NASA SC(2)-0714 AIRFOIL (sc20714-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA SC(2)-0714 AIRFOIL (sc20714-il) Reynolds number: 200,000 Max Cl/Cd: 43.69 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20714-il-200000-n5.txt Download as CSV file: xf-sc20714-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0714 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8755 0.08550 0.08017 -0.0656 1.0000 0.0345
-16.250 -0.9119 0.07585 0.07024 -0.0711 1.0000 0.0346
-16.000 -0.9332 0.06956 0.06374 -0.0741 1.0000 0.0348
-15.750 -0.9490 0.06462 0.05862 -0.0759 1.0000 0.0350
-15.500 -0.9618 0.06050 0.05432 -0.0769 1.0000 0.0352
-15.250 -0.9727 0.05697 0.05063 -0.0772 1.0000 0.0355
-15.000 -0.9817 0.05387 0.04736 -0.0770 1.0000 0.0359
-14.750 -0.9892 0.05111 0.04443 -0.0764 1.0000 0.0362
-14.500 -0.9953 0.04864 0.04178 -0.0754 1.0000 0.0366
-14.250 -1.0005 0.04643 0.03939 -0.0741 1.0000 0.0370
-14.000 -1.0047 0.04445 0.03722 -0.0724 1.0000 0.0374
-13.750 -1.0028 0.04305 0.03582 -0.0707 1.0000 0.0378
-13.500 -1.0015 0.04180 0.03455 -0.0687 1.0000 0.0382
-13.250 -1.0011 0.04061 0.03333 -0.0665 1.0000 0.0386
-13.000 -1.0017 0.03949 0.03217 -0.0641 1.0000 0.0391
-12.750 -1.0032 0.03841 0.03104 -0.0613 1.0000 0.0396
-12.500 -1.0060 0.03739 0.02996 -0.0582 1.0000 0.0401
-12.250 -1.0105 0.03643 0.02893 -0.0546 1.0000 0.0406
-12.000 -1.0123 0.03544 0.02784 -0.0514 1.0000 0.0412
-11.750 -1.0077 0.03436 0.02665 -0.0492 1.0000 0.0419
-11.500 -1.0002 0.03331 0.02546 -0.0473 1.0000 0.0426
-11.250 -0.9785 0.03217 0.02431 -0.0480 0.9984 0.0434
-11.000 -0.9546 0.03116 0.02329 -0.0491 0.9965 0.0442
-10.750 -0.9296 0.03022 0.02230 -0.0503 0.9947 0.0453
-10.500 -0.9032 0.02933 0.02134 -0.0516 0.9931 0.0467
-10.250 -0.8782 0.02847 0.02036 -0.0524 0.9912 0.0482
-10.000 -0.8530 0.02759 0.01946 -0.0533 0.9889 0.0495
-9.750 -0.8262 0.02681 0.01868 -0.0546 0.9867 0.0509
-9.500 -0.7987 0.02608 0.01792 -0.0558 0.9849 0.0525
-9.250 -0.7702 0.02539 0.01716 -0.0570 0.9834 0.0543
-9.000 -0.7409 0.02468 0.01643 -0.0585 0.9821 0.0562
-8.750 -0.7101 0.02405 0.01581 -0.0603 0.9810 0.0583
-8.500 -0.6852 0.02345 0.01518 -0.0607 0.9782 0.0605
-8.250 -0.6570 0.02289 0.01455 -0.0617 0.9758 0.0628
-8.000 -0.6269 0.02220 0.01392 -0.0634 0.9738 0.0653
-7.750 -0.5955 0.02167 0.01338 -0.0651 0.9721 0.0685
-7.500 -0.5626 0.02113 0.01282 -0.0671 0.9706 0.0719
-7.250 -0.5284 0.02057 0.01231 -0.0694 0.9694 0.0759
