LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Reynolds number: 50,000 Max Cl/Cd: 27.06 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5a-il-50000-n5.txt Download as CSV file: xf-c5a-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6366 0.09895 0.09099 -0.0473 1.0000 0.0505
-11.750 -0.6691 0.08996 0.08196 -0.0523 1.0000 0.0495
-11.500 -0.7049 0.08257 0.07448 -0.0554 1.0000 0.0487
-11.250 -0.7389 0.07694 0.06869 -0.0561 1.0000 0.0482
-11.000 -0.7697 0.07265 0.06422 -0.0548 1.0000 0.0477
-10.750 -0.7977 0.06934 0.06072 -0.0518 1.0000 0.0474
-10.500 -0.8223 0.06662 0.05781 -0.0475 1.0000 0.0473
-10.250 -0.8382 0.06372 0.05468 -0.0439 1.0000 0.0472
-10.000 -0.8477 0.06091 0.05164 -0.0405 1.0000 0.0472
-9.750 -0.8526 0.05818 0.04867 -0.0374 1.0000 0.0474
-9.500 -0.8525 0.05566 0.04595 -0.0346 1.0000 0.0479
-9.250 -0.8494 0.05333 0.04341 -0.0321 1.0000 0.0488
-9.000 -0.8446 0.05107 0.04092 -0.0296 1.0000 0.0498
-8.750 -0.8379 0.04881 0.03839 -0.0271 1.0000 0.0510
-8.500 -0.8284 0.04655 0.03583 -0.0249 1.0000 0.0522
-8.250 -0.8153 0.04434 0.03329 -0.0229 1.0000 0.0532
-8.000 -0.7984 0.04223 0.03086 -0.0212 1.0000 0.0542
-7.750 -0.7782 0.04033 0.02863 -0.0198 1.0000 0.0553
-7.500 -0.7557 0.03857 0.02677 -0.0189 1.0000 0.0570
-7.250 -0.7360 0.03718 0.02538 -0.0177 1.0000 0.0599
-7.000 -0.7156 0.03596 0.02405 -0.0163 1.0000 0.0635
-6.750 -0.6944 0.03483 0.02268 -0.0148 1.0000 0.0668
-6.500 -0.6782 0.03360 0.02150 -0.0129 1.0000 0.0701
-6.250 -0.6643 0.03254 0.02039 -0.0108 1.0000 0.0754
-6.000 -0.6517 0.03145 0.01925 -0.0084 1.0000 0.0817
-5.750 -0.6399 0.03035 0.01815 -0.0061 1.0000 0.0897
-5.500 -0.6284 0.02919 0.01703 -0.0038 1.0000 0.1023
-5.250 -0.6180 0.02778 0.01578 -0.0014 1.0000 0.1295
-5.000 -0.6117 0.02571 0.01439 0.0010 1.0000 0.2017
-4.750 -0.6089 0.02356 0.01361 0.0043 1.0000 0.3939
-4.500 -0.5973 0.02330 0.01409 0.0086 1.0000 0.5449
-4.250 -0.5866 0.02389 0.01492 0.0138 1.0000 0.6404
-4.000 -0.5744 0.02482 0.01588 0.0192 1.0000 0.6963
-3.750 -0.5581 0.02526 0.01618 0.0227 1.0000 0.7255
-3.500 -0.5386 0.02565 0.01642 0.0255 1.0000 0.7460
-3.250 -0.5200 0.02595 0.01656 0.0283 1.0000 0.7668
-3.000 -0.5020 0.02611 0.01656 0.0308 1.0000 0.7868
-2.750 -0.4835 0.02618 0.01649 0.0330 1.0000 0.8049
-2.500 -0.4619 0.02622 0.01637 0.0345 1.0000 0.8188
-2.250 -0.4396 0.02614 0.01615 0.0354 1.0000 0.8302
-2.000 -0.4195 0.02596 0.01585 0.0365 1.0000 0.8421
-1.750 -0.4004 0.02576 0.01553 0.0376 1.0000 0.8545
-1.500 -0.3774 0.02568 0.01532 0.0381 1.0000 0.8652
-1.250 -0.3543 0.02558 0.01513 0.0385 1.0000 0.8761
-1.000 -0.3325 0.02547 0.01493 0.0389 1.0000 0.8877
-0.750 -0.3092 0.02540 0.01478 0.0390 1.0000 0.8994
-0.500 -0.2812 0.02543 0.01474 0.0382 1.0000 0.9094
