NASA SC(2)-0412 AIRFOIL (sc20412-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0412 AIRFOIL (sc20412-il) Reynolds number: 50,000 Max Cl/Cd: 21.84 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20412-il-50000-n5.txt Download as CSV file: xf-sc20412-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0412 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7423 0.08558 0.07698 -0.0409 1.0000 0.0707
-11.250 -0.7697 0.07879 0.07007 -0.0443 1.0000 0.0705
-11.000 -0.7961 0.07316 0.06430 -0.0462 1.0000 0.0704
-10.750 -0.8210 0.06853 0.05949 -0.0466 1.0000 0.0705
-10.500 -0.8419 0.06418 0.05486 -0.0468 1.0000 0.0707
-10.250 -0.8404 0.06127 0.05188 -0.0464 1.0000 0.0719
-10.000 -0.8334 0.05893 0.04948 -0.0459 1.0000 0.0735
-9.750 -0.8306 0.05611 0.04647 -0.0453 1.0000 0.0752
-9.500 -0.8277 0.05302 0.04309 -0.0448 1.0000 0.0768
-9.250 -0.8221 0.04986 0.03956 -0.0441 1.0000 0.0783
-9.000 -0.8137 0.04684 0.03608 -0.0434 1.0000 0.0804
-8.750 -0.8002 0.04440 0.03339 -0.0428 1.0000 0.0830
-8.500 -0.7827 0.04266 0.03160 -0.0420 1.0000 0.0858
-8.250 -0.7650 0.04073 0.02947 -0.0412 1.0000 0.0888
-8.000 -0.7466 0.03880 0.02722 -0.0404 1.0000 0.0924
-7.750 -0.7269 0.03712 0.02541 -0.0395 1.0000 0.0962
-7.500 -0.7065 0.03577 0.02405 -0.0385 1.0000 0.1002
-7.250 -0.6854 0.03444 0.02255 -0.0374 1.0000 0.1049
-7.000 -0.6641 0.03322 0.02126 -0.0361 1.0000 0.1102
-6.750 -0.6432 0.03221 0.02031 -0.0348 1.0000 0.1158
-6.500 -0.6215 0.03131 0.01921 -0.0333 1.0000 0.1227
-6.250 -0.6018 0.03040 0.01846 -0.0317 1.0000 0.1298
-6.000 -0.5818 0.02960 0.01758 -0.0301 1.0000 0.1388
-5.750 -0.5637 0.02870 0.01682 -0.0287 1.0000 0.1488
-5.500 -0.5457 0.02781 0.01600 -0.0273 1.0000 0.1610
-5.250 -0.5278 0.02686 0.01519 -0.0262 1.0000 0.1776
-5.000 -0.5096 0.02582 0.01432 -0.0253 1.0000 0.2014
-4.750 -0.4912 0.02451 0.01339 -0.0250 1.0000 0.2401
-4.500 -0.4718 0.02290 0.01250 -0.0253 1.0000 0.3238
-4.250 -0.4626 0.02272 0.01350 -0.0202 1.0000 0.4580
-4.000 -0.4512 0.02387 0.01495 -0.0141 1.0000 0.5518
-3.750 -0.4286 0.02431 0.01520 -0.0131 1.0000 0.6129
-3.250 -0.3915 0.02556 0.01620 -0.0080 1.0000 0.6733
-3.000 -0.3750 0.02613 0.01669 -0.0049 1.0000 0.6963
-2.750 -0.3621 0.02676 0.01727 -0.0005 1.0000 0.7169
-2.500 -0.3499 0.02728 0.01776 0.0039 1.0000 0.7376
-2.250 -0.3374 0.02764 0.01808 0.0080 1.0000 0.7577
-2.000 -0.3234 0.02778 0.01817 0.0114 1.0000 0.7752
-1.750 -0.3080 0.02777 0.01810 0.0142 1.0000 0.7902
-1.500 -0.2898 0.02763 0.01789 0.0157 1.0000 0.8025
-1.250 -0.2702 0.02744 0.01764 0.0168 1.0000 0.8121
-1.000 -0.2497 0.02722 0.01737 0.0175 1.0000 0.8195
