FX 71-L-150/20 AIRFOIL (fx711520-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 71-L-150/20 AIRFOIL (fx711520-il) Reynolds number: 100,000 Max Cl/Cd: 36.7 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx711520-il-100000.txt Download as CSV file: xf-fx711520-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/20 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7219 0.11267 0.10742 -0.0054 1.0000 0.0699
-13.000 -0.8443 0.08761 0.08196 -0.0232 1.0000 0.0630
-12.750 -0.8437 0.08321 0.07753 -0.0244 1.0000 0.0623
-12.500 -0.8648 0.07732 0.07151 -0.0270 1.0000 0.0614
-12.250 -0.8926 0.07148 0.06548 -0.0291 1.0000 0.0605
-12.000 -0.9242 0.06609 0.05983 -0.0303 1.0000 0.0595
-11.750 -0.9673 0.06103 0.05435 -0.0299 1.0000 0.0582
-11.500 -1.0070 0.05785 0.05065 -0.0266 1.0000 0.0571
-11.250 -1.0010 0.05464 0.04728 -0.0259 1.0000 0.0567
-11.000 -0.9968 0.05147 0.04389 -0.0249 1.0000 0.0564
-10.750 -0.9904 0.04853 0.04069 -0.0239 1.0000 0.0561
-10.500 -0.9801 0.04566 0.03754 -0.0230 1.0000 0.0559
-10.250 -0.9661 0.04298 0.03458 -0.0223 1.0000 0.0559
-10.000 -0.9486 0.04051 0.03185 -0.0217 1.0000 0.0561
-9.750 -0.9279 0.03821 0.02928 -0.0214 1.0000 0.0566
-9.500 -0.9041 0.03614 0.02697 -0.0212 1.0000 0.0573
-9.250 -0.8719 0.03417 0.02513 -0.0220 1.0000 0.0587
-9.000 -0.8438 0.03260 0.02357 -0.0224 1.0000 0.0610
-8.750 -0.8166 0.03109 0.02201 -0.0225 1.0000 0.0638
-8.500 -0.7907 0.02981 0.02086 -0.0228 1.0000 0.0675
-8.250 -0.7664 0.02848 0.01964 -0.0227 1.0000 0.0721
-8.000 -0.7465 0.02717 0.01844 -0.0222 1.0000 0.0787
-7.750 -0.7346 0.02584 0.01729 -0.0210 1.0000 0.0876
-7.500 -0.7377 0.02487 0.01648 -0.0177 1.0000 0.0970
-7.250 -0.7215 0.02297 0.01489 -0.0184 0.9816 0.1290
-7.000 -0.6997 0.02053 0.01312 -0.0207 0.9666 0.2038
-6.750 -0.6808 0.01856 0.01193 -0.0219 0.9538 0.3202
-6.500 -0.6570 0.01796 0.01185 -0.0220 0.9434 0.4203
-6.250 -0.6241 0.01829 0.01232 -0.0226 0.9355 0.4848
-6.000 -0.5971 0.01900 0.01297 -0.0218 0.9257 0.5252
-5.750 -0.5616 0.02042 0.01439 -0.0213 0.9186 0.5524
-5.500 -0.5299 0.02194 0.01588 -0.0200 0.9111 0.5727
-5.250 -0.4980 0.02338 0.01724 -0.0186 0.9038 0.5900
-5.000 -0.4691 0.02430 0.01803 -0.0176 0.8972 0.6064
-4.750 -0.4330 0.02580 0.01953 -0.0163 0.8911 0.6144
-4.500 -0.4084 0.02621 0.01981 -0.0153 0.8846 0.6284
-4.250 -0.3730 0.02738 0.02092 -0.0140 0.8795 0.6362
-4.000 -0.3521 0.02753 0.02099 -0.0130 0.8726 0.6493
-3.750 -0.3198 0.02836 0.02176 -0.0118 0.8666 0.6572
-3.500 -0.3013 0.02821 0.02150 -0.0107 0.8609 0.6697
-3.250 -0.2706 0.02871 0.02197 -0.0100 0.8559 0.6763
-3.000 -0.2566 0.02833 0.02150 -0.0092 0.8490 0.6892
-2.750 -0.2261 0.02870 0.02183 -0.0081 0.8433 0.6946
-2.500 -0.2084 0.02859 0.02165 -0.0072 0.8368 0.7053
-2.250 -0.1857 0.02851 0.02154 -0.0065 0.8303 0.7123
-2.000 -0.1602 0.02860 0.02158 -0.0056 0.8250 0.7192
-1.750 -0.1464 0.02834 0.02126 -0.0048 0.8188 0.7297
-1.500 -0.1202 0.02845 0.02137 -0.0041 0.8125 0.7352
-1.250 -0.0996 0.02838 0.02126 -0.0033 0.8072 0.7434
