NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-34 (naca001034-il) Reynolds number: 200,000 Max Cl/Cd: 45.17 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001034-il-200000.txt Download as CSV file: xf-naca001034-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-34
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4980 0.10438 0.10098 -0.0204 1.0000 0.0457
-10.750 -0.5050 0.09931 0.09594 -0.0224 1.0000 0.0470
-10.500 -0.6424 0.09809 0.09465 -0.0199 1.0000 0.0402
-10.250 -0.6426 0.09401 0.09059 -0.0211 1.0000 0.0410
-10.000 -0.6519 0.08658 0.08318 -0.0273 1.0000 0.0412
-9.750 -0.6712 0.07949 0.07603 -0.0332 1.0000 0.0410
-9.500 -0.6884 0.07480 0.07127 -0.0348 1.0000 0.0410
-9.250 -0.7029 0.07120 0.06760 -0.0341 1.0000 0.0414
-9.000 -0.7148 0.06798 0.06430 -0.0324 1.0000 0.0420
-8.750 -0.7223 0.06466 0.06088 -0.0308 1.0000 0.0429
-8.500 -0.7280 0.06137 0.05746 -0.0289 1.0000 0.0441
-8.250 -0.7326 0.05815 0.05406 -0.0266 1.0000 0.0459
-8.000 -0.7388 0.05639 0.05187 -0.0226 1.0000 0.0494
-6.000 -0.6857 0.03150 0.02452 0.0037 1.0000 0.0374
-5.750 -0.6697 0.02683 0.01951 0.0061 1.0000 0.0325
-5.500 -0.6509 0.02494 0.01733 0.0082 1.0000 0.0334
-5.250 -0.6301 0.02314 0.01527 0.0099 1.0000 0.0340
-5.000 -0.6069 0.02117 0.01308 0.0114 1.0000 0.0330
-4.750 -0.5845 0.01964 0.01138 0.0128 1.0000 0.0333
-4.500 -0.5636 0.01840 0.01005 0.0144 1.0000 0.0345
-4.250 -0.5441 0.01744 0.00902 0.0161 1.0000 0.0366
-4.000 -0.5265 0.01630 0.00785 0.0179 1.0000 0.0408
-3.750 -0.5082 0.01542 0.00696 0.0195 1.0000 0.0453
-3.500 -0.4885 0.01471 0.00615 0.0210 1.0000 0.0526
-3.250 -0.4726 0.01282 0.00513 0.0226 1.0000 0.2142
-3.000 -0.4662 0.01032 0.00488 0.0263 1.0000 0.6743
-2.750 -0.4488 0.01019 0.00515 0.0293 1.0000 0.7893
-2.500 -0.4333 0.01048 0.00561 0.0331 1.0000 0.8606
-2.250 -0.4163 0.01098 0.00613 0.0368 1.0000 0.9046
-2.000 -0.3887 0.01155 0.00661 0.0379 1.0000 0.9331
-1.750 -0.3504 0.01193 0.00683 0.0359 1.0000 0.9475
-1.500 -0.3076 0.01224 0.00701 0.0326 1.0000 0.9582
-1.250 -0.2592 0.01251 0.00717 0.0280 1.0000 0.9656
-1.000 -0.2113 0.01272 0.00726 0.0232 1.0000 0.9721
-0.750 -0.1593 0.01288 0.00735 0.0176 0.9984 0.9769
-0.500 -0.1082 0.01302 0.00743 0.0122 0.9956 0.9826
-0.250 -0.0533 0.01307 0.00744 0.0059 0.9927 0.9854
0.000 0.0000 0.01308 0.00744 0.0000 0.9888 0.9888
0.250 0.0532 0.01307 0.00744 -0.0059 0.9854 0.9927
0.500 0.1082 0.01301 0.00743 -0.0122 0.9826 0.9956
0.750 0.1593 0.01288 0.00735 -0.0176 0.9769 0.9984
1.000 0.2112 0.01272 0.00726 -0.0232 0.9721 1.0000
1.250 0.2591 0.01251 0.00717 -0.0279 0.9656 1.0000
1.500 0.3075 0.01223 0.00701 -0.0326 0.9582 1.0000
1.750 0.3503 0.01192 0.00683 -0.0359 0.9475 1.0000
2.000 0.3886 0.01155 0.00662 -0.0379 0.9332 1.0000
2.250 0.4163 0.01098 0.00613 -0.0368 0.9047 1.0000
2.500 0.4332 0.01047 0.00561 -0.0331 0.8607 1.0000
2.750 0.4487 0.01019 0.00515 -0.0292 0.7890 1.0000
3.000 0.4662 0.01032 0.00487 -0.0262 0.6740 1.0000
3.250 0.4725 0.01283 0.00513 -0.0226 0.2127 1.0000
3.500 0.4885 0.01471 0.00615 -0.0210 0.0525 1.0000
3.750 0.5082 0.01542 0.00696 -0.0195 0.0453 1.0000
4.000 0.5265 0.01629 0.00785 -0.0179 0.0409 1.0000
4.250 0.5440 0.01745 0.00903 -0.0161 0.0367 1.0000
4.500 0.5636 0.01839 0.01005 -0.0144 0.0345 1.0000
4.750 0.5844 0.01964 0.01137 -0.0128 0.0333 1.0000
5.000 0.6068 0.02117 0.01307 -0.0114 0.0330 1.0000
5.250 0.6300 0.02314 0.01527 -0.0099 0.0340 1.0000
5.500 0.6509 0.02495 0.01734 -0.0082 0.0334 1.0000
5.750 0.6697 0.02682 0.01950 -0.0061 0.0325 1.0000
6.750 0.7015 0.02831 0.02327 0.0089 0.0663 1.0000
8.000 0.7390 0.05645 0.05193 0.0225 0.0495 1.0000
8.250 0.7327 0.05816 0.05406 0.0266 0.0459 1.0000
8.500 0.7281 0.06138 0.05747 0.0289 0.0441 1.0000
8.750 0.7225 0.06467 0.06089 0.0308 0.0429 1.0000
9.000 0.7150 0.06800 0.06432 0.0324 0.0419 1.0000
9.250 0.7034 0.07122 0.06762 0.0341 0.0414 1.0000
9.500 0.6890 0.07482 0.07129 0.0348 0.0410 1.0000
9.750 0.6723 0.07945 0.07598 0.0332 0.0409 1.0000
10.000 0.6530 0.08649 0.08308 0.0274 0.0411 1.0000
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Polar data table (+)
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