-0.750 -0.2287 0.02703 0.01712 0.0180 1.0000 0.8266
-0.500 -0.2063 0.02686 0.01691 0.0180 1.0000 0.8332
-0.250 -0.1857 0.02669 0.01671 0.0186 1.0000 0.8389
0.000 -0.1617 0.02661 0.01661 0.0181 1.0000 0.8447
0.250 -0.1311 0.02658 0.01657 0.0165 0.9963 0.8492
0.500 -0.0950 0.02661 0.01659 0.0140 0.9894 0.8531
0.750 -0.0553 0.02672 0.01671 0.0106 0.9823 0.8571
1.000 -0.0166 0.02681 0.01683 0.0074 0.9733 0.8607
1.250 0.0234 0.02687 0.01694 0.0042 0.9628 0.8637
1.500 0.0644 0.02689 0.01703 0.0011 0.9509 0.8662
1.750 0.1065 0.02689 0.01712 -0.0021 0.9381 0.8690
2.000 0.1501 0.02683 0.01717 -0.0054 0.9240 0.8721
2.250 0.1933 0.02668 0.01715 -0.0084 0.9069 0.8750
2.500 0.2407 0.02623 0.01686 -0.0113 0.8818 0.8776
2.750 0.2901 0.02535 0.01614 -0.0134 0.8507 0.8797
3.000 0.3299 0.02453 0.01548 -0.0139 0.8189 0.8824
3.250 0.3633 0.02388 0.01497 -0.0134 0.7828 0.8853
3.500 0.3956 0.02326 0.01445 -0.0127 0.7333 0.8880
3.750 0.4268 0.02274 0.01391 -0.0117 0.6497 0.8908
4.000 0.4584 0.02276 0.01303 -0.0100 0.4698 0.8934
4.250 0.4731 0.02386 0.01325 -0.0077 0.3402 0.8971
4.500 0.4908 0.02496 0.01383 -0.0066 0.2642 0.9010
4.750 0.5128 0.02594 0.01450 -0.0063 0.2206 0.9048
5.000 0.5357 0.02681 0.01518 -0.0059 0.1937 0.9084
5.250 0.5600 0.02760 0.01586 -0.0057 0.1743 0.9123
5.500 0.5864 0.02846 0.01664 -0.0058 0.1597 0.9164
5.750 0.6153 0.02931 0.01756 -0.0062 0.1466 0.9203
6.000 0.6441 0.03018 0.01851 -0.0064 0.1366 0.9241
6.250 0.6727 0.03120 0.01943 -0.0068 0.1282 0.9281
6.500 0.7024 0.03226 0.02073 -0.0073 0.1200 0.9325
6.750 0.7300 0.03342 0.02178 -0.0076 0.1138 0.9371
7.000 0.7575 0.03470 0.02342 -0.0078 0.1072 0.9422
7.250 0.7842 0.03599 0.02480 -0.0081 0.1019 0.9475
7.500 0.8102 0.03759 0.02659 -0.0083 0.0971 0.9530
7.750 0.8352 0.03942 0.02878 -0.0084 0.0925 0.9590
8.000 0.8600 0.04099 0.03049 -0.0088 0.0885 0.9660
8.250 0.8829 0.04322 0.03302 -0.0091 0.0850 0.9756
8.500 0.9021 0.04603 0.03638 -0.0090 0.0821 1.0000
8.750 0.9206 0.04862 0.03928 -0.0091 0.0791 1.0000
9.000 0.9413 0.05072 0.04149 -0.0096 0.0764 1.0000
9.250 0.9534 0.05399 0.04511 -0.0094 0.0744 1.0000
9.500 0.9551 0.05833 0.05005 -0.0087 0.0732 1.0000
9.750 0.9514 0.06287 0.05508 -0.0080 0.0722 1.0000
10.000 0.9416 0.06758 0.06021 -0.0074 0.0713 1.0000
10.250 0.9239 0.07242 0.06537 -0.0070 0.0708 1.0000
10.500 0.8992 0.07815 0.07138 -0.0079 0.0708 1.0000
10.750 0.8670 0.08583 0.07929 -0.0118 0.0712 1.0000
11.000 0.8315 0.09633 0.08995 -0.0195 0.0720 1.0000
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Polar data table (+)
Polar graphs
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