NACA 65(2)-215 (naca652215-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(2)-215 (naca652215-il) Reynolds number: 100,000 Max Cl/Cd: 46.14 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca652215-il-100000.txt Download as CSV file: xf-naca652215-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-215
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4886 0.11043 0.10534 -0.0389 1.0000 0.1661
-11.250 -0.4647 0.10796 0.10283 -0.0370 1.0000 0.1706
-11.000 -0.5009 0.10241 0.09744 -0.0423 1.0000 0.1808
-10.750 -0.4678 0.10032 0.09527 -0.0392 1.0000 0.1853
-10.500 -0.4992 0.09500 0.09011 -0.0434 1.0000 0.1965
-10.250 -0.4676 0.09343 0.08847 -0.0403 1.0000 0.2034
-8.500 -0.8439 0.05407 0.04773 -0.0237 1.0000 0.0895
-8.250 -0.8338 0.04928 0.04275 -0.0230 0.9981 0.0840
-8.000 -0.8136 0.04464 0.03710 -0.0232 0.9917 0.0761
-7.750 -0.7865 0.04113 0.03321 -0.0245 0.9862 0.0751
-7.500 -0.7580 0.03871 0.03032 -0.0257 0.9808 0.0761
-7.250 -0.7292 0.03646 0.02766 -0.0266 0.9752 0.0765
-7.000 -0.6930 0.03427 0.02511 -0.0285 0.9712 0.0769
-6.750 -0.6646 0.03277 0.02331 -0.0289 0.9653 0.0776
-6.500 -0.6284 0.03040 0.02104 -0.0308 0.9613 0.0812
-6.250 -0.5887 0.02914 0.01974 -0.0334 0.9577 0.0859
-6.000 -0.5615 0.02820 0.01870 -0.0333 0.9519 0.0892
-5.750 -0.5308 0.02696 0.01757 -0.0341 0.9472 0.0944
-5.500 -0.4954 0.02608 0.01671 -0.0360 0.9431 0.1044
-5.250 -0.4820 0.02524 0.01602 -0.0341 0.9356 0.1128
-5.000 -0.4577 0.02426 0.01513 -0.0342 0.9300 0.1325
-4.750 -0.4524 0.02237 0.01407 -0.0318 0.9236 0.2252
-4.500 -0.4601 0.02126 0.01495 -0.0250 0.9162 0.6068
-4.250 -0.4276 0.02289 0.01654 -0.0233 0.9122 0.6685
-4.000 -0.4189 0.02374 0.01731 -0.0189 0.9046 0.6922
-3.750 -0.3920 0.02506 0.01858 -0.0166 0.9000 0.7142
-3.500 -0.3561 0.02799 0.02153 -0.0122 0.8973 0.7484
-3.000 -0.3085 0.03096 0.02437 -0.0049 0.8872 0.7923
-2.750 -0.2582 0.03145 0.02468 -0.0081 0.8844 0.7996
-2.500 -0.2282 0.03123 0.02432 -0.0094 0.8810 0.8089
-2.250 -0.2275 0.03138 0.02442 -0.0050 0.8738 0.8162
-2.000 -0.2154 0.03107 0.02402 -0.0034 0.8682 0.8250
-1.750 -0.1658 0.03117 0.02400 -0.0075 0.8658 0.8294
-1.500 -0.1970 0.03087 0.02369 0.0012 0.8577 0.8400
-1.250 -0.1660 0.03094 0.02368 0.0002 0.8534 0.8444
-1.000 -0.1322 0.03087 0.02352 -0.0017 0.8500 0.8498
-0.750 -0.1402 0.03077 0.02339 0.0032 0.8440 0.8576
-0.500 -0.1263 0.03081 0.02340 0.0047 0.8387 0.8636
-0.250 -0.1070 0.03063 0.02314 0.0050 0.8346 0.8708
0.000 -0.0613 0.03081 0.02327 0.0014 0.8323 0.8738
0.250 -0.0832 0.03086 0.02333 0.0084 0.8247 0.8835
0.500 -0.0600 0.03093 0.02337 0.0083 0.8204 0.8890
0.750 -0.0224 0.03115 0.02355 0.0059 0.8175 0.8936
