LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.72 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5c-il-1000000.txt Download as CSV file: xf-c5c-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL576 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7646 0.05962 0.05756 -0.0678 1.0000 0.0154
-12.250 -0.8038 0.05319 0.05099 -0.0697 1.0000 0.0153
-12.000 -0.8409 0.04892 0.04660 -0.0681 1.0000 0.0152
-11.750 -0.8785 0.04414 0.04160 -0.0667 0.9990 0.0151
-11.500 -0.9114 0.03713 0.03409 -0.0665 0.9950 0.0149
-11.250 -0.9178 0.03223 0.02874 -0.0655 0.9918 0.0148
-11.000 -0.9088 0.02918 0.02538 -0.0650 0.9892 0.0149
-10.750 -0.8921 0.02683 0.02276 -0.0651 0.9876 0.0150
-10.500 -0.8712 0.02495 0.02065 -0.0654 0.9864 0.0152
-10.250 -0.8479 0.02333 0.01884 -0.0659 0.9856 0.0153
-10.000 -0.8226 0.02196 0.01730 -0.0666 0.9849 0.0155
-9.750 -0.8036 0.02084 0.01604 -0.0657 0.9823 0.0156
-9.500 -0.7807 0.01980 0.01487 -0.0654 0.9802 0.0157
-9.250 -0.7548 0.01881 0.01377 -0.0657 0.9787 0.0158
-9.000 -0.7277 0.01791 0.01276 -0.0663 0.9776 0.0160
-8.750 -0.6995 0.01708 0.01184 -0.0670 0.9768 0.0161
-8.500 -0.6701 0.01633 0.01101 -0.0679 0.9761 0.0162
-8.250 -0.6399 0.01563 0.01024 -0.0689 0.9755 0.0163
-8.000 -0.6101 0.01496 0.00950 -0.0698 0.9748 0.0164
-7.750 -0.5833 0.01385 0.00829 -0.0703 0.9740 0.0168
-7.500 -0.5635 0.01325 0.00764 -0.0689 0.9708 0.0171
-7.250 -0.5388 0.01278 0.00715 -0.0685 0.9682 0.0175
-7.000 -0.5108 0.01241 0.00677 -0.0689 0.9665 0.0181
-6.750 -0.4821 0.01207 0.00640 -0.0693 0.9651 0.0188
-6.500 -0.4534 0.01171 0.00601 -0.0697 0.9639 0.0196
-6.250 -0.4241 0.01142 0.00569 -0.0702 0.9628 0.0204
-6.000 -0.3964 0.01089 0.00514 -0.0704 0.9615 0.0227
-5.750 -0.3717 0.01070 0.00495 -0.0699 0.9589 0.0246
-5.500 -0.3473 0.01049 0.00472 -0.0692 0.9557 0.0260
-5.250 -0.3212 0.01014 0.00437 -0.0690 0.9531 0.0284
-5.000 -0.2933 0.00991 0.00413 -0.0691 0.9511 0.0303
-4.750 -0.2646 0.00971 0.00392 -0.0693 0.9494 0.0316
-4.500 -0.2366 0.00942 0.00362 -0.0694 0.9478 0.0345
-4.250 -0.2106 0.00923 0.00344 -0.0691 0.9452 0.0374
-4.000 -0.1855 0.00906 0.00326 -0.0685 0.9418 0.0405
-3.750 -0.1595 0.00880 0.00305 -0.0682 0.9391 0.0496
-3.500 -0.1338 0.00837 0.00283 -0.0679 0.9367 0.0909
-3.250 -0.1063 0.00809 0.00265 -0.0679 0.9345 0.1237
-3.000 -0.0786 0.00784 0.00249 -0.0680 0.9323 0.1474
