NACA 65(1)-212 a=0.6 (naca651212a06-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(1)-212 a=0.6 (naca651212a06-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.74 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca651212a06-il-1000000-n5.txt Download as CSV file: xf-naca651212a06-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-212 a=0.6
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -1.0513 0.06033 0.05803 -0.0482 1.0000 0.0059
-15.750 -1.0746 0.05335 0.05087 -0.0524 1.0000 0.0059
-15.500 -1.0958 0.04753 0.04487 -0.0552 1.0000 0.0060
-15.250 -1.1142 0.04267 0.03983 -0.0569 1.0000 0.0060
-15.000 -1.1231 0.03926 0.03627 -0.0574 1.0000 0.0060
-14.750 -1.1319 0.03612 0.03298 -0.0573 1.0000 0.0061
-14.500 -1.1344 0.03379 0.03053 -0.0568 1.0000 0.0062
-14.250 -1.1311 0.03212 0.02878 -0.0561 1.0000 0.0064
-14.000 -1.1295 0.03043 0.02698 -0.0548 1.0000 0.0065
-13.750 -1.1245 0.02908 0.02554 -0.0533 1.0000 0.0066
-13.500 -1.1168 0.02801 0.02439 -0.0518 1.0000 0.0067
-13.000 -1.0892 0.02585 0.02201 -0.0508 0.9591 0.0070
-12.750 -1.0776 0.02496 0.02097 -0.0493 0.9327 0.0071
-12.500 -1.0682 0.02430 0.02017 -0.0469 0.9160 0.0073
-12.250 -1.0559 0.02347 0.01920 -0.0451 0.9026 0.0075
-12.000 -1.0403 0.02282 0.01842 -0.0437 0.8909 0.0077
-11.750 -1.0237 0.02212 0.01759 -0.0424 0.8809 0.0080
-11.500 -1.0070 0.02135 0.01668 -0.0412 0.8720 0.0081
-11.250 -0.9891 0.02060 0.01579 -0.0401 0.8632 0.0083
-11.000 -0.9699 0.01994 0.01499 -0.0392 0.8553 0.0084
-10.750 -0.9525 0.01901 0.01393 -0.0380 0.8472 0.0087
-10.500 -0.9315 0.01845 0.01329 -0.0373 0.8407 0.0090
-10.250 -0.9097 0.01793 0.01271 -0.0367 0.8338 0.0092
-10.000 -0.8873 0.01750 0.01219 -0.0362 0.8274 0.0094
-9.750 -0.8640 0.01708 0.01170 -0.0357 0.8212 0.0097
-9.500 -0.8411 0.01661 0.01114 -0.0352 0.8150 0.0100
-9.250 -0.8176 0.01617 0.01062 -0.0348 0.8097 0.0103
-9.000 -0.7940 0.01571 0.01008 -0.0344 0.8037 0.0106
-8.750 -0.7698 0.01535 0.00963 -0.0340 0.7981 0.0110
-8.500 -0.7456 0.01492 0.00913 -0.0337 0.7931 0.0112
-8.250 -0.7209 0.01454 0.00868 -0.0334 0.7877 0.0114
-8.000 -0.6990 0.01380 0.00782 -0.0326 0.7825 0.0118
-7.750 -0.6748 0.01333 0.00730 -0.0323 0.7778 0.0122
-7.500 -0.6496 0.01300 0.00694 -0.0321 0.7729 0.0126
-7.250 -0.6243 0.01268 0.00658 -0.0318 0.7684 0.0129
-7.000 -0.5985 0.01241 0.00626 -0.0317 0.7642 0.0134
-6.750 -0.5730 0.01206 0.00586 -0.0315 0.7597 0.0138
-6.500 -0.5474 0.01173 0.00548 -0.0312 0.7550 0.0142