-1.000 -0.0813 0.02825 0.02109 -0.0027 0.8021 0.7508
-0.750 -0.0591 0.02828 0.02115 -0.0023 0.7958 0.7560
-0.500 -0.0392 0.02821 0.02105 -0.0017 0.7901 0.7634
-0.250 -0.0197 0.02818 0.02100 -0.0008 0.7846 0.7706
0.000 0.0000 0.02829 0.02114 0.0000 0.7769 0.7769
0.250 0.0197 0.02818 0.02100 0.0008 0.7706 0.7846
0.500 0.0392 0.02821 0.02105 0.0017 0.7634 0.7901
0.750 0.0591 0.02829 0.02115 0.0023 0.7560 0.7958
1.000 0.0814 0.02825 0.02109 0.0027 0.7508 0.8021
1.250 0.0996 0.02839 0.02127 0.0033 0.7435 0.8073
1.500 0.1201 0.02845 0.02138 0.0041 0.7352 0.8125
1.750 0.1464 0.02834 0.02126 0.0048 0.7298 0.8188
2.000 0.1602 0.02860 0.02158 0.0056 0.7192 0.8250
2.250 0.1857 0.02851 0.02154 0.0065 0.7123 0.8303
2.500 0.2083 0.02859 0.02165 0.0072 0.7052 0.8367
2.750 0.2263 0.02869 0.02181 0.0081 0.6946 0.8432
3.000 0.2566 0.02833 0.02151 0.0092 0.6892 0.8490
3.250 0.2705 0.02872 0.02198 0.0100 0.6763 0.8559
3.500 0.3012 0.02823 0.02152 0.0107 0.6697 0.8610
3.750 0.3198 0.02835 0.02176 0.0118 0.6572 0.8667
4.000 0.3519 0.02756 0.02102 0.0130 0.6494 0.8727
4.250 0.3731 0.02738 0.02092 0.0141 0.6362 0.8796
4.500 0.4084 0.02621 0.01981 0.0153 0.6284 0.8846
4.750 0.4330 0.02581 0.01953 0.0163 0.6144 0.8911
5.000 0.4691 0.02430 0.01804 0.0176 0.6064 0.8972
5.250 0.4979 0.02340 0.01726 0.0186 0.5901 0.9037
5.500 0.5299 0.02195 0.01588 0.0200 0.5728 0.9111
5.750 0.5617 0.02042 0.01438 0.0213 0.5524 0.9186
6.000 0.5971 0.01900 0.01297 0.0218 0.5250 0.9258
6.250 0.6241 0.01828 0.01232 0.0226 0.4842 0.9355
6.500 0.6570 0.01796 0.01184 0.0220 0.4199 0.9434
6.750 0.6808 0.01855 0.01193 0.0219 0.3201 0.9538
7.000 0.6996 0.02054 0.01312 0.0207 0.2032 0.9666
7.250 0.7215 0.02297 0.01489 0.0184 0.1289 0.9816
7.500 0.7372 0.02488 0.01648 0.0177 0.0965 1.0000
7.750 0.7342 0.02587 0.01731 0.0210 0.0870 1.0000
8.000 0.7467 0.02716 0.01844 0.0222 0.0786 1.0000
8.250 0.7667 0.02848 0.01964 0.0227 0.0722 1.0000
8.500 0.7912 0.02983 0.02088 0.0227 0.0674 1.0000
8.750 0.8172 0.03112 0.02203 0.0225 0.0639 1.0000
9.000 0.8438 0.03261 0.02358 0.0224 0.0608 1.0000
9.250 0.8722 0.03418 0.02514 0.0220 0.0587 1.0000
9.500 0.9045 0.03616 0.02698 0.0212 0.0573 1.0000
9.750 0.9282 0.03822 0.02928 0.0214 0.0566 1.0000
10.000 0.9487 0.04053 0.03188 0.0217 0.0561 1.0000
10.250 0.9665 0.04299 0.03459 0.0222 0.0559 1.0000
10.500 0.9804 0.04569 0.03756 0.0230 0.0559 1.0000
10.750 0.9910 0.04852 0.04067 0.0238 0.0561 1.0000
11.000 0.9975 0.05149 0.04390 0.0248 0.0564 1.0000
11.250 1.0016 0.05463 0.04728 0.0258 0.0567 1.0000
11.500 1.0077 0.05786 0.05066 0.0265 0.0571 1.0000
11.750 0.9660 0.06113 0.05446 0.0299 0.0583 1.0000
12.000 0.9237 0.06620 0.05995 0.0302 0.0596 1.0000
12.250 0.8918 0.07165 0.06565 0.0290 0.0605 1.0000
12.500 0.8657 0.07734 0.07154 0.0269 0.0615 1.0000
12.750 0.8460 0.08311 0.07743 0.0244 0.0623 1.0000
13.000 0.8478 0.08741 0.08174 0.0233 0.0631 1.0000
13.250 0.5110 0.14493 0.14032 -0.0107 0.1380 1.0000
13.500 0.5057 0.14908 0.14444 -0.0131 0.1365 1.0000
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