-2.750 -0.0536 0.00759 0.00238 -0.0675 0.9289 0.1855
-2.500 -0.0289 0.00722 0.00225 -0.0670 0.9255 0.2479
-2.250 -0.0042 0.00670 0.00208 -0.0666 0.9222 0.3460
-2.000 0.0205 0.00609 0.00187 -0.0661 0.9184 0.4640
-1.750 0.0445 0.00567 0.00176 -0.0654 0.9137 0.5580
-1.500 0.0696 0.00538 0.00170 -0.0648 0.9094 0.6276
-1.250 0.0961 0.00518 0.00166 -0.0645 0.9060 0.6828
-1.000 0.1241 0.00504 0.00160 -0.0644 0.9026 0.7161
-0.750 0.1505 0.00496 0.00156 -0.0639 0.8961 0.7365
-0.500 0.1787 0.00484 0.00143 -0.0637 0.8878 0.7500
-0.250 0.2051 0.00477 0.00138 -0.0632 0.8776 0.7620
0.000 0.2324 0.00471 0.00133 -0.0630 0.8675 0.7754
0.250 0.2597 0.00468 0.00128 -0.0627 0.8552 0.7881
0.500 0.2870 0.00467 0.00126 -0.0624 0.8437 0.8007
0.750 0.3140 0.00464 0.00127 -0.0621 0.8325 0.8136
1.000 0.3407 0.00463 0.00127 -0.0617 0.8185 0.8273
1.250 0.3663 0.00466 0.00126 -0.0611 0.7961 0.8412
1.500 0.3898 0.00476 0.00127 -0.0599 0.7569 0.8572
1.750 0.4111 0.00497 0.00134 -0.0583 0.7067 0.8737
2.000 0.4314 0.00526 0.00145 -0.0566 0.6540 0.8889
2.250 0.4518 0.00557 0.00158 -0.0549 0.5985 0.9044
2.500 0.4706 0.00597 0.00175 -0.0529 0.5314 0.9221
2.750 0.4883 0.00647 0.00195 -0.0508 0.4486 0.9399
3.000 0.5074 0.00702 0.00218 -0.0490 0.3664 0.9547
3.250 0.5294 0.00759 0.00241 -0.0480 0.2851 0.9667
3.500 0.5548 0.00815 0.00266 -0.0478 0.2105 0.9763
3.750 0.5830 0.00863 0.00290 -0.0481 0.1603 0.9845
4.000 0.6157 0.00908 0.00313 -0.0496 0.1166 0.9883
4.250 0.6500 0.00937 0.00334 -0.0512 0.1027 0.9918
4.500 0.6842 0.00965 0.00357 -0.0528 0.0899 0.9949
4.750 0.7194 0.00996 0.00378 -0.0547 0.0704 0.9972
5.000 0.7540 0.01031 0.00402 -0.0565 0.0586 0.9997
5.250 0.7744 0.01053 0.00422 -0.0550 0.0546 1.0000
5.500 0.7932 0.01072 0.00441 -0.0532 0.0525 1.0000
5.750 0.8124 0.01095 0.00463 -0.0515 0.0501 1.0000
6.000 0.8318 0.01124 0.00490 -0.0499 0.0474 1.0000
6.250 0.8517 0.01156 0.00525 -0.0483 0.0456 1.0000
6.500 0.8741 0.01177 0.00548 -0.0473 0.0450 1.0000
6.750 0.8967 0.01201 0.00574 -0.0463 0.0441 1.0000
7.000 0.9193 0.01228 0.00603 -0.0453 0.0429 1.0000
7.250 0.9419 0.01257 0.00634 -0.0444 0.0416 1.0000
7.500 0.9643 0.01289 0.00667 -0.0435 0.0402 1.0000
7.750 0.9853 0.01334 0.00713 -0.0423 0.0385 1.0000
8.000 1.0048 0.01390 0.00774 -0.0409 0.0368 1.0000
8.250 1.0293 0.01406 0.00792 -0.0403 0.0360 1.0000
