NASA SC(2)-0518 AIRFOIL (sc20518-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0518 AIRFOIL (sc20518-il) Reynolds number: 100,000 Max Cl/Cd: 30.15 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20518-il-100000-n5.txt Download as CSV file: xf-sc20518-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0518 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8725 0.09418 0.08647 -0.0601 1.0000 0.0717
-16.250 -0.8856 0.08877 0.08097 -0.0627 1.0000 0.0723
-16.000 -0.8951 0.08413 0.07624 -0.0647 1.0000 0.0730
-15.750 -0.9084 0.07923 0.07120 -0.0668 1.0000 0.0737
-15.500 -0.9221 0.07453 0.06635 -0.0685 1.0000 0.0745
-15.250 -0.9353 0.07017 0.06182 -0.0698 1.0000 0.0753
-15.000 -0.9481 0.06613 0.05757 -0.0708 1.0000 0.0762
-14.750 -0.9599 0.06238 0.05360 -0.0713 1.0000 0.0772
-14.500 -0.9705 0.05892 0.04989 -0.0715 1.0000 0.0782
-14.250 -0.9788 0.05582 0.04654 -0.0714 1.0000 0.0792
-14.000 -0.9656 0.05456 0.04532 -0.0709 1.0000 0.0802
-13.750 -0.9572 0.05305 0.04380 -0.0705 1.0000 0.0813
-13.500 -0.9510 0.05142 0.04212 -0.0699 1.0000 0.0825
-13.250 -0.9463 0.04971 0.04032 -0.0691 1.0000 0.0839
-13.000 -0.9425 0.04797 0.03843 -0.0682 1.0000 0.0853
-12.750 -0.9398 0.04623 0.03649 -0.0670 1.0000 0.0868
-12.500 -0.9284 0.04507 0.03534 -0.0659 1.0000 0.0881
-12.250 -0.9169 0.04409 0.03440 -0.0648 1.0000 0.0894
-12.000 -0.9083 0.04303 0.03333 -0.0633 1.0000 0.0909
-11.750 -0.9008 0.04197 0.03221 -0.0617 1.0000 0.0926
-11.500 -0.8938 0.04091 0.03105 -0.0598 1.0000 0.0944
-11.250 -0.8879 0.03989 0.02990 -0.0578 1.0000 0.0960
-11.000 -0.8753 0.03917 0.02929 -0.0560 1.0000 0.0975
-10.750 -0.8673 0.03845 0.02861 -0.0538 1.0000 0.0992
-10.500 -0.8615 0.03775 0.02791 -0.0513 1.0000 0.1009
-10.250 -0.8574 0.03707 0.02721 -0.0485 1.0000 0.1028
-10.000 -0.8547 0.03645 0.02652 -0.0454 1.0000 0.1047
-9.750 -0.8519 0.03587 0.02595 -0.0421 1.0000 0.1063
-9.500 -0.8508 0.03534 0.02549 -0.0387 1.0000 0.1079
-9.250 -0.8501 0.03479 0.02498 -0.0353 1.0000 0.1096
-9.000 -0.8464 0.03422 0.02441 -0.0324 1.0000 0.1117
-8.750 -0.8180 0.03346 0.02359 -0.0336 0.9962 0.1155
-8.500 -0.7885 0.03269 0.02290 -0.0351 0.9923 0.1190
-8.250 -0.7605 0.03194 0.02218 -0.0363 0.9876 0.1231
-8.000 -0.7313 0.03128 0.02148 -0.0375 0.9827 0.1279
-7.750 -0.7017 0.03047 0.02079 -0.0393 0.9785 0.1330
-7.500 -0.6753 0.02981 0.02013 -0.0401 0.9728 0.1390
-7.250 -0.6487 0.02904 0.01946 -0.0413 0.9673 0.1452