-0.250 -0.2526 0.02547 0.01472 0.0371 0.9992 0.9202
0.000 -0.2081 0.02573 0.01490 0.0328 0.9933 0.9287
0.250 -0.1630 0.02599 0.01511 0.0283 0.9871 0.9365
0.500 -0.1193 0.02622 0.01531 0.0241 0.9808 0.9447
0.750 -0.0712 0.02653 0.01560 0.0190 0.9751 0.9519
1.000 -0.0281 0.02672 0.01581 0.0148 0.9678 0.9596
1.250 0.0215 0.02701 0.01613 0.0093 0.9618 0.9659
1.500 0.0659 0.02721 0.01639 0.0049 0.9539 0.9733
1.750 0.1140 0.02744 0.01670 -0.0003 0.9466 0.9793
2.000 0.1615 0.02762 0.01699 -0.0053 0.9380 0.9861
2.250 0.2078 0.02771 0.01721 -0.0100 0.9267 0.9927
2.500 0.2561 0.02776 0.01741 -0.0149 0.9154 0.9988
2.750 0.2917 0.02772 0.01751 -0.0173 0.9036 1.0000
3.000 0.3261 0.02759 0.01753 -0.0192 0.8906 1.0000
3.250 0.3534 0.02726 0.01734 -0.0193 0.8702 1.0000
3.500 0.4014 0.02645 0.01675 -0.0222 0.8474 1.0000
3.750 0.4422 0.02544 0.01593 -0.0233 0.8189 1.0000
4.000 0.4757 0.02461 0.01528 -0.0232 0.7910 1.0000
4.250 0.5049 0.02398 0.01484 -0.0225 0.7636 1.0000
4.500 0.5286 0.02342 0.01443 -0.0208 0.7282 1.0000
4.750 0.5677 0.02248 0.01345 -0.0205 0.6555 1.0000
5.000 0.6032 0.02229 0.01261 -0.0197 0.5053 1.0000
5.250 0.6063 0.02313 0.01262 -0.0150 0.3720 1.0000
5.500 0.6055 0.02413 0.01303 -0.0102 0.2890 1.0000
5.750 0.6090 0.02511 0.01365 -0.0064 0.2356 1.0000
6.000 0.6163 0.02614 0.01437 -0.0034 0.1981 1.0000
6.250 0.6278 0.02720 0.01525 -0.0011 0.1714 1.0000
6.500 0.6424 0.02828 0.01618 0.0007 0.1521 1.0000
6.750 0.6617 0.02935 0.01720 0.0018 0.1386 1.0000
7.000 0.6868 0.03047 0.01839 0.0021 0.1278 1.0000
7.250 0.7140 0.03165 0.01959 0.0020 0.1185 1.0000
7.500 0.7412 0.03284 0.02080 0.0019 0.1106 1.0000
7.750 0.7736 0.03430 0.02242 0.0011 0.1052 1.0000
8.000 0.8014 0.03573 0.02401 0.0010 0.0998 1.0000
8.250 0.8268 0.03722 0.02551 0.0009 0.0951 1.0000
8.500 0.8515 0.03907 0.02773 0.0013 0.0911 1.0000
8.750 0.8735 0.04092 0.02981 0.0019 0.0874 1.0000
9.000 0.8938 0.04259 0.03154 0.0024 0.0838 1.0000
9.250 0.9095 0.04491 0.03423 0.0039 0.0809 1.0000
9.500 0.9212 0.04750 0.03728 0.0058 0.0784 1.0000
9.750 0.9305 0.04987 0.03999 0.0078 0.0755 1.0000
10.000 0.9409 0.05196 0.04225 0.0094 0.0729 1.0000
10.250 0.9523 0.05431 0.04471 0.0107 0.0709 1.0000
10.500 0.9502 0.05751 0.04829 0.0136 0.0697 1.0000
10.750 0.9386 0.06090 0.05214 0.0172 0.0686 1.0000
11.000 0.9223 0.06423 0.05583 0.0208 0.0677 1.0000
11.250 0.9024 0.06776 0.05964 0.0241 0.0670 1.0000
11.500 0.8796 0.07176 0.06389 0.0264 0.0667 1.0000
11.750 0.8537 0.07647 0.06881 0.0273 0.0666 1.0000
12.000 0.8247 0.08223 0.07474 0.0264 0.0669 1.0000
12.250 0.7939 0.08938 0.08200 0.0234 0.0674 1.0000
12.500 0.7639 0.09811 0.09080 0.0182 0.0681 1.0000
|
Polar data table (+)
Polar graphs
<< Back to LOCKHEED C-5A BL0 AIRFOIL (c5a-il)