NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Reynolds number: 200,000 Max Cl/Cd: 67.14 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001034a08cli02-il-200000.txt Download as CSV file: xf-naca001034a08cli02-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-34 a=0.8 c(li)=0.2
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3928 0.08858 0.08534 -0.0393 1.0000 0.0381
-9.500 -0.3995 0.08435 0.08114 -0.0402 1.0000 0.0389
-9.250 -0.4077 0.08001 0.07684 -0.0411 1.0000 0.0396
-9.000 -0.4180 0.07551 0.07239 -0.0422 1.0000 0.0401
-8.750 -0.4309 0.07093 0.06787 -0.0433 1.0000 0.0403
-8.500 -0.4476 0.06632 0.06330 -0.0445 1.0000 0.0400
-8.250 -0.4707 0.06218 0.05919 -0.0451 1.0000 0.0391
-8.000 -0.4982 0.05949 0.05652 -0.0426 1.0000 0.0383
-7.750 -0.5251 0.05735 0.05438 -0.0385 1.0000 0.0377
-7.500 -0.5450 0.05452 0.05151 -0.0355 1.0000 0.0377
-7.250 -0.5610 0.05148 0.04839 -0.0326 1.0000 0.0380
-7.000 -0.5732 0.04829 0.04510 -0.0299 1.0000 0.0388
-6.750 -0.5817 0.04512 0.04176 -0.0273 1.0000 0.0401
-6.500 -0.5875 0.04462 0.04078 -0.0235 1.0000 0.0430
-6.250 -0.5885 0.04332 0.03912 -0.0201 1.0000 0.0435
-6.000 -0.6115 0.04640 0.04164 -0.0203 1.0000 0.0450
-5.750 -0.6014 0.04313 0.03840 -0.0190 1.0000 0.0470
-5.500 -0.5900 0.04071 0.03585 -0.0174 1.0000 0.0503
-5.250 -0.5797 0.03875 0.03323 -0.0147 1.0000 0.0583
-5.000 -0.5642 0.03556 0.03008 -0.0140 1.0000 0.0620
-4.750 -0.5493 0.03348 0.02764 -0.0125 1.0000 0.0731
-4.500 -0.5293 0.03138 0.02534 -0.0121 0.9994 0.0866
-4.250 -0.4989 0.02905 0.02290 -0.0137 0.9969 0.1039
-4.000 -0.4492 0.02356 0.01593 -0.0098 0.9969 0.0316
-3.750 -0.4121 0.02252 0.01465 -0.0110 0.9945 0.0303
-3.500 -0.3785 0.02040 0.01235 -0.0118 0.9925 0.0297
-3.250 -0.3449 0.01863 0.01048 -0.0127 0.9904 0.0305
-3.000 -0.3116 0.01707 0.00894 -0.0141 0.9883 0.0372
-2.750 -0.2767 0.01631 0.00801 -0.0157 0.9853 0.0433
-2.500 -0.2478 0.01358 0.00682 -0.0172 0.9835 0.3836
-2.250 -0.2276 0.01217 0.00714 -0.0148 0.9810 0.7945
-2.000 -0.2008 0.01243 0.00768 -0.0124 0.9782 0.9207
-1.750 -0.1423 0.01303 0.00808 -0.0177 0.9791 0.9763
-1.500 -0.0838 0.01326 0.00810 -0.0245 0.9788 0.9870
-1.250 -0.0254 0.01342 0.00809 -0.0315 0.9783 0.9954
-1.000 0.0233 0.01345 0.00798 -0.0366 0.9753 1.0000
-0.750 0.0592 0.01339 0.00783 -0.0392 0.9692 1.0000
-0.500 0.0950 0.01335 0.00773 -0.0416 0.9633 1.0000
-0.250 0.1321 0.01331 0.00761 -0.0442 0.9573 1.0000
0.000 0.1780 0.01327 0.00753 -0.0485 0.9543 1.0000
0.250 0.2056 0.01321 0.00745 -0.0490 0.9453 1.0000
0.500 0.2518 0.01312 0.00736 -0.0532 0.9421 1.0000
0.750 0.2825 0.01307 0.00731 -0.0542 0.9341 1.0000
1.000 0.3282 0.01292 0.00720 -0.0582 0.9304 1.0000
1.250 0.3754 0.01271 0.00706 -0.0624 0.9276 1.0000
1.500 0.4010 0.01262 0.00701 -0.0621 0.9177 1.0000
1.750 0.4341 0.01245 0.00691 -0.0632 0.9103 1.0000
2.000 0.4694 0.01219 0.00675 -0.0646 0.9033 1.0000
2.250 0.4969 0.01199 0.00664 -0.0644 0.8932 1.0000
2.500 0.5289 0.01167 0.00642 -0.0648 0.8845 1.0000
2.750 0.5590 0.01135 0.00624 -0.0648 0.8748 1.0000
3.000 0.5849 0.01103 0.00602 -0.0638 0.8615 1.0000
3.250 0.6083 0.01038 0.00541 -0.0615 0.8347 1.0000
3.500 0.6291 0.00991 0.00493 -0.0587 0.7936 1.0000
3.750 0.6502 0.00973 0.00465 -0.0563 0.7354 1.0000
4.000 0.6687 0.00996 0.00459 -0.0536 0.6432 1.0000
4.250 0.6687 0.01127 0.00480 -0.0476 0.4367 1.0000
4.500 0.6526 0.01436 0.00590 -0.0402 0.0839 1.0000
4.750 0.6642 0.01562 0.00698 -0.0371 0.0459 1.0000
5.000 0.6761 0.01684 0.00826 -0.0339 0.0378 1.0000
5.250 0.6917 0.01784 0.00935 -0.0314 0.0333 1.0000
5.500 0.7066 0.01916 0.01065 -0.0291 0.0280 1.0000
5.750 0.7269 0.02182 0.01334 -0.0275 0.0262 1.0000
6.000 0.7532 0.02373 0.01541 -0.0267 0.0257 1.0000
6.250 0.7805 0.02645 0.01836 -0.0260 0.0258 1.0000
6.500 0.8027 0.02773 0.01993 -0.0245 0.0241 1.0000
6.750 0.8244 0.03065 0.02327 -0.0228 0.0243 1.0000
7.000 0.8484 0.03300 0.02585 -0.0211 0.0318 1.0000
12.000 0.5776 0.11679 0.11358 -0.0003 0.0437 1.0000
12.250 0.5740 0.12037 0.11715 -0.0012 0.0424 1.0000
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Polar data table (+)
Polar graphs
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