-7.000 -0.6170 0.02838 0.01882 -0.0431 0.9634 0.1536
-6.750 -0.5940 0.02760 0.01816 -0.0437 0.9565 0.1626
-6.500 -0.5656 0.02684 0.01749 -0.0452 0.9510 0.1749
-6.250 -0.5332 0.02600 0.01679 -0.0476 0.9472 0.1924
-6.000 -0.5105 0.02519 0.01613 -0.0483 0.9401 0.2146
-5.750 -0.4808 0.02411 0.01529 -0.0508 0.9347 0.2501
-5.500 -0.4453 0.02281 0.01437 -0.0548 0.9312 0.3074
-5.000 -0.3919 0.02237 0.01495 -0.0550 0.9196 0.4440
-4.750 -0.3617 0.02334 0.01614 -0.0535 0.9157 0.4843
-4.500 -0.3215 0.02330 0.01604 -0.0564 0.9130 0.5175
-4.250 -0.2906 0.02338 0.01606 -0.0574 0.9071 0.5390
-4.000 -0.2583 0.02347 0.01607 -0.0587 0.9011 0.5567
-3.750 -0.2196 0.02342 0.01593 -0.0613 0.8972 0.5728
-3.500 -0.1874 0.02410 0.01661 -0.0605 0.8940 0.5791
-3.250 -0.1563 0.02399 0.01642 -0.0622 0.8875 0.5928
-3.000 -0.1344 0.02497 0.01746 -0.0590 0.8812 0.5985
-2.750 -0.0983 0.02518 0.01761 -0.0606 0.8773 0.6131
-2.500 -0.0699 0.02615 0.01864 -0.0582 0.8741 0.6178
-2.250 -0.0511 0.02664 0.01914 -0.0559 0.8659 0.6240
-2.000 -0.0166 0.02623 0.01866 -0.0584 0.8606 0.6339
-1.750 0.0124 0.02655 0.01900 -0.0574 0.8565 0.6367
-1.500 0.0447 0.02675 0.01921 -0.0571 0.8535 0.6405
-1.250 0.0629 0.02691 0.01938 -0.0556 0.8446 0.6454
-1.000 0.1032 0.02618 0.01859 -0.0600 0.8397 0.6542
-0.750 0.1339 0.02620 0.01862 -0.0596 0.8356 0.6562
-0.500 0.1623 0.02621 0.01866 -0.0592 0.8305 0.6585
-0.250 0.1835 0.02627 0.01875 -0.0579 0.8214 0.6611
0.000 0.2192 0.02592 0.01841 -0.0589 0.8154 0.6641
0.250 0.2487 0.02555 0.01804 -0.0592 0.8036 0.6680
0.500 0.2938 0.02464 0.01706 -0.0624 0.7929 0.6728
0.750 0.3255 0.02409 0.01649 -0.0636 0.7776 0.6762
1.000 0.3538 0.02376 0.01617 -0.0629 0.7634 0.6777
1.250 0.3848 0.02339 0.01578 -0.0627 0.7488 0.6793
1.500 0.4119 0.02316 0.01555 -0.0620 0.7326 0.6813
1.750 0.4381 0.02298 0.01540 -0.0614 0.7152 0.6837
2.000 0.4664 0.02278 0.01519 -0.0612 0.6973 0.6864
2.250 0.4962 0.02255 0.01495 -0.0614 0.6770 0.6894
2.500 0.5278 0.02228 0.01462 -0.0622 0.6509 0.6929
2.750 0.5627 0.02198 0.01419 -0.0640 0.6149 0.6969
3.000 0.5881 0.02192 0.01402 -0.0633 0.5681 0.6987
3.250 0.6096 0.02208 0.01388 -0.0616 0.5029 0.7003
3.500 0.6262 0.02260 0.01394 -0.0593 0.4249 0.7022
3.750 0.6415 0.02329 0.01423 -0.0571 0.3610 0.7043
4.000 0.6595 0.02392 0.01457 -0.0557 0.3111 0.7064
4.250 0.6794 0.02452 0.01492 -0.0548 0.2719 0.7086
