NACA 0010-65 (naca001065-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-65 (naca001065-il) Reynolds number: 200,000 Max Cl/Cd: 35.69 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001065-il-200000-n5.txt Download as CSV file: xf-naca001065-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-65
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.8122 0.06173 0.05773 -0.0521 1.0000 0.0189
-11.500 -0.8483 0.05615 0.05197 -0.0502 1.0000 0.0187
-11.250 -0.8827 0.05181 0.04740 -0.0455 1.0000 0.0187
-11.000 -0.9144 0.04846 0.04381 -0.0388 1.0000 0.0188
-10.750 -0.9433 0.04536 0.04042 -0.0313 1.0000 0.0191
-10.500 -0.9656 0.04184 0.03649 -0.0245 1.0000 0.0195
-10.250 -0.9797 0.03868 0.03285 -0.0184 1.0000 0.0200
-10.000 -0.9843 0.03632 0.03017 -0.0136 1.0000 0.0205
-9.750 -0.9793 0.03515 0.02888 -0.0102 1.0000 0.0211
-9.500 -0.9706 0.03447 0.02814 -0.0073 1.0000 0.0217
-9.250 -0.9612 0.03374 0.02730 -0.0044 1.0000 0.0227
-9.000 -0.9525 0.03261 0.02597 -0.0013 1.0000 0.0239
-8.750 -0.9434 0.03112 0.02418 0.0018 1.0000 0.0252
-8.500 -0.9324 0.02961 0.02232 0.0047 1.0000 0.0265
-8.250 -0.9196 0.02830 0.02071 0.0072 1.0000 0.0275
-8.000 -0.9060 0.02703 0.01936 0.0094 1.0000 0.0289
-7.750 -0.8905 0.02637 0.01861 0.0114 1.0000 0.0302
-7.500 -0.8741 0.02556 0.01766 0.0133 1.0000 0.0317
-7.250 -0.8559 0.02468 0.01659 0.0149 0.9999 0.0332
-7.000 -0.8294 0.02387 0.01557 0.0148 0.9985 0.0351
-6.750 -0.8026 0.02287 0.01438 0.0147 0.9971 0.0364
-6.500 -0.7762 0.02175 0.01321 0.0145 0.9958 0.0382
-6.250 -0.7483 0.02114 0.01252 0.0140 0.9945 0.0401
-6.000 -0.7222 0.02047 0.01178 0.0140 0.9929 0.0417
-5.750 -0.6958 0.01979 0.01101 0.0140 0.9911 0.0430
-5.500 -0.6685 0.01921 0.01034 0.0138 0.9893 0.0446
-5.250 -0.6403 0.01874 0.00976 0.0135 0.9875 0.0462
-5.000 -0.6138 0.01802 0.00904 0.0133 0.9860 0.0483
-4.750 -0.5867 0.01753 0.00854 0.0131 0.9843 0.0503
-4.500 -0.5618 0.01712 0.00808 0.0135 0.9816 0.0526
-4.250 -0.5351 0.01675 0.00766 0.0134 0.9792 0.0555
-4.000 -0.5072 0.01639 0.00728 0.0132 0.9772 0.0593
-3.750 -0.4781 0.01604 0.00695 0.0126 0.9755 0.0668
-3.500 -0.4509 0.01569 0.00665 0.0124 0.9734 0.0800
-3.250 -0.4275 0.01536 0.00639 0.0131 0.9701 0.0986
-3.000 -0.4012 0.01501 0.00618 0.0130 0.9675 0.1272
-2.750 -0.3735 0.01464 0.00598 0.0126 0.9653 0.1673
-2.500 -0.3456 0.01421 0.00580 0.0122 0.9635 0.2251
-2.250 -0.3249 0.01355 0.00559 0.0131 0.9604 0.3287
-2.000 -0.3232 0.01171 0.00542 0.0184 0.9559 0.6826
-1.750 -0.2786 0.01208 0.00641 0.0163 0.9579 0.8575
-1.500 -0.2458 0.01246 0.00678 0.0158 0.9561 0.8912
-1.250 -0.2099 0.01282 0.00709 0.0145 0.9547 0.9079
-1.000 -0.1712 0.01326 0.00751 0.0126 0.9539 0.9229
-0.750 -0.1210 0.01391 0.00812 0.0084 0.9551 0.9374