-6.000 -0.4955 0.01113 0.00477 -0.0309 0.7471 0.0149
-5.750 -0.4689 0.01091 0.00451 -0.0308 0.7432 0.0152
-5.500 -0.4436 0.01049 0.00404 -0.0306 0.7391 0.0161
-5.250 -0.4173 0.01024 0.00374 -0.0305 0.7353 0.0168
-5.000 -0.3904 0.01000 0.00349 -0.0304 0.7316 0.0175
-4.750 -0.3634 0.00980 0.00326 -0.0304 0.7277 0.0182
-4.500 -0.3363 0.00960 0.00304 -0.0304 0.7241 0.0190
-4.250 -0.3091 0.00943 0.00283 -0.0304 0.7207 0.0198
-4.000 -0.2818 0.00925 0.00262 -0.0305 0.7176 0.0206
-3.750 -0.2545 0.00904 0.00241 -0.0305 0.7140 0.0225
-3.500 -0.2270 0.00888 0.00225 -0.0305 0.7103 0.0246
-3.250 -0.1994 0.00876 0.00210 -0.0306 0.7068 0.0264
-3.000 -0.1718 0.00863 0.00195 -0.0307 0.7037 0.0292
-2.750 -0.1440 0.00847 0.00182 -0.0308 0.7007 0.0334
-2.500 -0.1162 0.00834 0.00170 -0.0309 0.6972 0.0397
-2.250 -0.0890 0.00812 0.00157 -0.0310 0.6936 0.0659
-2.000 -0.0629 0.00775 0.00142 -0.0309 0.6903 0.1345
-1.750 -0.0370 0.00730 0.00127 -0.0309 0.6874 0.2259
-1.500 -0.0139 0.00647 0.00106 -0.0305 0.6841 0.4052
-1.250 0.0107 0.00595 0.00098 -0.0302 0.6805 0.5360
-1.000 0.0377 0.00579 0.00098 -0.0301 0.6771 0.5916
-0.750 0.0650 0.00569 0.00098 -0.0301 0.6740 0.6256
-0.500 0.0933 0.00564 0.00098 -0.0303 0.6708 0.6415
-0.250 0.1217 0.00561 0.00098 -0.0304 0.6673 0.6551
0.000 0.1501 0.00560 0.00098 -0.0306 0.6638 0.6645
0.250 0.1786 0.00561 0.00098 -0.0308 0.6604 0.6699
0.500 0.2072 0.00561 0.00099 -0.0310 0.6573 0.6758
0.750 0.2359 0.00561 0.00101 -0.0313 0.6539 0.6817
1.000 0.2644 0.00561 0.00103 -0.0315 0.6502 0.6876
1.250 0.2928 0.00562 0.00105 -0.0317 0.6466 0.6941
1.500 0.3213 0.00563 0.00108 -0.0319 0.6424 0.7003
1.750 0.3495 0.00563 0.00112 -0.0320 0.6347 0.7074
2.250 0.4053 0.00571 0.00119 -0.0322 0.6086 0.7220
2.750 0.4582 0.00605 0.00133 -0.0319 0.5389 0.7386
3.000 0.4812 0.00659 0.00154 -0.0313 0.4503 0.7464
3.250 0.5007 0.00752 0.00194 -0.0303 0.3226 0.7542
3.500 0.5205 0.00840 0.00234 -0.0294 0.2084 0.7607
3.750 0.5418 0.00907 0.00268 -0.0286 0.1264 0.7669
4.000 0.5645 0.00963 0.00299 -0.0281 0.0690 0.7721
4.250 0.5883 0.01001 0.00324 -0.0276 0.0397 0.7761
4.500 0.6136 0.01026 0.00346 -0.0273 0.0307 0.7804
4.750 0.6395 0.01047 0.00366 -0.0272 0.0274 0.7846
5.000 0.6646 0.01069 0.00388 -0.0269 0.0240 0.7883
5.250 0.6897 0.01089 0.00411 -0.0266 0.0218 0.7922
5.500 0.7148 0.01110 0.00433 -0.0263 0.0199 0.7960
6.000 0.7632 0.01161 0.00487 -0.0254 0.0164 0.8033
6.250 0.7871 0.01183 0.00514 -0.0249 0.0155 0.8080
6.750 0.8321 0.01232 0.00577 -0.0233 0.0139 0.8229
