NASA SC(2)-0706 AIRFOIL (sc20706-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0706 AIRFOIL (sc20706-il) Reynolds number: 200,000 Max Cl/Cd: 40.6 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20706-il-200000.txt Download as CSV file: xf-sc20706-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0706 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5869 0.08833 0.08473 -0.0161 1.0000 0.0423
-9.000 -0.5937 0.08451 0.08097 -0.0174 1.0000 0.0433
-8.750 -0.5994 0.07963 0.07617 -0.0216 1.0000 0.0443
-8.500 -0.6000 0.07245 0.06893 -0.0320 1.0000 0.0451
-8.250 -0.5961 0.06706 0.06317 -0.0405 1.0000 0.0464
-8.000 -0.5914 0.06019 0.05603 -0.0447 1.0000 0.0471
-7.750 -0.5833 0.05539 0.05147 -0.0438 1.0000 0.0491
-7.500 -0.5693 0.05300 0.04908 -0.0438 1.0000 0.0530
-7.250 -0.5428 0.04677 0.04204 -0.0513 1.0000 0.0608
-7.000 -0.5255 0.04288 0.03829 -0.0516 1.0000 0.0630
-6.750 -0.5019 0.03979 0.03503 -0.0531 1.0000 0.0676
-6.500 -0.4712 0.03557 0.03033 -0.0568 1.0000 0.0766
-6.250 -0.4236 0.02710 0.02075 -0.0600 1.0000 0.0429
-6.000 -0.3835 0.02224 0.01494 -0.0620 1.0000 0.0355
-5.750 -0.3540 0.02022 0.01279 -0.0631 1.0000 0.0388
-5.500 -0.3232 0.01842 0.01073 -0.0636 1.0000 0.0399
-5.250 -0.2924 0.01682 0.00894 -0.0640 1.0000 0.0412
-5.000 -0.2616 0.01558 0.00756 -0.0645 1.0000 0.0443
-4.750 -0.2287 0.01428 0.00627 -0.0659 1.0000 0.0513
-4.500 -0.1949 0.01336 0.00532 -0.0674 1.0000 0.0617
-4.250 -0.1587 0.01244 0.00447 -0.0697 1.0000 0.0873
-4.000 -0.0997 0.00978 0.00400 -0.0785 1.0000 0.6058
-3.750 -0.0736 0.00982 0.00411 -0.0777 1.0000 0.6632
-3.500 -0.0492 0.00995 0.00427 -0.0765 1.0000 0.7030
-3.250 -0.0272 0.01015 0.00452 -0.0746 1.0000 0.7348
-3.000 -0.0035 0.01032 0.00467 -0.0733 1.0000 0.7574
-2.750 0.0168 0.01049 0.00486 -0.0710 1.0000 0.7765
-2.500 0.0386 0.01063 0.00501 -0.0693 1.0000 0.7933
-2.250 0.0607 0.01074 0.00513 -0.0677 1.0000 0.8082
-2.000 0.0830 0.01081 0.00522 -0.0661 1.0000 0.8214
-1.750 0.1066 0.01084 0.00526 -0.0651 1.0000 0.8322
-1.500 0.1327 0.01085 0.00528 -0.0647 1.0000 0.8420
-1.250 0.1581 0.01085 0.00532 -0.0642 1.0000 0.8512
-1.000 0.1824 0.01084 0.00535 -0.0634 1.0000 0.8597
-0.750 0.2087 0.01085 0.00541 -0.0632 1.0000 0.8690
-0.500 0.2334 0.01085 0.00549 -0.0626 1.0000 0.8781
-0.250 0.2576 0.01084 0.00556 -0.0618 1.0000 0.8868
0.000 0.2837 0.01086 0.00566 -0.0616 1.0000 0.8961
0.250 0.3084 0.01086 0.00578 -0.0611 1.0000 0.9059
0.500 0.3319 0.01084 0.00591 -0.0602 1.0000 0.9159
0.750 0.3557 0.01083 0.00604 -0.0595 1.0000 0.9270
1.000 0.4147 0.01039 0.00583 -0.0658 0.9766 0.9330
1.250 0.4896 0.01206 0.00455 -0.0732 0.1946 0.9310
1.500 0.5060 0.01340 0.00524 -0.0709 0.0743 0.9419
1.750 0.5265 0.01396 0.00576 -0.0692 0.0583 0.9542
2.000 0.5471 0.01473 0.00658 -0.0675 0.0511 0.9693
2.250 0.5744 0.01574 0.00755 -0.0674 0.0440 1.0000
2.500 0.6064 0.01724 0.00914 -0.0682 0.0399 1.0000
2.750 0.6393 0.01893 0.01102 -0.0689 0.0380 1.0000
3.000 0.6725 0.02113 0.01348 -0.0695 0.0378 1.0000
3.250 0.7046 0.02406 0.01680 -0.0697 0.0395 1.0000
3.500 0.7351 0.02651 0.01966 -0.0697 0.0382 1.0000
4.000 0.7952 0.03748 0.03208 -0.0663 0.0717 1.0000
4.250 0.8165 0.04103 0.03610 -0.0656 0.0635 1.0000
4.500 0.8387 0.04403 0.03933 -0.0654 0.0590 1.0000
4.750 0.8587 0.04813 0.04337 -0.0658 0.0567 1.0000
5.000 0.8732 0.05262 0.04861 -0.0643 0.0513 1.0000
5.250 0.8898 0.05653 0.05281 -0.0640 0.0476 1.0000
5.500 0.9043 0.06008 0.05645 -0.0637 0.0453 1.0000
5.750 0.9161 0.06538 0.06153 -0.0641 0.0432 1.0000
6.000 0.9150 0.07274 0.06922 -0.0637 0.0423 1.0000
6.250 0.9241 0.07647 0.07356 -0.0649 0.0391 1.0000
6.500 0.9271 0.08193 0.07918 -0.0665 0.0374 1.0000
6.750 0.9269 0.08732 0.08467 -0.0685 0.0363 1.0000
7.000 0.9239 0.09272 0.09013 -0.0710 0.0355 1.0000
7.250 0.9160 0.09790 0.09534 -0.0736 0.0351 1.0000
7.500 0.9084 0.10380 0.10125 -0.0786 0.0348 1.0000
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Polar data table (+)
Polar graphs
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