-0.500 -0.0730 0.01429 0.00849 0.0043 0.9556 0.9465
-0.250 -0.0373 0.01436 0.00853 0.0024 0.9538 0.9506
0.000 0.0000 0.01436 0.00853 0.0000 0.9521 0.9521
0.250 0.0373 0.01436 0.00853 -0.0024 0.9506 0.9538
0.500 0.0731 0.01429 0.00849 -0.0043 0.9466 0.9557
0.750 0.1210 0.01391 0.00812 -0.0084 0.9374 0.9552
1.000 0.1711 0.01326 0.00751 -0.0126 0.9230 0.9539
1.250 0.2099 0.01281 0.00709 -0.0145 0.9079 0.9547
1.500 0.2459 0.01245 0.00678 -0.0158 0.8912 0.9561
1.750 0.2786 0.01207 0.00640 -0.0163 0.8574 0.9579
2.000 0.3231 0.01171 0.00542 -0.0184 0.6838 0.9559
2.250 0.3248 0.01355 0.00559 -0.0131 0.3286 0.9604
2.500 0.3456 0.01421 0.00579 -0.0122 0.2251 0.9635
2.750 0.3735 0.01464 0.00597 -0.0126 0.1675 0.9653
3.000 0.4012 0.01501 0.00617 -0.0130 0.1272 0.9675
3.250 0.4275 0.01536 0.00639 -0.0131 0.0987 0.9702
3.500 0.4508 0.01569 0.00665 -0.0124 0.0800 0.9735
3.750 0.4781 0.01603 0.00695 -0.0126 0.0669 0.9756
4.000 0.5073 0.01638 0.00727 -0.0132 0.0594 0.9773
4.250 0.5351 0.01675 0.00766 -0.0134 0.0555 0.9793
4.500 0.5617 0.01712 0.00809 -0.0135 0.0526 0.9816
4.750 0.5866 0.01753 0.00854 -0.0131 0.0503 0.9844
5.000 0.6138 0.01802 0.00904 -0.0133 0.0483 0.9861
5.250 0.6403 0.01874 0.00975 -0.0135 0.0462 0.9876
5.500 0.6685 0.01920 0.01033 -0.0138 0.0446 0.9893
5.750 0.6958 0.01979 0.01101 -0.0140 0.0431 0.9912
6.000 0.7222 0.02047 0.01178 -0.0140 0.0417 0.9929
6.250 0.7484 0.02113 0.01252 -0.0140 0.0401 0.9945
6.500 0.7763 0.02175 0.01320 -0.0145 0.0382 0.9959
6.750 0.8026 0.02287 0.01438 -0.0147 0.0364 0.9971
7.000 0.8294 0.02387 0.01556 -0.0148 0.0351 0.9985
7.250 0.8559 0.02467 0.01659 -0.0149 0.0332 0.9999
7.500 0.8740 0.02555 0.01766 -0.0132 0.0317 1.0000
7.750 0.8904 0.02637 0.01861 -0.0113 0.0302 1.0000
8.000 0.9059 0.02703 0.01936 -0.0094 0.0289 1.0000
8.250 0.9195 0.02829 0.02069 -0.0072 0.0275 1.0000
8.500 0.9323 0.02960 0.02231 -0.0046 0.0265 1.0000
8.750 0.9433 0.03112 0.02418 -0.0017 0.0252 1.0000
9.000 0.9524 0.03259 0.02595 0.0014 0.0239 1.0000
9.250 0.9612 0.03372 0.02729 0.0044 0.0227 1.0000
9.500 0.9705 0.03445 0.02813 0.0073 0.0217 1.0000
9.750 0.9792 0.03515 0.02888 0.0102 0.0211 1.0000
10.000 0.9843 0.03631 0.03016 0.0136 0.0205 1.0000
10.250 0.9798 0.03867 0.03284 0.0184 0.0200 1.0000
10.500 0.9656 0.04183 0.03648 0.0245 0.0195 1.0000
10.750 0.9434 0.04536 0.04042 0.0313 0.0191 1.0000
11.000 0.9146 0.04847 0.04382 0.0387 0.0188 1.0000
11.250 0.8827 0.05184 0.04743 0.0455 0.0187 1.0000
11.500 0.8484 0.05620 0.05202 0.0502 0.0187 1.0000
11.750 0.8122 0.06182 0.05783 0.0520 0.0188 1.0000
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Polar data table (+)
Polar graphs
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