NASA SC(2)-0712 AIRFOIL (sc20712-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0712 AIRFOIL (sc20712-il) Reynolds number: 50,000 Max Cl/Cd: 23.7 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20712-il-50000-n5.txt Download as CSV file: xf-sc20712-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6858 0.08008 0.07144 -0.0578 1.0000 0.0713
-11.500 -0.7139 0.07496 0.06626 -0.0588 1.0000 0.0712
-11.250 -0.7420 0.07094 0.06218 -0.0580 1.0000 0.0711
-11.000 -0.7669 0.06679 0.05788 -0.0578 1.0000 0.0712
-10.750 -0.7792 0.06313 0.05407 -0.0575 1.0000 0.0718
-10.500 -0.7753 0.06076 0.05169 -0.0566 1.0000 0.0731
-10.250 -0.7738 0.05808 0.04889 -0.0559 1.0000 0.0743
-10.000 -0.7724 0.05503 0.04560 -0.0555 1.0000 0.0755
-9.750 -0.7682 0.05185 0.04213 -0.0552 1.0000 0.0767
-9.500 -0.7599 0.04881 0.03876 -0.0550 1.0000 0.0783
-9.250 -0.7485 0.04587 0.03536 -0.0550 1.0000 0.0809
-9.000 -0.7333 0.04328 0.03241 -0.0550 1.0000 0.0835
-8.750 -0.7154 0.04153 0.03062 -0.0543 1.0000 0.0859
-8.500 -0.6965 0.03970 0.02861 -0.0538 1.0000 0.0886
-8.250 -0.6766 0.03798 0.02661 -0.0534 1.0000 0.0925
-8.000 -0.6559 0.03633 0.02471 -0.0528 1.0000 0.0965
-7.750 -0.6359 0.03507 0.02350 -0.0517 1.0000 0.1001
-7.500 -0.6151 0.03391 0.02221 -0.0506 1.0000 0.1048
-7.250 -0.5941 0.03283 0.02096 -0.0494 1.0000 0.1105
-7.000 -0.5744 0.03191 0.02015 -0.0479 1.0000 0.1159
-6.750 -0.5537 0.03111 0.01923 -0.0464 1.0000 0.1230
-6.500 -0.5338 0.03029 0.01848 -0.0451 1.0000 0.1306
-6.250 -0.5127 0.02956 0.01765 -0.0440 1.0000 0.1406
-6.000 -0.4917 0.02871 0.01695 -0.0433 1.0000 0.1522
-5.750 -0.4693 0.02784 0.01617 -0.0430 1.0000 0.1677
-5.500 -0.4451 0.02688 0.01538 -0.0432 1.0000 0.1898
-5.250 -0.4176 0.02564 0.01451 -0.0448 1.0000 0.2278
-5.000 -0.3868 0.02407 0.01371 -0.0475 1.0000 0.3207
-4.750 -0.3760 0.02408 0.01479 -0.0427 1.0000 0.4477
-4.250 -0.3411 0.02565 0.01645 -0.0362 1.0000 0.5930
-4.000 -0.3207 0.02637 0.01705 -0.0340 1.0000 0.6268
-3.750 -0.3012 0.02705 0.01760 -0.0317 1.0000 0.6537
-3.500 -0.2882 0.02781 0.01831 -0.0274 1.0000 0.6756
-3.250 -0.2748 0.02848 0.01894 -0.0234 1.0000 0.6983
-3.000 -0.2583 0.02902 0.01941 -0.0205 1.0000 0.7216
-2.750 -0.2447 0.02936 0.01970 -0.0169 1.0000 0.7395
-2.500 -0.2295 0.02952 0.01980 -0.0139 1.0000 0.7545
-2.250 -0.2138 0.02951 0.01976 -0.0113 1.0000 0.7663
-2.000 -0.1933 0.02946 0.01964 -0.0102 1.0000 0.7775
-1.750 -0.1685 0.02944 0.01954 -0.0104 1.0000 0.7881
-1.500 -0.1507 0.02929 0.01936 -0.0087 1.0000 0.7958
-1.250 -0.1236 0.02929 0.01931 -0.0096 1.0000 0.8042
