NASA SC(2)-0712 AIRFOIL (sc20712-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0712 AIRFOIL (sc20712-il) Reynolds number: 200,000 Max Cl/Cd: 47.38 at α=0.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20712-il-200000-n5.txt Download as CSV file: xf-sc20712-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8543 0.07737 0.07240 -0.0590 1.0000 0.0283
-15.000 -0.8901 0.06779 0.06254 -0.0652 1.0000 0.0282
-14.750 -0.9159 0.06108 0.05558 -0.0688 1.0000 0.0283
-14.500 -0.9360 0.05584 0.05009 -0.0708 1.0000 0.0284
-14.250 -0.9521 0.05156 0.04556 -0.0716 1.0000 0.0286
-14.000 -0.9650 0.04802 0.04177 -0.0716 1.0000 0.0288
-13.750 -0.9712 0.04541 0.03903 -0.0709 1.0000 0.0291
-13.500 -0.9727 0.04347 0.03703 -0.0697 1.0000 0.0293
-13.250 -0.9743 0.04177 0.03527 -0.0682 1.0000 0.0296
-13.000 -0.9772 0.04025 0.03369 -0.0660 1.0000 0.0299
-12.750 -0.9826 0.03891 0.03228 -0.0632 1.0000 0.0301
-12.500 -0.9848 0.03754 0.03084 -0.0607 1.0000 0.0305
-12.250 -0.9816 0.03611 0.02930 -0.0591 1.0000 0.0309
-12.000 -0.9754 0.03469 0.02776 -0.0578 1.0000 0.0314
-11.750 -0.9664 0.03330 0.02621 -0.0569 1.0000 0.0322
-11.500 -0.9550 0.03191 0.02463 -0.0560 1.0000 0.0330
-11.250 -0.9415 0.03058 0.02309 -0.0552 1.0000 0.0339
-11.000 -0.9260 0.02956 0.02207 -0.0546 1.0000 0.0346
-10.750 -0.9089 0.02869 0.02117 -0.0540 1.0000 0.0353
-10.500 -0.8909 0.02781 0.02022 -0.0535 1.0000 0.0362
-10.250 -0.8719 0.02690 0.01922 -0.0531 1.0000 0.0372
-10.000 -0.8522 0.02599 0.01819 -0.0526 1.0000 0.0383
-9.750 -0.8302 0.02513 0.01720 -0.0525 0.9997 0.0396
-9.500 -0.8005 0.02434 0.01643 -0.0541 0.9983 0.0409
-9.250 -0.7700 0.02365 0.01570 -0.0556 0.9967 0.0426
-9.000 -0.7391 0.02293 0.01488 -0.0571 0.9952 0.0445
-8.750 -0.7077 0.02218 0.01406 -0.0586 0.9938 0.0463
-8.500 -0.6769 0.02153 0.01342 -0.0602 0.9922 0.0482
-8.250 -0.6465 0.02096 0.01280 -0.0615 0.9904 0.0507
-8.000 -0.6152 0.02040 0.01215 -0.0629 0.9885 0.0530
-7.750 -0.5829 0.01970 0.01151 -0.0647 0.9868 0.0556
-7.500 -0.5498 0.01921 0.01099 -0.0665 0.9852 0.0589
-7.250 -0.5162 0.01869 0.01045 -0.0684 0.9839 0.0624
-7.000 -0.4819 0.01817 0.00996 -0.0705 0.9828 0.0664
-6.750 -0.4489 0.01779 0.00953 -0.0722 0.9811 0.0711
-6.500 -0.4168 0.01728 0.00908 -0.0738 0.9787 0.0764
-6.250 -0.3838 0.01692 0.00869 -0.0754 0.9766 0.0824
-6.000 -0.3495 0.01648 0.00832 -0.0774 0.9750 0.0904
-5.750 -0.3146 0.01610 0.00797 -0.0795 0.9735 0.1004
-5.500 -0.2787 0.01571 0.00764 -0.0818 0.9722 0.1146
-5.250 -0.2416 0.01528 0.00735 -0.0845 0.9711 0.1388
-5.000 -0.2029 0.01473 0.00704 -0.0876 0.9702 0.1842
-4.750 -0.1617 0.01400 0.00672 -0.0917 0.9698 0.2682
-4.500 -0.1185 0.01319 0.00644 -0.0962 0.9697 0.3842
-4.250 -0.0804 0.01282 0.00667 -0.0989 0.9692 0.5101
-4.000 -0.0544 0.01293 0.00693 -0.0983 0.9649 0.5569
-3.750 -0.0224 0.01302 0.00702 -0.0991 0.9619 0.5843
-3.500 0.0100 0.01314 0.00715 -0.1000 0.9596 0.6035
-3.250 0.0428 0.01330 0.00733 -0.1008 0.9576 0.6205
-3.000 0.0767 0.01350 0.00754 -0.1017 0.9559 0.6373
-2.750 0.1041 0.01373 0.00778 -0.1014 0.9519 0.6497
-2.500 0.1293 0.01402 0.00812 -0.1004 0.9475 0.6582
-2.250 0.1635 0.01411 0.00819 -0.1017 0.9450 0.6678
-2.000 0.1953 0.01423 0.00835 -0.1021 0.9428 0.6722
