LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Reynolds number: 50,000 Max Cl/Cd: 35.05 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-l188tip-il-50000.txt Download as CSV file: xf-l188tip-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED L-188 TIP 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 -0.4013 0.10279 0.09587 -0.0218 1.0000 0.3196
-8.000 -0.4336 0.10296 0.09620 -0.0186 1.0000 0.3309
-7.750 -0.4333 0.10051 0.09381 -0.0158 1.0000 0.3472
-7.500 -0.4377 0.09843 0.09181 -0.0127 1.0000 0.3638
-7.250 -0.4447 0.09653 0.08999 -0.0092 1.0000 0.3805
-7.000 -0.4554 0.09489 0.08844 -0.0054 1.0000 0.3972
-6.750 -0.4166 0.08983 0.08330 -0.0046 1.0000 0.4196
-6.500 -0.4224 0.08821 0.08176 -0.0007 1.0000 0.4426
-6.250 -0.4548 0.08820 0.08191 0.0055 1.0000 0.4623
-6.000 -0.4411 0.08551 0.07924 0.0088 1.0000 0.4946
-5.500 -0.5470 0.05549 0.04760 -0.0341 1.0000 0.1667
-5.250 -0.5308 0.05151 0.04357 -0.0336 1.0000 0.1615
-5.000 -0.5105 0.04670 0.03761 -0.0350 1.0000 0.1510
-4.750 -0.4906 0.04353 0.03427 -0.0349 1.0000 0.1530
-4.500 -0.4685 0.04092 0.03135 -0.0348 1.0000 0.1550
-4.250 -0.4446 0.03852 0.02855 -0.0347 1.0000 0.1568
-4.000 -0.4204 0.03665 0.02628 -0.0345 1.0000 0.1628
-3.750 -0.3946 0.03482 0.02389 -0.0344 1.0000 0.1679
-3.500 -0.3711 0.03331 0.02237 -0.0340 1.0000 0.1772
-3.250 -0.3460 0.03194 0.02077 -0.0336 1.0000 0.1877
-3.000 -0.3213 0.03082 0.01953 -0.0332 1.0000 0.2022
-2.750 -0.2966 0.02976 0.01850 -0.0326 1.0000 0.2209
-2.500 -0.2717 0.02886 0.01759 -0.0321 1.0000 0.2488
-2.250 -0.2451 0.02774 0.01679 -0.0320 1.0000 0.2959
-2.000 -0.2207 0.02504 0.01659 -0.0300 1.0000 0.6246
-1.750 -0.2034 0.02450 0.01668 -0.0229 1.0000 1.0000
-1.500 -0.1844 0.02463 0.01634 -0.0228 1.0000 1.0000
-1.250 -0.1642 0.02487 0.01621 -0.0227 1.0000 1.0000
-1.000 -0.1434 0.02519 0.01619 -0.0228 1.0000 1.0000
-0.750 -0.1223 0.02557 0.01628 -0.0228 1.0000 1.0000
-0.500 -0.1010 0.02600 0.01646 -0.0229 1.0000 1.0000
-0.250 -0.0798 0.02647 0.01670 -0.0230 1.0000 1.0000
0.000 -0.0587 0.02699 0.01701 -0.0230 1.0000 1.0000
0.250 -0.0376 0.02755 0.01739 -0.0231 1.0000 1.0000
0.500 -0.0167 0.02815 0.01783 -0.0231 1.0000 1.0000
0.750 0.0041 0.02878 0.01831 -0.0232 1.0000 1.0000
1.000 0.0247 0.02945 0.01886 -0.0232 1.0000 1.0000
1.250 0.0451 0.03017 0.01946 -0.0233 1.0000 1.0000
1.500 0.0652 0.03092 0.02012 -0.0234 1.0000 1.0000
1.750 0.0852 0.03171 0.02082 -0.0234 1.0000 1.0000
2.000 0.1049 0.03254 0.02159 -0.0235 1.0000 1.0000
2.250 0.1244 0.03341 0.02241 -0.0236 1.0000 1.0000
2.500 0.1436 0.03433 0.02329 -0.0237 1.0000 1.0000
2.750 0.1625 0.03530 0.02423 -0.0239 1.0000 1.0000
3.000 0.1810 0.03632 0.02523 -0.0240 1.0000 1.0000
3.250 0.1993 0.03739 0.02630 -0.0242 1.0000 1.0000
3.500 0.2487 0.03951 0.02844 -0.0303 0.9857 1.0000
3.750 0.3044 0.04159 0.03058 -0.0373 0.9608 1.0000
4.000 0.3510 0.04326 0.03233 -0.0421 0.9378 1.0000
4.250 0.3926 0.04463 0.03378 -0.0458 0.9152 1.0000
4.500 0.4391 0.04595 0.03521 -0.0498 0.8918 1.0000
4.750 0.4760 0.04682 0.03620 -0.0519 0.8675 1.0000
5.000 0.5205 0.04754 0.03709 -0.0547 0.8425 1.0000
5.250 0.5717 0.04778 0.03751 -0.0578 0.8166 1.0000
5.500 0.6090 0.04774 0.03763 -0.0585 0.7894 1.0000
5.750 0.6545 0.04712 0.03725 -0.0595 0.7617 1.0000
6.000 0.7088 0.04553 0.03594 -0.0606 0.7337 1.0000
6.250 0.7834 0.04176 0.03257 -0.0619 0.7067 1.0000
6.500 0.8416 0.03755 0.02874 -0.0603 0.6763 1.0000
6.750 0.8976 0.03274 0.02429 -0.0574 0.6349 1.0000
7.000 0.9515 0.02782 0.01938 -0.0533 0.5450 1.0000
7.250 0.9702 0.02768 0.01810 -0.0481 0.4142 1.0000
7.500 0.9851 0.02967 0.01917 -0.0453 0.3390 1.0000
7.750 1.0117 0.03175 0.02077 -0.0448 0.2881 1.0000
8.000 1.0443 0.03382 0.02254 -0.0453 0.2526 1.0000
8.250 1.0757 0.03597 0.02459 -0.0457 0.2272 1.0000
8.500 1.1043 0.03812 0.02672 -0.0457 0.2081 1.0000
8.750 1.1307 0.04047 0.02918 -0.0455 0.1938 1.0000
9.000 1.1537 0.04293 0.03178 -0.0449 0.1821 1.0000
9.250 1.1825 0.04575 0.03450 -0.0452 0.1719 1.0000
9.500 1.1897 0.04826 0.03761 -0.0423 0.1655 1.0000
9.750 1.2126 0.05112 0.04052 -0.0418 0.1584 1.0000
10.000 1.2177 0.05445 0.04430 -0.0391 0.1547 1.0000
10.250 1.2156 0.05766 0.04802 -0.0356 0.1514 1.0000
10.500 1.2150 0.06094 0.05166 -0.0326 0.1482 1.0000
10.750 1.2142 0.06453 0.05555 -0.0298 0.1462 1.0000
11.000 1.2367 0.06881 0.05974 -0.0301 0.1423 1.0000
11.250 1.2204 0.07270 0.06403 -0.0262 0.1419 1.0000
11.500 1.2002 0.07678 0.06844 -0.0224 0.1418 1.0000
11.750 1.1781 0.08092 0.07280 -0.0189 0.1420 1.0000
12.000 1.1563 0.08548 0.07755 -0.0162 0.1423 1.0000
12.250 0.6011 0.14054 0.13311 -0.0395 0.3593 1.0000
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Polar data table (+)
Polar graphs
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