NASA SC(2)-0614 AIRFOIL (sc20614-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0614 AIRFOIL (sc20614-il) Reynolds number: 50,000 Max Cl/Cd: 22.71 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20614-il-50000-n5.txt Download as CSV file: xf-sc20614-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0614 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6037 0.10086 0.09196 -0.0472 1.0000 0.0868
-12.250 -0.6589 0.08655 0.07759 -0.0559 1.0000 0.0860
-12.000 -0.7126 0.07638 0.06726 -0.0610 1.0000 0.0853
-11.750 -0.7521 0.07004 0.06075 -0.0624 1.0000 0.0850
-11.500 -0.7830 0.06567 0.05623 -0.0616 1.0000 0.0851
-11.250 -0.8092 0.06233 0.05276 -0.0594 1.0000 0.0854
-11.000 -0.8256 0.05900 0.04923 -0.0582 1.0000 0.0860
-10.750 -0.8357 0.05591 0.04589 -0.0568 1.0000 0.0871
-10.500 -0.8414 0.05297 0.04262 -0.0554 1.0000 0.0886
-10.250 -0.8435 0.05009 0.03933 -0.0542 1.0000 0.0905
-10.000 -0.8299 0.04856 0.03787 -0.0530 1.0000 0.0927
-9.750 -0.8185 0.04687 0.03610 -0.0518 1.0000 0.0951
-9.500 -0.8070 0.04498 0.03399 -0.0506 1.0000 0.0978
-9.250 -0.7950 0.04301 0.03168 -0.0496 1.0000 0.1011
-9.000 -0.7793 0.04151 0.03014 -0.0484 1.0000 0.1042
-8.750 -0.7627 0.04029 0.02891 -0.0472 1.0000 0.1077
-8.500 -0.7458 0.03897 0.02742 -0.0461 1.0000 0.1119
-8.250 -0.7281 0.03770 0.02599 -0.0448 1.0000 0.1163
-8.000 -0.7100 0.03676 0.02514 -0.0434 1.0000 0.1206
-7.750 -0.6916 0.03582 0.02411 -0.0420 1.0000 0.1260
-7.500 -0.6730 0.03495 0.02319 -0.0403 1.0000 0.1315
-7.250 -0.6547 0.03422 0.02251 -0.0387 1.0000 0.1374
-6.750 -0.6188 0.03279 0.02111 -0.0353 1.0000 0.1518
-6.500 -0.6006 0.03213 0.02037 -0.0338 1.0000 0.1607
-6.250 -0.5833 0.03135 0.01976 -0.0326 1.0000 0.1705
-6.000 -0.5650 0.03056 0.01907 -0.0316 1.0000 0.1831
-5.750 -0.5459 0.02970 0.01836 -0.0310 1.0000 0.1994
-5.500 -0.5251 0.02871 0.01757 -0.0311 1.0000 0.2237
-5.250 -0.5021 0.02751 0.01675 -0.0320 1.0000 0.2640
-5.000 -0.4781 0.02623 0.01623 -0.0331 1.0000 0.3435
-4.750 -0.4695 0.02676 0.01762 -0.0275 1.0000 0.4348
-4.500 -0.4600 0.02801 0.01915 -0.0215 1.0000 0.5038
-4.250 -0.4365 0.02855 0.01955 -0.0208 1.0000 0.5573
-4.000 -0.4096 0.02897 0.01978 -0.0214 1.0000 0.5969
-3.750 -0.3932 0.02986 0.02059 -0.0182 1.0000 0.6185
-3.500 -0.3762 0.03064 0.02130 -0.0154 1.0000 0.6396
-3.000 -0.3417 0.03196 0.02248 -0.0103 1.0000 0.6787
-2.750 -0.3279 0.03258 0.02306 -0.0067 1.0000 0.6951
-2.500 -0.3137 0.03307 0.02352 -0.0034 1.0000 0.7113
-2.250 -0.2983 0.03341 0.02382 -0.0007 1.0000 0.7266
-2.000 -0.2716 0.03376 0.02411 -0.0002 0.9956 0.7415
-1.750 -0.2473 0.03393 0.02423 0.0010 0.9910 0.7513
-1.500 -0.2158 0.03395 0.02418 -0.0006 0.9862 0.7607
-1.250 -0.1855 0.03399 0.02416 -0.0014 0.9816 0.7677
