LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Reynolds number: 50,000 Max Cl/Cd: 30.42 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5b-il-50000.txt Download as CSV file: xf-c5b-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4797 0.10023 0.09290 -0.0104 1.0000 0.3880
-8.000 -0.4594 0.09575 0.08841 -0.0097 1.0000 0.3956
-7.500 -0.6778 0.06991 0.06264 -0.0305 1.0000 0.1676
-7.250 -0.6889 0.06385 0.05625 -0.0296 1.0000 0.1518
-7.000 -0.7010 0.05823 0.04992 -0.0278 1.0000 0.1393
-6.750 -0.6909 0.05431 0.04589 -0.0264 1.0000 0.1358
-6.500 -0.6844 0.05024 0.04140 -0.0246 1.0000 0.1315
-6.250 -0.6761 0.04630 0.03674 -0.0227 1.0000 0.1276
-6.000 -0.6612 0.04341 0.03351 -0.0212 1.0000 0.1286
-5.750 -0.6442 0.04088 0.03069 -0.0199 1.0000 0.1309
-5.500 -0.6252 0.03839 0.02782 -0.0186 1.0000 0.1331
-5.250 -0.6038 0.03601 0.02502 -0.0173 1.0000 0.1351
-5.000 -0.5813 0.03406 0.02253 -0.0161 1.0000 0.1397
-4.750 -0.5580 0.03214 0.02064 -0.0154 1.0000 0.1480
-4.500 -0.5325 0.03041 0.01865 -0.0144 1.0000 0.1566
-4.250 -0.5069 0.02888 0.01713 -0.0136 1.0000 0.1718
-4.000 -0.4812 0.02733 0.01576 -0.0127 1.0000 0.1948
-3.750 -0.4567 0.02556 0.01433 -0.0116 1.0000 0.2442
-3.500 -0.4483 0.02177 0.01323 -0.0072 1.0000 0.5461
-3.250 -0.4494 0.02234 0.01451 0.0042 1.0000 0.7728
-3.000 -0.3278 0.02653 0.01797 -0.0003 1.0000 0.9366
-2.750 -0.1212 0.02672 0.01696 -0.0340 1.0000 1.0000
-2.500 -0.1200 0.02614 0.01628 -0.0313 1.0000 1.0000
-2.250 -0.1188 0.02563 0.01568 -0.0284 1.0000 1.0000
-2.000 -0.1177 0.02517 0.01513 -0.0253 1.0000 1.0000
-1.750 -0.1169 0.02475 0.01464 -0.0221 1.0000 1.0000
-1.500 -0.1162 0.02436 0.01418 -0.0188 1.0000 1.0000
-1.250 -0.1157 0.02400 0.01375 -0.0154 1.0000 1.0000
-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 -0.0979 0.02291 0.01228 0.0000 1.0000 1.0000
0.250 -0.0855 0.02297 0.01224 0.0017 1.0000 1.0000
0.500 -0.0705 0.02312 0.01229 0.0029 1.0000 1.0000
0.750 -0.0539 0.02334 0.01244 0.0038 1.0000 1.0000
1.000 -0.0363 0.02363 0.01266 0.0045 1.0000 1.0000
1.250 -0.0180 0.02398 0.01295 0.0051 1.0000 1.0000
1.500 0.0007 0.02438 0.01331 0.0056 1.0000 1.0000
1.750 0.0196 0.02484 0.01374 0.0059 1.0000 1.0000
2.000 0.0385 0.02534 0.01423 0.0063 1.0000 1.0000
2.250 0.0574 0.02590 0.01479 0.0065 1.0000 1.0000
2.500 0.0762 0.02652 0.01541 0.0067 1.0000 1.0000
2.750 0.0949 0.02719 0.01611 0.0068 1.0000 1.0000
3.000 0.1132 0.02792 0.01687 0.0069 1.0000 1.0000
3.250 0.1313 0.02871 0.01772 0.0070 1.0000 1.0000
3.500 0.1490 0.02958 0.01865 0.0069 1.0000 1.0000
3.750 0.1663 0.03052 0.01966 0.0068 1.0000 1.0000
4.000 0.1975 0.03190 0.02117 0.0039 0.9946 1.0000
4.250 0.2693 0.03391 0.02343 -0.0062 0.9649 1.0000
4.500 0.3379 0.03511 0.02492 -0.0146 0.9290 1.0000
4.750 0.4222 0.03490 0.02509 -0.0231 0.8811 1.0000
5.000 0.4982 0.03367 0.02430 -0.0288 0.8419 1.0000
5.250 0.5597 0.03176 0.02284 -0.0311 0.8028 1.0000
5.500 0.6454 0.02587 0.01760 -0.0309 0.7346 1.0000
5.750 0.7008 0.02304 0.01330 -0.0253 0.4262 1.0000
6.000 0.7109 0.02565 0.01461 -0.0218 0.3076 1.0000
6.250 0.7504 0.02810 0.01647 -0.0235 0.2478 1.0000
6.500 0.7901 0.03012 0.01827 -0.0252 0.2178 1.0000
6.750 0.8254 0.03210 0.02031 -0.0262 0.2007 1.0000
7.000 0.8594 0.03437 0.02254 -0.0272 0.1893 1.0000
7.250 0.8833 0.03628 0.02476 -0.0263 0.1794 1.0000
7.500 0.9088 0.03884 0.02752 -0.0258 0.1730 1.0000
7.750 0.9270 0.04121 0.03036 -0.0240 0.1676 1.0000
8.000 0.9516 0.04398 0.03307 -0.0238 0.1605 1.0000
8.250 0.9619 0.04677 0.03643 -0.0210 0.1581 1.0000
8.500 0.9691 0.04974 0.03994 -0.0180 0.1554 1.0000
8.750 0.9750 0.05285 0.04348 -0.0152 0.1525 1.0000
9.000 0.9777 0.05643 0.04749 -0.0123 0.1516 1.0000
9.250 0.9738 0.06043 0.05192 -0.0091 0.1522 1.0000
9.500 0.9649 0.06465 0.05651 -0.0059 0.1533 1.0000
9.750 0.9520 0.06909 0.06126 -0.0029 0.1548 1.0000
10.000 0.9374 0.07371 0.06610 -0.0004 0.1566 1.0000
10.250 0.9257 0.07849 0.07102 0.0015 0.1584 1.0000
10.500 0.8546 0.08596 0.07869 0.0031 0.1712 1.0000
10.750 0.8547 0.09176 0.08456 0.0026 0.1761 1.0000
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Polar data table (+)
Polar graphs
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