NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(1)-212 (naca651212-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.8 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca651212-il-1000000-n5.txt Download as CSV file: xf-naca651212-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-212
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
------ -------- --------- --------- -------- -------- --------
-16.250 -1.0431 0.06366 0.06131 -0.0497 1.0000 0.0064
-16.000 -1.0659 0.05661 0.05409 -0.0539 1.0000 0.0064
-15.750 -1.0848 0.05087 0.04818 -0.0567 1.0000 0.0064
-15.500 -1.0991 0.04624 0.04338 -0.0584 1.0000 0.0064
-15.250 -1.1058 0.04282 0.03981 -0.0592 1.0000 0.0065
-15.000 -1.1154 0.03930 0.03612 -0.0596 1.0000 0.0065
-14.750 -1.1178 0.03670 0.03339 -0.0595 1.0000 0.0066
-14.500 -1.1160 0.03465 0.03120 -0.0592 1.0000 0.0066
-14.250 -1.1186 0.03229 0.02869 -0.0584 1.0000 0.0066
-14.000 -1.1175 0.03039 0.02668 -0.0574 1.0000 0.0069
-13.750 -1.1127 0.02889 0.02508 -0.0563 1.0000 0.0070
-13.500 -1.1031 0.02786 0.02400 -0.0553 1.0000 0.0071
-13.250 -1.0985 0.02644 0.02246 -0.0537 1.0000 0.0072
-13.000 -1.0873 0.02565 0.02162 -0.0524 1.0000 0.0073
-12.750 -1.0758 0.02494 0.02085 -0.0509 1.0000 0.0075
-12.500 -1.0668 0.02411 0.01995 -0.0490 1.0000 0.0076
-12.250 -1.0563 0.02345 0.01923 -0.0470 1.0000 0.0078
-12.000 -1.0440 0.02262 0.01829 -0.0453 1.0000 0.0080
-11.750 -1.0291 0.02186 0.01746 -0.0439 1.0000 0.0082
-11.500 -1.0129 0.02121 0.01672 -0.0426 1.0000 0.0084
-11.250 -0.9834 0.02040 0.01582 -0.0442 0.9819 0.0087
-11.000 -0.9510 0.01964 0.01495 -0.0462 0.9698 0.0090
-10.750 -0.9213 0.01891 0.01410 -0.0476 0.9568 0.0091
-10.500 -0.8988 0.01807 0.01312 -0.0475 0.9413 0.0094
-10.250 -0.8796 0.01732 0.01226 -0.0466 0.9272 0.0097
-10.000 -0.8593 0.01680 0.01165 -0.0458 0.9153 0.0099
-9.750 -0.8380 0.01637 0.01114 -0.0450 0.9042 0.0101
-9.500 -0.8157 0.01598 0.01068 -0.0444 0.8940 0.0104
-9.250 -0.7935 0.01554 0.01016 -0.0437 0.8849 0.0107
-9.000 -0.7709 0.01515 0.00969 -0.0431 0.8757 0.0110
-8.750 -0.7482 0.01468 0.00913 -0.0426 0.8670 0.0113
-8.500 -0.7246 0.01435 0.00872 -0.0421 0.8589 0.0117
-8.250 -0.7009 0.01394 0.00824 -0.0417 0.8510 0.0120
-8.000 -0.6774 0.01354 0.00774 -0.0412 0.8435 0.0122
-7.750 -0.6531 0.01316 0.00730 -0.0408 0.8356 0.0123
-7.500 -0.6304 0.01261 0.00665 -0.0402 0.8282 0.0127
-7.250 -0.6064 0.01216 0.00616 -0.0398 0.8210 0.0132
-6.750 -0.5559 0.01155 0.00547 -0.0394 0.8080 0.0141
-6.500 -0.5306 0.01126 0.00511 -0.0392 0.8011 0.0145
-6.250 -0.5049 0.01097 0.00478 -0.0390 0.7947 0.0149
-6.000 -0.4790 0.01070 0.00445 -0.0389 0.7880 0.0153
-5.750 -0.4529 0.01044 0.00414 -0.0387 0.7822 0.0159
-5.500 -0.4264 0.01021 0.00386 -0.0387 0.7761 0.0162
-5.250 -0.4002 0.00995 0.00355 -0.0386 0.7702 0.0169
-5.000 -0.3736 0.00969 0.00327 -0.0385 0.7644 0.0182
-4.750 -0.3468 0.00949 0.00305 -0.0385 0.7582 0.0192
-4.500 -0.3198 0.00932 0.00284 -0.0385 0.7526 0.0203
-4.250 -0.2924 0.00916 0.00265 -0.0386 0.7470 0.0214
-4.000 -0.2652 0.00899 0.00245 -0.0386 0.7417 0.0230
-3.750 -0.2378 0.00881 0.00227 -0.0387 0.7368 0.0256
-3.500 -0.2102 0.00867 0.00212 -0.0388 0.7313 0.0279