-1.000 -0.1504 0.03399 0.02409 -0.0042 0.9765 0.7751
-0.750 -0.1213 0.03395 0.02403 -0.0048 0.9707 0.7800
-0.500 -0.0879 0.03396 0.02402 -0.0067 0.9649 0.7855
-0.250 -0.0512 0.03401 0.02405 -0.0097 0.9578 0.7913
0.000 -0.0167 0.03400 0.02404 -0.0115 0.9508 0.7952
0.250 0.0156 0.03395 0.02402 -0.0131 0.9424 0.7988
0.500 0.0522 0.03398 0.02407 -0.0156 0.9346 0.8026
0.750 0.0896 0.03402 0.02414 -0.0184 0.9257 0.8064
1.000 0.1249 0.03400 0.02419 -0.0205 0.9158 0.8098
1.250 0.1644 0.03392 0.02418 -0.0230 0.9066 0.8128
1.500 0.1961 0.03381 0.02417 -0.0241 0.8940 0.8159
1.750 0.2345 0.03359 0.02404 -0.0263 0.8796 0.8185
2.000 0.2778 0.03312 0.02368 -0.0287 0.8615 0.8212
2.250 0.3259 0.03234 0.02302 -0.0315 0.8406 0.8240
2.500 0.3722 0.03131 0.02214 -0.0332 0.8200 0.8265
2.750 0.4007 0.03056 0.02153 -0.0323 0.7940 0.8291
3.000 0.4424 0.02936 0.02047 -0.0328 0.7671 0.8313
3.250 0.4675 0.02864 0.01989 -0.0312 0.7282 0.8338
3.500 0.4943 0.02797 0.01932 -0.0299 0.6758 0.8367
3.750 0.5440 0.02678 0.01782 -0.0309 0.5635 0.8393
4.250 0.5901 0.02823 0.01759 -0.0280 0.3222 0.8448
4.500 0.6057 0.02929 0.01820 -0.0266 0.2648 0.8477
4.750 0.6258 0.03030 0.01891 -0.0260 0.2274 0.8508
5.000 0.6499 0.03124 0.01970 -0.0260 0.2004 0.8540
5.250 0.6768 0.03220 0.02053 -0.0265 0.1810 0.8571
5.500 0.7018 0.03294 0.02123 -0.0262 0.1665 0.8600
5.750 0.7307 0.03377 0.02205 -0.0266 0.1548 0.8629
6.000 0.7616 0.03470 0.02286 -0.0275 0.1450 0.8657
6.250 0.7952 0.03566 0.02396 -0.0286 0.1360 0.8686
6.500 0.8282 0.03682 0.02504 -0.0299 0.1289 0.8718
6.750 0.8570 0.03784 0.02627 -0.0302 0.1221 0.8750
7.000 0.8849 0.03896 0.02734 -0.0305 0.1171 0.8785
7.250 0.9130 0.04035 0.02895 -0.0309 0.1119 0.8820
7.500 0.9401 0.04176 0.03052 -0.0313 0.1070 0.8854
7.750 0.9671 0.04318 0.03188 -0.0319 0.1033 0.8884
8.000 0.9877 0.04491 0.03400 -0.0312 0.0994 0.8918
8.250 1.0081 0.04668 0.03606 -0.0307 0.0959 0.8957
8.500 1.0296 0.04837 0.03787 -0.0305 0.0929 0.8998
8.750 1.0494 0.05024 0.03982 -0.0302 0.0903 0.9038
9.000 1.0579 0.05277 0.04289 -0.0284 0.0877 0.9080
9.250 1.0672 0.05543 0.04596 -0.0270 0.0857 0.9122
9.500 1.0764 0.05808 0.04891 -0.0258 0.0839 0.9163
9.750 1.0853 0.06026 0.05128 -0.0245 0.0822 0.9204
10.000 1.0976 0.06233 0.05341 -0.0238 0.0806 0.9250
10.250 1.0885 0.06583 0.05733 -0.0214 0.0795 0.9296
10.500 1.0674 0.06951 0.06145 -0.0181 0.0788 0.9347
10.750 1.0436 0.07389 0.06622 -0.0161 0.0783 0.9403
11.000 1.0155 0.07906 0.07175 -0.0154 0.0781 0.9457
11.250 0.9814 0.08551 0.07852 -0.0164 0.0782 0.9511
11.500 0.9416 0.09409 0.08737 -0.0203 0.0785 0.9559
11.750 0.8944 0.10634 0.09984 -0.0284 0.0791 0.9593
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Polar data table (+)
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