NASA SC(2)-0712 AIRFOIL (sc20712-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0712 AIRFOIL (sc20712-il) Reynolds number: 100,000 Max Cl/Cd: 32.01 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20712-il-100000.txt Download as CSV file: xf-sc20712-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0712 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5079 0.10256 0.09685 -0.0295 1.0000 0.1825
-10.250 -0.7729 0.06411 0.05795 -0.0545 1.0000 0.0966
-10.000 -0.7687 0.06010 0.05382 -0.0537 1.0000 0.0935
-9.750 -0.7707 0.05558 0.04911 -0.0535 1.0000 0.0921
-9.500 -0.7700 0.05105 0.04424 -0.0539 1.0000 0.0915
-9.250 -0.7621 0.04693 0.03971 -0.0545 1.0000 0.0919
-9.000 -0.7480 0.04309 0.03542 -0.0553 1.0000 0.0925
-8.750 -0.7293 0.03960 0.03148 -0.0562 1.0000 0.0930
-8.500 -0.7066 0.03690 0.02824 -0.0571 1.0000 0.0946
-8.250 -0.6842 0.03405 0.02515 -0.0577 1.0000 0.0975
-8.000 -0.6615 0.03232 0.02337 -0.0576 1.0000 0.1004
-7.750 -0.6370 0.03066 0.02151 -0.0577 1.0000 0.1033
-7.500 -0.6109 0.02928 0.01983 -0.0579 1.0000 0.1078
-7.250 -0.5859 0.02759 0.01801 -0.0579 1.0000 0.1120
-7.000 -0.5617 0.02640 0.01685 -0.0575 1.0000 0.1166
-6.750 -0.5356 0.02548 0.01577 -0.0575 1.0000 0.1232
-6.500 -0.5109 0.02429 0.01467 -0.0571 1.0000 0.1298
-6.250 -0.4847 0.02349 0.01384 -0.0570 1.0000 0.1383
-6.000 -0.4591 0.02258 0.01308 -0.0568 1.0000 0.1485
-5.750 -0.4324 0.02177 0.01236 -0.0568 1.0000 0.1615
-5.500 -0.4046 0.02099 0.01178 -0.0573 1.0000 0.1800
-5.250 -0.3738 0.02009 0.01122 -0.0585 1.0000 0.2129
-5.000 -0.3284 0.01794 0.01119 -0.0635 1.0000 0.4849
-4.750 -0.3140 0.01913 0.01257 -0.0591 1.0000 0.5999
-4.250 -0.2886 0.02130 0.01465 -0.0502 1.0000 0.6526
-4.000 -0.2761 0.02223 0.01553 -0.0459 1.0000 0.6698
-3.750 -0.2682 0.02314 0.01645 -0.0403 1.0000 0.6826
-3.500 -0.2594 0.02394 0.01723 -0.0351 1.0000 0.6959
-3.250 -0.2480 0.02459 0.01786 -0.0307 1.0000 0.7105
-3.000 -0.2353 0.02513 0.01836 -0.0269 1.0000 0.7258
-2.750 -0.2216 0.02557 0.01878 -0.0234 1.0000 0.7414
-2.500 -0.2099 0.02596 0.01916 -0.0194 1.0000 0.7575
-2.250 -0.2003 0.02626 0.01945 -0.0149 1.0000 0.7740
-2.000 -0.1916 0.02641 0.01961 -0.0103 1.0000 0.7906
-1.750 -0.1803 0.02642 0.01962 -0.0065 1.0000 0.8064
-1.500 -0.1639 0.02639 0.01957 -0.0044 1.0000 0.8207
-1.250 -0.1470 0.02625 0.01942 -0.0025 1.0000 0.8322
-1.000 -0.1293 0.02604 0.01920 -0.0009 1.0000 0.8415
-0.750 -0.1026 0.02608 0.01921 -0.0018 1.0000 0.8506
-0.500 -0.0846 0.02586 0.01901 -0.0005 1.0000 0.8583
-0.250 -0.0565 0.02597 0.01911 -0.0019 1.0000 0.8654
0.000 -0.0354 0.02586 0.01902 -0.0015 1.0000 0.8706
0.250 -0.0078 0.02601 0.01919 -0.0029 1.0000 0.8751
0.500 0.0231 0.02632 0.01953 -0.0052 1.0000 0.8790
0.750 0.0602 0.02652 0.01977 -0.0080 0.9944 0.8826
1.000 0.1163 0.02693 0.02023 -0.0144 0.9818 0.8858
1.250 0.1697 0.02703 0.02039 -0.0199 0.9641 0.8891
1.500 0.2389 0.02682 0.02027 -0.0275 0.9423 0.8918
1.750 0.2962 0.02613 0.01968 -0.0322 0.9212 0.8946
2.000 0.3467 0.02516 0.01884 -0.0353 0.8999 0.8972
2.250 0.4025 0.02390 0.01773 -0.0388 0.8802 0.8993
2.500 0.4575 0.02232 0.01631 -0.0416 0.8592 0.9016
2.750 0.5074 0.02055 0.01473 -0.0430 0.8313 0.9044
3.000 0.5485 0.01902 0.01332 -0.0429 0.7822 0.9069
3.250 0.5947 0.01858 0.01121 -0.0419 0.4285 0.9086
3.500 0.6015 0.02053 0.01184 -0.0386 0.2529 0.9113
3.750 0.6213 0.02167 0.01251 -0.0376 0.2029 0.9146
4.000 0.6464 0.02264 0.01326 -0.0375 0.1757 0.9176
4.250 0.6751 0.02374 0.01415 -0.0382 0.1574 0.9200
4.500 0.7025 0.02456 0.01492 -0.0383 0.1437 0.9226
4.750 0.7322 0.02563 0.01595 -0.0388 0.1333 0.9253
5.000 0.7639 0.02698 0.01713 -0.0399 0.1243 0.9280
5.250 0.7946 0.02802 0.01837 -0.0406 0.1171 0.9312
5.500 0.8255 0.02930 0.01964 -0.0414 0.1113 0.9346
5.750 0.8537 0.03090 0.02136 -0.0416 0.1064 0.9382
6.000 0.8812 0.03222 0.02296 -0.0416 0.1019 0.9417
6.250 0.9102 0.03385 0.02471 -0.0422 0.0984 0.9450
6.500 0.9373 0.03651 0.02735 -0.0429 0.0949 0.9487
6.750 0.9567 0.03794 0.02936 -0.0414 0.0924 0.9532
7.000 0.9771 0.04047 0.03235 -0.0404 0.0910 0.9576
7.250 0.9941 0.04323 0.03558 -0.0391 0.0898 0.9622
7.500 1.0088 0.04603 0.03880 -0.0377 0.0882 0.9676
7.750 1.0221 0.04904 0.04218 -0.0364 0.0869 0.9733
8.000 1.0264 0.05367 0.04738 -0.0344 0.0881 0.9801
8.250 1.0253 0.05909 0.05331 -0.0324 0.0907 0.9922
8.500 1.0316 0.06445 0.05892 -0.0321 0.0931 1.0000
8.750 0.8078 0.10087 0.09702 -0.0448 0.1796 1.0000
9.000 0.8329 0.10317 0.09935 -0.0429 0.1751 1.0000
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Polar data table (+)
Polar graphs
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