4.500 0.7011 0.02505 0.01528 -0.0543 0.2403 0.7109
4.750 0.7243 0.02557 0.01564 -0.0541 0.2168 0.7134
5.000 0.7492 0.02607 0.01602 -0.0543 0.1979 0.7161
5.250 0.7757 0.02660 0.01642 -0.0550 0.1831 0.7190
5.750 0.8165 0.02766 0.01741 -0.0529 0.1627 0.7229
6.000 0.8347 0.02826 0.01796 -0.0515 0.1553 0.7250
6.250 0.8548 0.02880 0.01853 -0.0503 0.1481 0.7272
6.500 0.8738 0.02944 0.01910 -0.0492 0.1425 0.7295
6.750 0.8955 0.02998 0.01969 -0.0486 0.1365 0.7319
7.000 0.9160 0.03062 0.02030 -0.0479 0.1317 0.7345
7.250 0.9393 0.03127 0.02097 -0.0477 0.1270 0.7373
7.500 0.9633 0.03195 0.02163 -0.0479 0.1225 0.7403
7.750 0.9850 0.03274 0.02234 -0.0476 0.1190 0.7428
8.000 1.0044 0.03341 0.02313 -0.0464 0.1152 0.7446
8.250 1.0230 0.03416 0.02393 -0.0452 0.1119 0.7468
8.500 1.0416 0.03497 0.02471 -0.0441 0.1090 0.7494
8.750 1.0621 0.03582 0.02564 -0.0434 0.1060 0.7524
9.000 1.0833 0.03669 0.02659 -0.0429 0.1030 0.7556
9.250 1.1049 0.03760 0.02750 -0.0427 0.1003 0.7589
9.500 1.1285 0.03861 0.02843 -0.0429 0.0981 0.7622
9.750 1.1475 0.03962 0.02964 -0.0421 0.0954 0.7646
10.000 1.1639 0.04061 0.03075 -0.0409 0.0931 0.7668
10.250 1.1805 0.04162 0.03181 -0.0398 0.0911 0.7694
10.500 1.1983 0.04265 0.03280 -0.0390 0.0895 0.7722
10.750 1.2141 0.04395 0.03430 -0.0381 0.0874 0.7754
11.000 1.2298 0.04529 0.03580 -0.0373 0.0853 0.7791
11.250 1.2468 0.04664 0.03723 -0.0371 0.0835 0.7832
11.500 1.2592 0.04784 0.03848 -0.0357 0.0822 0.7859
11.750 1.2739 0.04902 0.03965 -0.0346 0.0811 0.7889
12.000 1.2810 0.05088 0.04179 -0.0331 0.0795 0.7921
12.250 1.2881 0.05280 0.04393 -0.0319 0.0780 0.7955
12.500 1.2963 0.05469 0.04598 -0.0311 0.0766 0.7991
12.750 1.3056 0.05656 0.04796 -0.0307 0.0754 0.8028
13.000 1.3126 0.05820 0.04967 -0.0294 0.0744 0.8054
13.250 1.3229 0.05976 0.05124 -0.0285 0.0735 0.8086
13.500 1.3191 0.06271 0.05447 -0.0275 0.0726 0.8117
13.750 1.3113 0.06620 0.05828 -0.0268 0.0717 0.8149
14.000 1.3026 0.06996 0.06233 -0.0266 0.0708 0.8183
14.250 1.2927 0.07395 0.06657 -0.0267 0.0700 0.8215
14.500 1.2800 0.07805 0.07091 -0.0268 0.0693 0.8241
14.750 1.2667 0.08246 0.07555 -0.0274 0.0686 0.8269
15.000 1.2535 0.08714 0.08042 -0.0287 0.0680 0.8300
15.250 1.2406 0.09213 0.08559 -0.0305 0.0675 0.8332
15.500 1.2306 0.09712 0.09071 -0.0327 0.0669 0.8365
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Polar data table (+)
Polar graphs
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