028 0.01478 -0.0298 0.9885 0.0146
-9.000 -0.8712 0.01941 0.01384 -0.0304 0.9875 0.0148
-8.750 -0.8436 0.01865 0.01302 -0.0311 0.9867 0.0150
-8.500 -0.8153 0.01797 0.01228 -0.0319 0.9860 0.0152
-8.250 -0.7859 0.01736 0.01162 -0.0329 0.9854 0.0153
-8.000 -0.7658 0.01683 0.01105 -0.0317 0.9820 0.0154
-7.750 -0.7444 0.01563 0.00980 -0.0313 0.9798 0.0157
-7.500 -0.7183 0.01480 0.00892 -0.0317 0.9784 0.0161
-7.250 -0.6893 0.01419 0.00829 -0.0326 0.9773 0.0165
-7.000 -0.6588 0.01370 0.00778 -0.0337 0.9764 0.0169
-6.750 -0.6273 0.01327 0.00733 -0.0349 0.9757 0.0174
-6.500 -0.5949 0.01287 0.00691 -0.0364 0.9752 0.0181
-6.250 -0.5748 0.01257 0.00659 -0.0350 0.9708 0.0188
-6.000 -0.5447 0.01224 0.00624 -0.0357 0.9689 0.0194
-5.750 -0.5147 0.01164 0.00561 -0.0367 0.9674 0.0212
-5.500 -0.4817 0.01130 0.00527 -0.0381 0.9664 0.0229
-5.250 -0.4481 0.01093 0.00489 -0.0396 0.9656 0.0257
-5.000 -0.4134 0.01058 0.00455 -0.0415 0.9650 0.0298
-4.750 -0.3786 0.01019 0.00420 -0.0433 0.9643 0.0379
-4.500 -0.3480 0.00936 0.00373 -0.0445 0.9634 0.1105
-4.250 -0.3290 0.00905 0.00352 -0.0428 0.9577 0.1377
-3.750 -0.2759 0.00746 0.00277 -0.0436 0.9533 0.3401
-3.500 -0.2482 0.00668 0.00246 -0.0442 0.9516 0.4572
-3.250 -0.2201 0.00625 0.00228 -0.0445 0.9490 0.5263
-3.000 -0.1964 0.00605 0.00217 -0.0436 0.9438 0.5577
-2.750 -0.1672 0.00584 0.00206 -0.0440 0.9409 0.5899
-2.500 -0.1365 0.00571 0.00197 -0.0447 0.9386 0.6124
-2.250 -0.1054 0.00559 0.00189 -0.0454 0.9364 0.6298
-2.000 -0.0789 0.00554 0.00185 -0.0451 0.9318 0.6436
-1.750 -0.0505 0.00544 0.00178 -0.0452 0.9270 0.6524
-1.500 -0.0195 0.00535 0.00166 -0.0458 0.9227 0.6599
-1.250 0.0084 0.00527 0.00160 -0.0458 0.9161 0.6678
-1.000 0.0375 0.00521 0.00152 -0.0460 0.9088 0.6761
-0.750 0.0661 0.00514 0.00148 -0.0461 0.9016 0.6845
-0.500 0.0950 0.00511 0.00142 -0.0463 0.8931 0.6919
-0.250 0.1229 0.00505 0.00137 -0.0462 0.8804 0.6981
0.000 0.1512 0.00503 0.00133 -0.0463 0.8666 0.7052
0.250 0.1791 0.00503 0.00129 -0.0462 0.8484 0.7121
0.500 0.2059 0.00507 0.00126 -0.0458 0.8233 0.7194
0.750 0.2319 0.00517 0.00125 -0.0454 0.7948 0.7257
1.000 0.2573 0.00526 0.00127 -0.0448 0.7666 0.7319
1.250 0.2823 0.00539 0.00130 -0.0441 0.7342 0.7379
1.500 0.3061 0.00557 0.00135 -0.0432 0.6947 0.7435
1.750 0.3275 0.00586 0.00144 -0.0418 0.6384 0.7495
2.000 0.3496 0.00618 0.00154 -0.0407 0.5821 0.7556
2.250 0.3719 0.00649 0.00166 -0.0396 0.5269 0.7613
2.500 0.3942 0.00687 0.00180 -0.0386 0.4570 0.7675
2.750 0.4145 0.00744 0.00200 -0.0373 0.3665 0.7738
3.000 0.4353 0.00798 0.00222 -0.0361 0.2800 0.7805
3.250 0.4578 0.00847 0.00243 -0.0352 0.2107 0.7878
3.500 0.4812 0.00884 0.00265 -0.0345 0.1642 0.7946
3.750 0.5059 0.00915 0.00283 -0.0340 0.1342 0.8012
4.000 0.5317 0.00936 0.00300 -0.0337 0.1185 0.8071
4.250 0.5557 0.00970 0.00321 -0.0331 0.0847 0.8133
4.500 0.5802 0.01004 0.00343 -0.0326 0.0632 0.8198
4.750 0.6056 0.01026 0.00366 -0.0322 0.0570 0.8257
5.000 0.6310 0.01048 0.00388 -0.0318 0.0541 0.8321
5.250 0.6563 0.01075 0.00415 -0.0314 0.0513 0.8384