-1.000 -0.1033 0.02916 0.01916 -0.0088 1.0000 0.8100
-0.750 -0.0771 0.02916 0.01914 -0.0095 1.0000 0.8159
-0.500 -0.0503 0.02920 0.01917 -0.0104 1.0000 0.8209
-0.250 -0.0255 0.02921 0.01919 -0.0108 0.9991 0.8255
0.000 0.0140 0.02945 0.01943 -0.0141 0.9933 0.8299
0.250 0.0540 0.02970 0.01970 -0.0177 0.9863 0.8342
0.500 0.0915 0.02985 0.01991 -0.0203 0.9786 0.8377
0.750 0.1316 0.03006 0.02018 -0.0235 0.9704 0.8412
1.000 0.1702 0.03021 0.02042 -0.0265 0.9600 0.8447
1.250 0.2131 0.03039 0.02070 -0.0301 0.9485 0.8482
1.500 0.2561 0.03041 0.02085 -0.0334 0.9350 0.8513
1.750 0.2982 0.03021 0.02080 -0.0361 0.9180 0.8543
2.000 0.3485 0.02962 0.02038 -0.0394 0.8948 0.8573
2.250 0.3961 0.02860 0.01955 -0.0415 0.8641 0.8601
2.500 0.4419 0.02742 0.01856 -0.0429 0.8309 0.8627
2.750 0.4743 0.02650 0.01784 -0.0422 0.7933 0.8653
3.000 0.4999 0.02570 0.01721 -0.0403 0.7438 0.8685
3.250 0.5440 0.02442 0.01589 -0.0402 0.6368 0.8714
3.500 0.5888 0.02495 0.01476 -0.0404 0.3781 0.8739
3.750 0.6047 0.02645 0.01550 -0.0390 0.2713 0.8774
4.000 0.6246 0.02762 0.01627 -0.0383 0.2176 0.8807
4.250 0.6466 0.02862 0.01702 -0.0377 0.1868 0.8842
4.500 0.6724 0.02955 0.01787 -0.0377 0.1640 0.8879
4.750 0.7013 0.03054 0.01880 -0.0383 0.1474 0.8915
5.000 0.7309 0.03146 0.01971 -0.0387 0.1347 0.8952
5.250 0.7602 0.03243 0.02062 -0.0392 0.1244 0.8990
5.500 0.7932 0.03352 0.02187 -0.0400 0.1154 0.9029
5.750 0.8251 0.03484 0.02306 -0.0411 0.1083 0.9066
6.000 0.8544 0.03605 0.02459 -0.0413 0.1018 0.9103
6.250 0.8831 0.03743 0.02600 -0.0418 0.0969 0.9141
6.500 0.9115 0.03910 0.02785 -0.0422 0.0923 0.9180
6.750 0.9371 0.04080 0.02989 -0.0422 0.0879 0.9222
7.000 0.9611 0.04252 0.03178 -0.0419 0.0849 0.9269
7.250 0.9851 0.04441 0.03369 -0.0420 0.0820 0.9320
7.500 1.0019 0.04678 0.03667 -0.0408 0.0789 0.9372
7.750 1.0182 0.04928 0.03961 -0.0397 0.0765 0.9427
8.000 1.0332 0.05188 0.04256 -0.0387 0.0747 0.9487
8.250 1.0483 0.05412 0.04501 -0.0379 0.0728 0.9558
8.500 1.0644 0.05645 0.04739 -0.0374 0.0710 0.9647
8.750 1.0609 0.06028 0.05191 -0.0350 0.0696 0.9820
9.000 1.0560 0.06448 0.05665 -0.0332 0.0685 1.0000
9.250 1.0465 0.06889 0.06149 -0.0314 0.0679 1.0000
9.500 1.0302 0.07332 0.06628 -0.0296 0.0677 1.0000
9.750 1.0086 0.07830 0.07157 -0.0285 0.0677 1.0000
10.000 0.9820 0.08421 0.07775 -0.0290 0.0679 1.0000
10.250 0.9507 0.09161 0.08539 -0.0319 0.0683 1.0000
10.500 0.9186 0.10094 0.09489 -0.0378 0.0688 1.0000
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Polar data table (+)
Polar graphs
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