-1.750 0.2288 0.01434 0.00850 -0.1029 0.9409 0.6773
-1.500 0.2574 0.01441 0.00858 -0.1030 0.9356 0.6833
-1.250 0.2921 0.01432 0.00849 -0.1044 0.9313 0.6872
-1.000 0.3363 0.01390 0.00811 -0.1071 0.9261 0.6889
-0.750 0.3718 0.01346 0.00770 -0.1078 0.9128 0.6907
-0.500 0.4073 0.01304 0.00730 -0.1085 0.8976 0.6929
-0.250 0.4440 0.01266 0.00691 -0.1095 0.8784 0.6955
0.000 0.4768 0.01244 0.00668 -0.1100 0.8562 0.6984
0.250 0.5112 0.01225 0.00646 -0.1110 0.8326 0.7016
0.500 0.5458 0.01209 0.00621 -0.1119 0.7965 0.7042
0.750 0.5752 0.01214 0.00603 -0.1114 0.7242 0.7056
1.000 0.5933 0.01299 0.00604 -0.1087 0.5586 0.7073
1.250 0.6082 0.01417 0.00645 -0.1061 0.4049 0.7093
1.500 0.6279 0.01510 0.00684 -0.1047 0.2937 0.7114
1.750 0.6508 0.01584 0.00718 -0.1041 0.2144 0.7137
2.000 0.6760 0.01641 0.00748 -0.1038 0.1652 0.7165
2.250 0.7032 0.01687 0.00776 -0.1039 0.1357 0.7196
2.500 0.7304 0.01726 0.00805 -0.1039 0.1173 0.7220
2.750 0.7555 0.01765 0.00840 -0.1033 0.1038 0.7234
3.000 0.7806 0.01805 0.00877 -0.1028 0.0931 0.7251
3.250 0.8061 0.01845 0.00914 -0.1023 0.0847 0.7269
3.500 0.8316 0.01885 0.00955 -0.1018 0.0781 0.7289
3.750 0.8571 0.01931 0.00997 -0.1015 0.0722 0.7311
4.000 0.8832 0.01974 0.01043 -0.1011 0.0674 0.7336
4.250 0.9096 0.02021 0.01089 -0.1010 0.0633 0.7364
4.500 0.9354 0.02075 0.01141 -0.1007 0.0598 0.7393
4.750 0.9593 0.02122 0.01195 -0.0999 0.0566 0.7409
5.000 0.9828 0.02175 0.01249 -0.0990 0.0540 0.7428
5.250 1.0060 0.02238 0.01315 -0.0982 0.0518 0.7447
5.500 1.0302 0.02294 0.01379 -0.0975 0.0495 0.7469
5.750 1.0544 0.02350 0.01437 -0.0969 0.0473 0.7495
6.000 1.0778 0.02422 0.01507 -0.0962 0.0456 0.7524
6.250 1.1028 0.02492 0.01585 -0.0958 0.0439 0.7557
6.500 1.1252 0.02559 0.01663 -0.0948 0.0423 0.7576
6.750 1.1473 0.02623 0.01733 -0.0937 0.0407 0.7596
7.000 1.1689 0.02696 0.01807 -0.0928 0.0395 0.7618
7.250 1.1910 0.02784 0.01905 -0.0918 0.0382 0.7640
7.500 1.2134 0.02874 0.02009 -0.0909 0.0371 0.7665
7.750 1.2355 0.02964 0.02109 -0.0901 0.0359 0.7692
8.000 1.2576 0.03050 0.02200 -0.0893 0.0349 0.7721
8.250 1.2770 0.03134 0.02289 -0.0881 0.0340 0.7739
8.500 1.2957 0.03242 0.02406 -0.0867 0.0332 0.7759
8.750 1.3144 0.03356 0.02543 -0.0852 0.0322 0.7781
9.000 1.3322 0.03475 0.02681 -0.0837 0.0313 0.7805
9.250 1.3491 0.03596 0.02818 -0.0822 0.0306 0.7833
9.500 1.3653 0.03717 0.02951 -0.0806 0.0300 0.7865
9.750 1.3799 0.03834 0.03079 -0.0789 0.0295 0.7892
10.000 1.3921 0.03956 0.03210 -0.0767 0.0290 0.7914
10.250 1.4028 0.04099 0.03362 -0.0745 0.0286 0.7937
10.500 1.4067 0.04278 0.03569 -0.0712 0.0283 0.7963
10.750 1.4086 0.04483 0.03806 -0.0679 0.0278 0.7990
11.000 1.4090 0.04709 0.04061 -0.0648 0.0273 0.8019
11.250 1.4070 0.04948 0.04328 -0.0617 0.0269 0.8045
11.500 1.4026 0.05195 0.04602 -0.0587 0.0265 0.8067
11.750 1.3964 0.05463 0.04896 -0.0559 0.0262 0.8091
12.000 1.3895 0.05747 0.05201 -0.0536 0.0258 0.8117
12.250 1.3804 0.06071 0.05547 -0.0518 0.0256 0.8143
12.500 1.3695 0.06434 0.05932 -0.0506 0.0254 0.8168
12.750 1.3564 0.06855 0.06375 -0.0502 0.0252 0.8192
13.000 1.3380 0.07370 0.06914 -0.0506 0.0251 0.8208
13.250 1.3129 0.08053 0.07624 -0.0528 0.0250 0.8222
13.500 1.2668 0.09252 0.08862 -0.0597 0.0251 0.8231
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