5.500 0.6807 0.01102 0.00448 -0.0307 0.0491 0.8445
5.750 0.7064 0.01122 0.00472 -0.0304 0.0484 0.8511
6.000 0.7313 0.01144 0.00499 -0.0299 0.0474 0.8572
6.250 0.7560 0.01168 0.00527 -0.0294 0.0460 0.8638
6.500 0.7806 0.01195 0.00556 -0.0289 0.0445 0.8703
6.750 0.8040 0.01224 0.00590 -0.0281 0.0431 0.8770
7.000 0.8263 0.01268 0.00638 -0.0272 0.0412 0.8841
7.250 0.8467 0.01319 0.00698 -0.0258 0.0398 0.8913
7.500 0.8713 0.01338 0.00721 -0.0253 0.0393 0.8988
7.750 0.8947 0.01359 0.00748 -0.0245 0.0385 0.9062
8.000 0.9179 0.01384 0.00779 -0.0238 0.0375 0.9146
8.250 0.9402 0.01407 0.00807 -0.0228 0.0363 0.9230
8.750 0.9816 0.01466 0.00873 -0.0202 0.0337 0.9450
9.000 0.9962 0.01530 0.00946 -0.0178 0.0322 0.9623
9.250 1.0231 0.01541 0.00962 -0.0178 0.0315 0.9822
9.500 1.0520 0.01557 0.00981 -0.0184 0.0302 1.0000
9.750 1.0774 0.01571 0.00993 -0.0183 0.0288 1.0000
10.000 1.1003 0.01598 0.01017 -0.0177 0.0273 1.0000
10.250 1.1207 0.01642 0.01064 -0.0166 0.0259 1.0000
10.500 1.1436 0.01666 0.01090 -0.0160 0.0248 1.0000
10.750 1.1659 0.01693 0.01117 -0.0153 0.0235 1.0000
11.000 1.1864 0.01733 0.01156 -0.0143 0.0222 1.0000
11.250 1.2045 0.01790 0.01216 -0.0129 0.0211 1.0000
11.500 1.2247 0.01830 0.01262 -0.0119 0.0203 1.0000
11.750 1.2442 0.01874 0.01308 -0.0107 0.0193 1.0000
12.000 1.2625 0.01926 0.01361 -0.0095 0.0184 1.0000
12.250 1.2763 0.02009 0.01448 -0.0076 0.0174 1.0000
12.500 1.2943 0.02061 0.01507 -0.0063 0.0169 1.0000
12.750 1.3114 0.02119 0.01571 -0.0050 0.0162 1.0000
13.000 1.3277 0.02181 0.01637 -0.0036 0.0155 1.0000
13.250 1.3421 0.02256 0.01716 -0.0020 0.0148 1.0000
13.500 1.3505 0.02374 0.01840 0.0004 0.0140 1.0000
13.750 1.3656 0.02444 0.01918 0.0018 0.0136 1.0000
14.000 1.3788 0.02527 0.02009 0.0034 0.0131 1.0000
14.250 1.3910 0.02618 0.02107 0.0050 0.0127 1.0000
14.500 1.4021 0.02718 0.02214 0.0066 0.0122 1.0000
14.750 1.4105 0.02839 0.02342 0.0084 0.0118 1.0000
15.000 1.4122 0.03013 0.02525 0.0107 0.0112 1.0000
15.250 1.4164 0.03172 0.02695 0.0126 0.0109 1.0000
15.500 1.4245 0.03307 0.02840 0.0139 0.0107 1.0000
15.750 1.4306 0.03462 0.03006 0.0153 0.0104 1.0000
16.000 1.4347 0.03638 0.03192 0.0166 0.0101 1.0000
16.250 1.4379 0.03830 0.03394 0.0177 0.0099 1.0000
16.500 1.4398 0.04044 0.03617 0.0186 0.0096 1.0000
16.750 1.4389 0.04293 0.03877 0.0193 0.0094 1.0000
17.000 1.4350 0.04590 0.04185 0.0197 0.0092 1.0000
17.250 1.4277 0.04946 0.04553 0.0196 0.0090 1.0000
17.500 1.4147 0.05398 0.05019 0.0189 0.0089 1.0000
17.750 1.3984 0.05933 0.05569 0.0173 0.0088 1.0000
18.000 1.3758 0.06606 0.06259 0.0147 0.0086 1.0000
18.250 1.3517 0.07347 0.07018 0.0112 0.0086 1.0000
18.500 1.3269 0.08156 0.07844 0.0070 0.0086 1.0000
18.750 1.3003 0.09040 0.08745 0.0023 0.0086 1.0000
19.000 1.2711 0.10003 0.09725 -0.0029 0.0087 1.0000
19.250 1.2361 0.11101 0.10841 -0.0088 0.0088 1.0000
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Polar data table (+)
Polar graphs
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