NASA SC(2)-0710 AIRFOIL (sc20710-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0710 AIRFOIL (sc20710-il) Reynolds number: 100,000 Max Cl/Cd: 33.79 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20710-il-100000-n5.txt Download as CSV file: xf-sc20710-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0710 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6304 0.09136 0.08552 -0.0406 1.0000 0.0354
-11.750 -0.6553 0.08075 0.07491 -0.0472 1.0000 0.0351
-11.500 -0.6843 0.07234 0.06646 -0.0525 1.0000 0.0348
-11.250 -0.7124 0.06637 0.06040 -0.0549 1.0000 0.0346
-11.000 -0.7404 0.06206 0.05600 -0.0547 1.0000 0.0344
-10.750 -0.7652 0.05816 0.05198 -0.0539 1.0000 0.0344
-10.500 -0.7821 0.05370 0.04725 -0.0545 1.0000 0.0345
-10.250 -0.7917 0.04911 0.04223 -0.0548 1.0000 0.0350
-10.000 -0.7926 0.04458 0.03712 -0.0553 1.0000 0.0358
-9.750 -0.7794 0.04261 0.03509 -0.0551 1.0000 0.0366
-9.500 -0.7646 0.04060 0.03290 -0.0551 1.0000 0.0376
-9.250 -0.7482 0.03824 0.03027 -0.0553 1.0000 0.0385
-9.000 -0.7297 0.03570 0.02739 -0.0555 1.0000 0.0395
-8.750 -0.7090 0.03331 0.02463 -0.0558 1.0000 0.0408
-8.500 -0.6868 0.03113 0.02205 -0.0559 1.0000 0.0423
-8.250 -0.6642 0.02951 0.02023 -0.0559 1.0000 0.0443
-8.000 -0.6412 0.02848 0.01917 -0.0559 1.0000 0.0465
-7.750 -0.6172 0.02729 0.01781 -0.0558 1.0000 0.0493
-7.500 -0.5928 0.02605 0.01632 -0.0555 1.0000 0.0518
-7.250 -0.5688 0.02496 0.01526 -0.0556 1.0000 0.0549
-7.000 -0.5438 0.02415 0.01441 -0.0556 1.0000 0.0588
-6.750 -0.5184 0.02334 0.01343 -0.0554 1.0000 0.0629
-6.500 -0.4927 0.02245 0.01263 -0.0557 1.0000 0.0675
-6.250 -0.4663 0.02175 0.01188 -0.0559 1.0000 0.0727
-6.000 -0.4390 0.02100 0.01116 -0.0564 1.0000 0.0788
-5.750 -0.4108 0.02040 0.01055 -0.0570 1.0000 0.0860
-5.500 -0.3814 0.01975 0.00993 -0.0580 1.0000 0.0948
-5.250 -0.3513 0.01918 0.00940 -0.0590 1.0000 0.1077
-5.000 -0.3201 0.01861 0.00893 -0.0603 1.0000 0.1262
-4.750 -0.2875 0.01798 0.00851 -0.0621 1.0000 0.1643
-4.500 -0.2478 0.01690 0.00807 -0.0661 1.0000 0.2808
-4.250 -0.2134 0.01604 0.00843 -0.0681 1.0000 0.4999
-4.000 -0.1952 0.01644 0.00907 -0.0652 1.0000 0.5819
-3.750 -0.1716 0.01679 0.00939 -0.0640 1.0000 0.6211
-3.500 -0.1476 0.01715 0.00970 -0.0630 1.0000 0.6490
-3.250 -0.1278 0.01763 0.01016 -0.0608 1.0000 0.6697
-3.000 -0.1087 0.01813 0.01063 -0.0585 1.0000 0.6879
-2.750 -0.0912 0.01866 0.01116 -0.0557 1.0000 0.7052
-2.500 -0.0746 0.01914 0.01165 -0.0528 1.0000 0.7195
-2.250 -0.0543 0.01947 0.01196 -0.0510 1.0000 0.7312
-2.000 -0.0279 0.01968 0.01213 -0.0509 1.0000 0.7422
-1.750 -0.0090 0.01988 0.01234 -0.0489 1.0000 0.7479
