NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-34 (naca001034-il) Reynolds number: 500,000 Max Cl/Cd: 46.49 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001034-il-500000.txt Download as CSV file: xf-naca001034-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6495 0.08696 0.08477 -0.0216 1.0000 0.0149
-10.000 -0.6651 0.07735 0.07513 -0.0305 1.0000 0.0142
-9.750 -0.6848 0.07091 0.06860 -0.0348 1.0000 0.0138
-9.500 -0.7038 0.06625 0.06384 -0.0357 1.0000 0.0138
-9.250 -0.7216 0.06262 0.06011 -0.0339 1.0000 0.0138
-9.000 -0.7338 0.05911 0.05646 -0.0316 1.0000 0.0141
-8.750 -0.7407 0.05556 0.05274 -0.0292 1.0000 0.0147
-8.500 -0.7282 0.05446 0.05138 -0.0265 1.0000 0.0167
-8.250 -0.7297 0.05240 0.04911 -0.0230 1.0000 0.0169
-8.000 -0.7324 0.04985 0.04634 -0.0193 1.0000 0.0170
-7.750 -0.7342 0.04727 0.04354 -0.0154 1.0000 0.0170
-5.750 -0.6847 0.02116 0.01526 0.0116 0.9991 0.0143
-5.500 -0.6549 0.01858 0.01237 0.0116 0.9978 0.0140
-5.250 -0.6236 0.01702 0.01065 0.0109 0.9964 0.0147
-5.000 -0.5919 0.01580 0.00933 0.0100 0.9949 0.0155
-4.750 -0.5583 0.01549 0.00892 0.0086 0.9930 0.0169
-4.500 -0.5318 0.01374 0.00707 0.0086 0.9904 0.0180
-4.250 -0.5026 0.01259 0.00583 0.0080 0.9876 0.0202
-4.000 -0.4693 0.01200 0.00519 0.0065 0.9854 0.0231
-3.750 -0.4342 0.01160 0.00473 0.0047 0.9836 0.0271
-3.500 -0.4022 0.01088 0.00396 0.0036 0.9812 0.0443
-3.250 -0.3838 0.00883 0.00328 0.0041 0.9762 0.3526
-3.000 -0.3575 0.00769 0.00300 0.0036 0.9729 0.5575
-2.750 -0.3260 0.00714 0.00288 0.0026 0.9707 0.6698
-2.500 -0.2927 0.00681 0.00288 0.0015 0.9691 0.7588
-2.250 -0.2669 0.00669 0.00286 0.0021 0.9631 0.8013
-2.000 -0.2343 0.00662 0.00283 0.0012 0.9597 0.8291
-1.750 -0.1999 0.00655 0.00275 -0.0001 0.9569 0.8450
-1.500 -0.1701 0.00650 0.00269 -0.0004 0.9519 0.8582
-1.250 -0.1407 0.00644 0.00264 -0.0006 0.9463 0.8702
-1.000 -0.1088 0.00638 0.00258 -0.0013 0.9423 0.8801
-0.750 -0.0830 0.00636 0.00256 -0.0007 0.9348 0.8901
-0.500 -0.0544 0.00632 0.00251 -0.0007 0.9293 0.8996
-0.250 -0.0273 0.00632 0.00252 -0.0003 0.9219 0.9070
0.000 0.0000 0.00630 0.00248 0.0000 0.9153 0.9153
0.250 0.0274 0.00632 0.00252 0.0003 0.9070 0.9219
0.500 0.0544 0.00632 0.00251 0.0007 0.8996 0.9293
0.750 0.0830 0.00636 0.00256 0.0007 0.8901 0.9348
1.000 0.1088 0.00638 0.00258 0.0013 0.8802 0.9423
1.250 0.1407 0.00644 0.00264 0.0006 0.8702 0.9463
1.500 0.1701 0.00650 0.00269 0.0004 0.8581 0.9519
1.750 0.1999 0.00655 0.00275 0.0001 0.8450 0.9569
2.000 0.2343 0.00662 0.00283 -0.0012 0.8291 0.9597
2.250 0.2669 0.00669 0.00286 -0.0021 0.8012 0.9631
2.500 0.2927 0.00681 0.00286 -0.0015 0.7589 0.9691
2.750 0.3260 0.00714 0.00288 -0.0026 0.6702 0.9707
3.000 0.3575 0.00769 0.00300 -0.0036 0.5577 0.9729
3.250 0.3837 0.00884 0.00328 -0.0041 0.3519 0.9762
3.500 0.4021 0.01088 0.00396 -0.0036 0.0442 0.9812
3.750 0.4341 0.01161 0.00474 -0.0046 0.0271 0.9836
4.000 0.4693 0.01200 0.00519 -0.0065 0.0231 0.9854
4.250 0.5026 0.01258 0.00583 -0.0080 0.0203 0.9876
4.500 0.5319 0.01373 0.00706 -0.0086 0.0180 0.9904
4.750 0.5580 0.01556 0.00899 -0.0085 0.0170 0.9930
5.000 0.5919 0.01580 0.00933 -0.0100 0.0155 0.9949
5.250 0.6237 0.01702 0.01065 -0.0109 0.0147 0.9964
5.500 0.6548 0.01858 0.01237 -0.0116 0.0141 0.9978
5.750 0.6846 0.02115 0.01525 -0.0116 0.0143 0.9991
6.000 0.6661 0.01439 0.00947 -0.0026 0.0242 0.9962
6.250 0.6932 0.01659 0.01198 -0.0027 0.0225 0.9983
6.500 0.7148 0.01902 0.01469 -0.0023 0.0210 1.0000
6.750 0.7214 0.02076 0.01662 0.0009 0.0201 1.0000
7.000 0.7274 0.02239 0.01834 0.0038 0.0192 1.0000
7.250 0.7325 0.02436 0.02035 0.0066 0.0184 1.0000
7.500 0.7182 0.02993 0.02616 0.0114 0.0174 1.0000
7.750 0.7342 0.04726 0.04354 0.0155 0.0170 1.0000
8.000 0.7324 0.04984 0.04633 0.0193 0.0170 1.0000
8.250 0.7297 0.05239 0.04909 0.0230 0.0169 1.0000
8.500 0.7280 0.05451 0.05143 0.0264 0.0167 1.0000
8.750 0.7410 0.05556 0.05274 0.0291 0.0147 1.0000
9.000 0.7341 0.05912 0.05647 0.0315 0.0141 1.0000
9.250 0.7219 0.06264 0.06013 0.0338 0.0138 1.0000
9.500 0.7042 0.06628 0.06387 0.0356 0.0137 1.0000
9.750 0.6852 0.07096 0.06866 0.0347 0.0138 1.0000
10.000 0.6656 0.07744 0.07522 0.0303 0.0142 1.0000
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Polar data table (+)
Polar graphs
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