-7.000 -0.4939 0.02014 0.01185 -0.0716 0.9683 0.0806
-6.750 -0.4618 0.01962 0.01140 -0.0734 0.9668 0.0858
-6.500 -0.4333 0.01924 0.01100 -0.0743 0.9640 0.0918
-6.250 -0.4005 0.01875 0.01058 -0.0763 0.9618 0.0995
-6.000 -0.3660 0.01831 0.01019 -0.0785 0.9600 0.1089
-5.750 -0.3305 0.01788 0.00985 -0.0809 0.9586 0.1223
-5.500 -0.2941 0.01745 0.00952 -0.0835 0.9574 0.1422
-5.250 -0.2557 0.01696 0.00919 -0.0867 0.9564 0.1711
-5.000 -0.2149 0.01636 0.00883 -0.0905 0.9557 0.2172
-4.750 -0.1680 0.01543 0.00839 -0.0963 0.9556 0.3130
-4.500 -0.1203 0.01458 0.00831 -0.1021 0.9557 0.4623
-4.250 -0.0916 0.01490 0.00904 -0.1015 0.9541 0.5417
-4.000 -0.0646 0.01515 0.00933 -0.1011 0.9508 0.5704
-3.750 -0.0360 0.01532 0.00948 -0.1012 0.9470 0.5874
-3.500 -0.0028 0.01543 0.00955 -0.1024 0.9445 0.6022
-3.250 0.0313 0.01559 0.00967 -0.1035 0.9423 0.6150
-3.000 0.0620 0.01587 0.00998 -0.1036 0.9401 0.6229
-2.750 0.0986 0.01607 0.01015 -0.1052 0.9387 0.6356
-2.500 0.1113 0.01668 0.01085 -0.1011 0.9321 0.6415
-2.250 0.1441 0.01690 0.01104 -0.1020 0.9288 0.6531
-2.000 0.1707 0.01718 0.01138 -0.1008 0.9256 0.6559
-1.750 0.2042 0.01724 0.01147 -0.1015 0.9235 0.6584
-1.500 0.2362 0.01720 0.01145 -0.1020 0.9192 0.6610
-1.250 0.2672 0.01704 0.01129 -0.1025 0.9120 0.6641
-1.000 0.3132 0.01658 0.01082 -0.1061 0.9086 0.6679
-0.750 0.3579 0.01591 0.01013 -0.1093 0.8998 0.6714
-0.500 0.3992 0.01524 0.00947 -0.1108 0.8877 0.6726
-0.250 0.4286 0.01495 0.00920 -0.1103 0.8722 0.6739
0.000 0.4582 0.01474 0.00902 -0.1099 0.8546 0.6756
0.250 0.4909 0.01452 0.00880 -0.1103 0.8350 0.6774
0.500 0.5234 0.01433 0.00860 -0.1107 0.8074 0.6793
0.750 0.5648 0.01404 0.00813 -0.1128 0.7509 0.6810
1.000 0.5947 0.01445 0.00779 -0.1125 0.6122 0.6831
1.250 0.6119 0.01542 0.00800 -0.1104 0.4743 0.6858
1.500 0.6339 0.01622 0.00822 -0.1099 0.3679 0.6886
1.750 0.6568 0.01693 0.00847 -0.1094 0.2821 0.6904
2.000 0.6785 0.01754 0.00879 -0.1083 0.2219 0.6913
2.250 0.7014 0.01808 0.00910 -0.1075 0.1784 0.6923
2.500 0.7256 0.01852 0.00940 -0.1068 0.1512 0.6934
2.750 0.7499 0.01893 0.00973 -0.1061 0.1328 0.6947
3.000 0.7748 0.01932 0.01006 -0.1056 0.1183 0.6961
3.250 0.8002 0.01970 0.01038 -0.1051 0.1073 0.6976
3.500 0.8258 0.02009 0.01073 -0.1048 0.0991 0.6991
3.750 0.8518 0.02047 0.01108 -0.1045 0.0926 0.7007
4.000 0.8778 0.02088 0.01147 -0.1043 0.0872 0.7024
4.250 0.9045 0.02125 0.01184 -0.1042 0.0820 0.7042