8.500 1.0531 0.01427 0.00815 -0.0397 0.0346 1.0000
8.750 1.0766 0.01450 0.00838 -0.0391 0.0331 1.0000
9.000 1.0991 0.01480 0.00867 -0.0383 0.0314 1.0000
9.250 1.1189 0.01531 0.00921 -0.0369 0.0296 1.0000
9.500 1.1421 0.01550 0.00941 -0.0362 0.0285 1.0000
9.750 1.1642 0.01573 0.00966 -0.0353 0.0271 1.0000
10.000 1.1852 0.01604 0.00996 -0.0342 0.0258 1.0000
10.250 1.2025 0.01665 0.01058 -0.0325 0.0242 1.0000
10.500 1.2233 0.01697 0.01094 -0.0314 0.0235 1.0000
10.750 1.2439 0.01730 0.01131 -0.0303 0.0225 1.0000
11.000 1.2639 0.01768 0.01170 -0.0292 0.0215 1.0000
11.250 1.2821 0.01819 0.01222 -0.0278 0.0205 1.0000
11.500 1.2978 0.01889 0.01296 -0.0260 0.0196 1.0000
11.750 1.3164 0.01936 0.01349 -0.0246 0.0192 1.0000
12.000 1.3344 0.01986 0.01404 -0.0233 0.0186 1.0000
12.250 1.3522 0.02037 0.01461 -0.0219 0.0179 1.0000
12.500 1.3691 0.02093 0.01520 -0.0205 0.0172 1.0000
12.750 1.3837 0.02168 0.01597 -0.0188 0.0164 1.0000
13.000 1.3970 0.02250 0.01686 -0.0169 0.0157 1.0000
13.250 1.4132 0.02310 0.01753 -0.0155 0.0153 1.0000
13.500 1.4288 0.02375 0.01825 -0.0140 0.0147 1.0000
13.750 1.4431 0.02448 0.01904 -0.0125 0.0141 1.0000
14.000 1.4558 0.02534 0.01994 -0.0108 0.0134 1.0000
14.250 1.4621 0.02668 0.02134 -0.0084 0.0126 1.0000
14.500 1.4765 0.02741 0.02216 -0.0070 0.0122 1.0000
14.750 1.4888 0.02831 0.02314 -0.0055 0.0116 1.0000
15.000 1.4996 0.02933 0.02423 -0.0039 0.0110 1.0000
15.250 1.5066 0.03068 0.02563 -0.0020 0.0104 1.0000
15.500 1.5096 0.03236 0.02741 0.0001 0.0098 1.0000
15.750 1.5184 0.03362 0.02878 0.0015 0.0093 1.0000
16.000 1.5249 0.03510 0.03034 0.0030 0.0089 1.0000
16.250 1.5295 0.03676 0.03209 0.0045 0.0085 1.0000
16.500 1.5317 0.03871 0.03412 0.0059 0.0082 1.0000
16.750 1.5292 0.04119 0.03670 0.0073 0.0078 1.0000
17.000 1.5214 0.04431 0.03995 0.0085 0.0075 1.0000
17.250 1.5203 0.04694 0.04270 0.0091 0.0074 1.0000
17.500 1.5169 0.04997 0.04586 0.0094 0.0073 1.0000
17.750 1.5106 0.05352 0.04954 0.0093 0.0072 1.0000
18.000 1.5028 0.05752 0.05368 0.0087 0.0071 1.0000
18.250 1.4918 0.06222 0.05853 0.0075 0.0070 1.0000
18.500 1.4772 0.06774 0.06419 0.0056 0.0069 1.0000
18.750 1.4584 0.07430 0.07091 0.0028 0.0068 1.0000
19.000 1.4325 0.08255 0.07935 -0.0013 0.0069 1.0000
19.250 1.3970 0.09303 0.09003 -0.0069 0.0069 1.0000
|
Polar data table (+)
Polar graphs
<< Back to LOCKHEED C-5A BL576 AIRFOIL (c5c-il)