1.000 -0.0250 0.03125 0.02365 0.0097 0.8117 0.9028
1.250 -0.0040 0.03151 0.02391 0.0097 0.8066 0.9089
1.500 0.0215 0.03163 0.02401 0.0093 0.8026 0.9164
1.750 0.0629 0.03199 0.02438 0.0062 0.7989 0.9206
2.000 0.0595 0.03225 0.02466 0.0097 0.7918 0.9315
2.250 0.1036 0.03261 0.02505 0.0060 0.7873 0.9355
2.500 0.1579 0.03292 0.02540 0.0011 0.7841 0.9393
2.750 0.1636 0.03349 0.02602 0.0024 0.7754 0.9494
3.000 0.2128 0.03379 0.02638 -0.0019 0.7705 0.9537
3.250 0.2441 0.03432 0.02697 -0.0041 0.7638 0.9607
3.500 0.2901 0.03478 0.02753 -0.0086 0.7568 0.9650
3.750 0.3532 0.03486 0.02772 -0.0147 0.7529 0.9674
4.000 0.3787 0.03563 0.02859 -0.0168 0.7423 0.9752
4.250 0.4430 0.03541 0.02854 -0.0227 0.7376 0.9771
4.500 0.4728 0.03599 0.02925 -0.0249 0.7262 0.9850
4.750 0.5484 0.03500 0.02847 -0.0313 0.7215 0.9852
5.000 0.5922 0.03482 0.02848 -0.0346 0.7087 0.9910
5.250 0.7339 0.02560 0.01946 -0.0399 0.6867 0.9791
5.500 0.7883 0.02248 0.01644 -0.0407 0.6607 0.9830
5.750 0.8356 0.02042 0.01451 -0.0420 0.6294 0.9879
6.000 0.8698 0.01885 0.01300 -0.0416 0.5631 0.9959
6.250 0.8574 0.01916 0.01216 -0.0340 0.3544 1.0000
6.500 0.8274 0.02026 0.01268 -0.0252 0.2728 1.0000
6.750 0.7971 0.02088 0.01302 -0.0163 0.2311 1.0000
7.000 0.7664 0.02114 0.01313 -0.0073 0.2107 1.0000
7.250 0.7438 0.02272 0.01413 -0.0009 0.1554 1.0000
7.500 0.7399 0.02449 0.01550 0.0024 0.1244 1.0000
7.750 0.7461 0.02600 0.01681 0.0045 0.1086 1.0000
8.000 0.7595 0.02727 0.01798 0.0059 0.0974 1.0000
8.250 0.7799 0.02848 0.01914 0.0067 0.0891 1.0000
8.500 0.8168 0.03011 0.02050 0.0058 0.0823 1.0000
8.750 0.8493 0.03136 0.02189 0.0053 0.0774 1.0000
9.000 0.8877 0.03302 0.02351 0.0037 0.0725 1.0000
9.250 0.9498 0.03658 0.02711 -0.0014 0.0695 1.0000
9.500 0.9773 0.03873 0.02956 -0.0014 0.0685 1.0000
9.750 0.9984 0.04090 0.03207 -0.0008 0.0671 1.0000
10.000 1.0156 0.04320 0.03468 0.0002 0.0657 1.0000
10.250 1.0311 0.04604 0.03788 0.0014 0.0655 1.0000
10.500 1.0423 0.04925 0.04146 0.0029 0.0660 1.0000
10.750 1.0489 0.05273 0.04528 0.0047 0.0669 1.0000
11.000 1.0536 0.05649 0.04933 0.0064 0.0680 1.0000
11.250 1.0621 0.06139 0.05442 0.0071 0.0694 1.0000
11.500 1.0550 0.06343 0.05684 0.0106 0.0716 1.0000
11.750 0.9971 0.06713 0.06116 0.0172 0.0756 1.0000
12.000 0.9719 0.07178 0.06606 0.0190 0.0782 1.0000
12.250 0.9612 0.07680 0.07122 0.0194 0.0805 1.0000
12.500 0.8988 0.08364 0.07850 0.0191 0.0869 1.0000
12.750 0.8429 0.09254 0.08758 0.0152 0.0892 1.0000
13.000 0.7417 0.09077 0.08610 0.0191 0.0802 1.0000
13.250 0.6241 0.11520 0.11077 0.0039 0.0978 1.0000
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Polar data table (+)
Polar graphs
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