7.000 0.8498 0.01272 0.00632 -0.0214 0.0131 0.8394
7.250 0.8715 0.01323 0.00686 -0.0206 0.0124 0.8871
7.500 0.8944 0.01357 0.00721 -0.0201 0.0122 0.8917
7.750 0.9163 0.01395 0.00761 -0.0193 0.0119 0.8957
8.000 0.9371 0.01439 0.00807 -0.0184 0.0116 0.8986
8.250 0.9564 0.01480 0.00853 -0.0172 0.0114 0.9007
8.500 0.9749 0.01524 0.00902 -0.0158 0.0110 0.9028
8.750 0.9922 0.01567 0.00950 -0.0143 0.0108 0.9047
9.000 1.0072 0.01611 0.00998 -0.0123 0.0107 0.9065
9.250 1.0217 0.01663 0.01052 -0.0104 0.0105 0.9081
9.500 1.0354 0.01717 0.01111 -0.0084 0.0103 0.9096
9.750 1.0499 0.01769 0.01168 -0.0066 0.0101 0.9111
10.000 1.0629 0.01835 0.01240 -0.0047 0.0100 0.9124
10.250 1.0770 0.01897 0.01307 -0.0030 0.0098 0.9137
10.500 1.0891 0.01975 0.01390 -0.0012 0.0095 0.9151
10.750 1.1001 0.02064 0.01486 0.0007 0.0094 0.9170
11.000 1.1083 0.02179 0.01609 0.0028 0.0091 0.9188
11.250 1.1220 0.02252 0.01688 0.0042 0.0091 0.9206
11.500 1.1369 0.02315 0.01758 0.0054 0.0089 0.9222
11.750 1.1482 0.02412 0.01865 0.0069 0.0089 0.9235
12.000 1.1596 0.02511 0.01973 0.0084 0.0088 0.9248
12.250 1.1718 0.02605 0.02075 0.0096 0.0087 0.9260
12.500 1.1832 0.02709 0.02187 0.0108 0.0086 0.9267
12.750 1.1950 0.02812 0.02298 0.0119 0.0084 0.9270
13.000 1.2045 0.02942 0.02437 0.0131 0.0083 0.9271
13.250 1.2173 0.03036 0.02538 0.0139 0.0081 0.9272
13.500 1.2243 0.03193 0.02705 0.0151 0.0080 0.9272
13.750 1.2355 0.03305 0.02823 0.0158 0.0078 0.9273
14.000 1.2438 0.03447 0.02976 0.0167 0.0077 0.9275
14.250 1.2509 0.03607 0.03144 0.0175 0.0076 0.9275
14.500 1.2593 0.03752 0.03297 0.0181 0.0074 0.9275
14.750 1.2660 0.03920 0.03473 0.0186 0.0073 0.9274
15.000 1.2723 0.04093 0.03653 0.0191 0.0072 0.9273
15.250 1.2743 0.04319 0.03891 0.0196 0.0072 0.9272
15.500 1.2776 0.04536 0.04117 0.0198 0.0071 0.9271
15.750 1.2811 0.04759 0.04348 0.0199 0.0069 0.9269
16.000 1.2835 0.05002 0.04599 0.0198 0.0069 0.9268
16.250 1.2787 0.05342 0.04952 0.0195 0.0068 0.9266
16.500 1.2726 0.05718 0.05340 0.0189 0.0067 0.9265
16.750 1.2567 0.06242 0.05883 0.0176 0.0065 0.9263
17.000 1.2479 0.06705 0.06361 0.0161 0.0065 0.9261
17.250 1.2518 0.06996 0.06659 0.0149 0.0065 0.9260
17.500 1.2379 0.07580 0.07261 0.0124 0.0065 0.9258
17.750 1.2367 0.07986 0.07678 0.0104 0.0064 0.9257
18.000 1.2186 0.08712 0.08421 0.0066 0.0064 0.9255
18.250 1.1947 0.09597 0.09324 0.0016 0.0064 0.9254
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Polar data table (+)
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