4.500 0.9307 0.02171 0.01225 -0.1042 0.0779 0.7061
4.750 0.9583 0.02209 0.01264 -0.1043 0.0740 0.7082
5.000 0.9833 0.02257 0.01309 -0.1040 0.0707 0.7100
5.250 1.0057 0.02308 0.01362 -0.1029 0.0680 0.7111
5.500 1.0287 0.02355 0.01415 -0.1020 0.0653 0.7122
5.750 1.0513 0.02406 0.01468 -0.1010 0.0630 0.7134
6.000 1.0731 0.02469 0.01530 -0.1000 0.0610 0.7146
6.250 1.0963 0.02520 0.01590 -0.0992 0.0587 0.7159
6.500 1.1191 0.02574 0.01649 -0.0983 0.0566 0.7174
6.750 1.1412 0.02633 0.01709 -0.0974 0.0548 0.7189
7.000 1.1629 0.02704 0.01781 -0.0965 0.0533 0.7206
7.250 1.1856 0.02768 0.01855 -0.0956 0.0516 0.7223
7.500 1.2077 0.02832 0.01925 -0.0948 0.0500 0.7242
7.750 1.2293 0.02898 0.01992 -0.0939 0.0485 0.7264
8.000 1.2502 0.02979 0.02070 -0.0931 0.0473 0.7288
8.250 1.2693 0.03053 0.02160 -0.0916 0.0459 0.7300
8.500 1.2866 0.03131 0.02250 -0.0898 0.0446 0.7312
8.750 1.3024 0.03209 0.02336 -0.0878 0.0436 0.7325
9.000 1.3173 0.03289 0.02422 -0.0858 0.0427 0.7339
9.250 1.3328 0.03381 0.02516 -0.0840 0.0420 0.7354
9.500 1.3491 0.03488 0.02634 -0.0824 0.0411 0.7370
9.750 1.3652 0.03597 0.02760 -0.0807 0.0401 0.7388
10.000 1.3804 0.03706 0.02883 -0.0790 0.0392 0.7407
10.250 1.3947 0.03815 0.03003 -0.0773 0.0383 0.7426
10.500 1.4082 0.03925 0.03120 -0.0756 0.0376 0.7447
10.750 1.4211 0.04041 0.03241 -0.0740 0.0370 0.7471
11.000 1.4318 0.04167 0.03373 -0.0719 0.0365 0.7486
11.250 1.4406 0.04322 0.03546 -0.0697 0.0360 0.7501
11.500 1.4476 0.04496 0.03744 -0.0674 0.0354 0.7516
11.750 1.4532 0.04681 0.03952 -0.0651 0.0349 0.7532
12.000 1.4572 0.04876 0.04168 -0.0629 0.0344 0.7549
12.250 1.4601 0.05083 0.04394 -0.0607 0.0339 0.7566
12.500 1.4616 0.05301 0.04630 -0.0588 0.0335 0.7584
12.750 1.4622 0.05531 0.04877 -0.0570 0.0332 0.7602
13.000 1.4620 0.05773 0.05133 -0.0554 0.0328 0.7621
13.250 1.4613 0.06028 0.05401 -0.0542 0.0325 0.7640
13.500 1.4598 0.06295 0.05680 -0.0531 0.0322 0.7657
13.750 1.4567 0.06581 0.05978 -0.0522 0.0320 0.7669
14.000 1.4525 0.06895 0.06304 -0.0516 0.0318 0.7682
14.250 1.4429 0.07297 0.06725 -0.0515 0.0315 0.7696
14.500 1.4233 0.07865 0.07324 -0.0524 0.0314 0.7709
14.750 1.3998 0.08551 0.08042 -0.0547 0.0312 0.7721
15.000 1.3726 0.09381 0.08904 -0.0588 0.0311 0.7731
15.250 1.3374 0.10465 0.10022 -0.0655 0.0310 0.7739
15.500 1.2822 0.12158 0.11756 -0.0777 0.0311 0.7737
|
Polar data table (+)
Polar graphs
<< Back to NASA SC(2)-0714 AIRFOIL (sc20714-il)