-1.500 0.0165 0.02003 0.01248 -0.0487 1.0000 0.7548
-1.250 0.0433 0.02015 0.01259 -0.0490 1.0000 0.7605
-1.000 0.0765 0.02028 0.01273 -0.0502 0.9960 0.7647
-0.750 0.1123 0.02041 0.01286 -0.0522 0.9924 0.7693
-0.500 0.1514 0.02051 0.01297 -0.0552 0.9885 0.7743
-0.250 0.1881 0.02061 0.01313 -0.0571 0.9840 0.7770
0.000 0.2241 0.02062 0.01320 -0.0589 0.9763 0.7799
0.250 0.2663 0.02058 0.01323 -0.0619 0.9680 0.7830
0.500 0.3138 0.02043 0.01317 -0.0659 0.9585 0.7860
0.750 0.3628 0.01988 0.01272 -0.0696 0.9380 0.7890
1.000 0.4162 0.01887 0.01182 -0.0732 0.9104 0.7910
1.250 0.4561 0.01803 0.01111 -0.0741 0.8805 0.7930
1.500 0.4863 0.01754 0.01073 -0.0735 0.8429 0.7957
1.750 0.5586 0.01653 0.00912 -0.0792 0.6403 0.7974
2.000 0.5796 0.01819 0.00931 -0.0776 0.3670 0.8006
2.250 0.6028 0.01950 0.00977 -0.0774 0.2127 0.8040
2.500 0.6268 0.02034 0.01023 -0.0770 0.1476 0.8065
2.750 0.6505 0.02099 0.01073 -0.0763 0.1189 0.8088
3.000 0.6752 0.02161 0.01130 -0.0758 0.1032 0.8112
3.250 0.7004 0.02229 0.01194 -0.0754 0.0924 0.8140
3.500 0.7262 0.02302 0.01263 -0.0753 0.0834 0.8171
3.750 0.7540 0.02377 0.01347 -0.0755 0.0767 0.8204
4.000 0.7768 0.02447 0.01415 -0.0746 0.0710 0.8228
4.250 0.8011 0.02529 0.01505 -0.0739 0.0661 0.8256
4.500 0.8266 0.02609 0.01591 -0.0736 0.0614 0.8286
4.750 0.8526 0.02716 0.01693 -0.0736 0.0573 0.8318
5.000 0.8813 0.02822 0.01818 -0.0738 0.0535 0.8348
5.250 0.9061 0.02910 0.01911 -0.0734 0.0500 0.8372
5.500 0.9306 0.03034 0.02037 -0.0730 0.0474 0.8396
5.750 0.9569 0.03184 0.02217 -0.0726 0.0453 0.8422
6.000 0.9826 0.03337 0.02393 -0.0724 0.0431 0.8451
6.250 1.0076 0.03464 0.02535 -0.0722 0.0410 0.8482
6.500 1.0307 0.03615 0.02690 -0.0719 0.0393 0.8512
6.750 1.0506 0.03835 0.02963 -0.0705 0.0378 0.8541
7.000 1.0689 0.04092 0.03266 -0.0690 0.0368 0.8571
7.250 1.0853 0.04372 0.03591 -0.0675 0.0359 0.8602
7.500 1.0994 0.04676 0.03939 -0.0660 0.0352 0.8632
7.750 1.1094 0.04988 0.04293 -0.0640 0.0346 0.8661
8.000 1.1178 0.05256 0.04592 -0.0619 0.0340 0.8691
8.250 1.1270 0.05490 0.04848 -0.0601 0.0334 0.8725
8.500 1.1354 0.05727 0.05099 -0.0586 0.0327 0.8760
8.750 1.1288 0.06156 0.05572 -0.0558 0.0323 0.8791
9.000 1.1102 0.06643 0.06109 -0.0520 0.0320 0.8819
9.250 1.0865 0.07085 0.06586 -0.0483 0.0319 0.8852
9.500 1.0622 0.07571 0.07099 -0.0461 0.0319 0.8887
9.750 1.0362 0.08146 0.07698 -0.0461 0.0319 0.8919
10.000 1.0102 0.08824 0.08396 -0.0485 0.0321 0.8946
10.250 0.9851 0.09661 0.09248 -0.0538 0.0323 0.8971
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Polar data table (+)
Polar graphs
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