-3.250 -0.1826 0.00856 0.00197 -0.0389 0.7259 0.0311
-3.000 -0.1550 0.00840 0.00183 -0.0390 0.7211 0.0374
-2.750 -0.1276 0.00819 0.00170 -0.0391 0.7162 0.0572
-2.500 -0.1007 0.00790 0.00154 -0.0392 0.7113 0.1037
-2.250 -0.0748 0.00739 0.00135 -0.0393 0.7068 0.2001
-2.000 -0.0494 0.00671 0.00113 -0.0395 0.7018 0.3348
-1.750 -0.0250 0.00589 0.00093 -0.0395 0.6971 0.5150
-1.500 0.0024 0.00567 0.00091 -0.0396 0.6929 0.5813
-1.250 0.0305 0.00557 0.00091 -0.0397 0.6882 0.6158
-0.750 0.0873 0.00553 0.00091 -0.0401 0.6792 0.6504
-0.500 0.1161 0.00552 0.00091 -0.0404 0.6749 0.6569
-0.250 0.1449 0.00552 0.00091 -0.0406 0.6703 0.6616
0.000 0.1736 0.00555 0.00091 -0.0409 0.6660 0.6661
0.250 0.2024 0.00555 0.00092 -0.0411 0.6619 0.6704
0.500 0.2312 0.00555 0.00094 -0.0414 0.6575 0.6751
0.750 0.2599 0.00558 0.00095 -0.0416 0.6530 0.6798
1.000 0.2885 0.00560 0.00098 -0.0419 0.6489 0.6842
1.250 0.3171 0.00561 0.00102 -0.0421 0.6420 0.6888
1.500 0.3452 0.00567 0.00104 -0.0422 0.6276 0.6938
1.750 0.3733 0.00573 0.00108 -0.0423 0.6137 0.6983
2.000 0.4006 0.00583 0.00112 -0.0423 0.5912 0.7030
2.250 0.4269 0.00603 0.00118 -0.0421 0.5476 0.7082
2.500 0.4517 0.00640 0.00131 -0.0418 0.4799 0.7131
2.750 0.4715 0.00729 0.00165 -0.0407 0.3430 0.7182
3.250 0.5145 0.00879 0.00232 -0.0393 0.1363 0.7285
3.500 0.5377 0.00933 0.00262 -0.0388 0.0721 0.7341
3.750 0.5626 0.00969 0.00286 -0.0385 0.0411 0.7400
4.000 0.5888 0.00992 0.00306 -0.0383 0.0321 0.7453
4.250 0.6150 0.01012 0.00326 -0.0382 0.0280 0.7511
4.500 0.6413 0.01033 0.00348 -0.0380 0.0246 0.7569
4.750 0.6675 0.01051 0.00369 -0.0379 0.0227 0.7628
5.000 0.6933 0.01074 0.00393 -0.0377 0.0205 0.7695
5.250 0.7187 0.01099 0.00421 -0.0374 0.0184 0.7757
5.500 0.7444 0.01121 0.00447 -0.0372 0.0175 0.7824
6.000 0.7946 0.01172 0.00502 -0.0366 0.0152 0.7953
6.250 0.8186 0.01208 0.00541 -0.0361 0.0140 0.8025
6.500 0.8430 0.01235 0.00574 -0.0357 0.0137 0.8097
6.750 0.8671 0.01267 0.00610 -0.0352 0.0133 0.8174
7.000 0.8907 0.01298 0.00648 -0.0347 0.0129 0.8247
7.250 0.9140 0.01333 0.00689 -0.0341 0.0125 0.8324
7.500 0.9367 0.01369 0.00730 -0.0334 0.0122 0.8403
8.000 0.9808 0.01444 0.00817 -0.0318 0.0116 0.8582
8.250 1.0019 0.01486 0.00865 -0.0309 0.0114 0.8675
8.500 1.0221 0.01532 0.00917 -0.0298 0.0110 0.8776
8.750 1.0407 0.01583 0.00976 -0.0285 0.0108 0.8890
9.000 1.0559 0.01654 0.01058 -0.0266 0.0104 0.9023
9.250 1.0736 0.01699 0.01111 -0.0250 0.0102 0.9164
9.500 1.0895 0.01745 0.01166 -0.0232 0.0101 0.9332
9.750 1.1044 0.01790 0.01224 -0.0212 0.0100 0.9606
10.000 1.1251 0.01849 0.01290 -0.0206 0.0098 1.0000
10.250 1.1401 0.01916 0.01363 -0.0189 0.0097 1.0000
10.500 1.1553 0.01980 0.01434 -0.0174 0.0095 1.0000
10.750 1.1699 0.02052 0.01512 -0.0158 0.0093 1.0000
11.000 1.1840 0.02129 0.01596 -0.0143 0.0092 1.0000
11.250 1.1982 0.02205 0.01678 -0.0128 0.0090 1.0000
11.500 1.2136 0.02269 0.01748 -0.0116 0.0087 1.0000
11.750 1.2262 0.02360 0.01846 -0.0101 0.0086 1.0000
12.000 1.2402 0.02438 0.01929 -0.0089 0.0084 1.0000
12.250 1.2532 0.02526 0.02023 -0.0077 0.0083 1.0000
12.500 1.2641 0.02634 0.02139 -0.0063 0.0082 1.0000
12.750 1.2750 0.02743 0.02255 -0.0050 0.0081 1.0000
13.000 1.2841 0.02869 0.02388 -0.0037 0.0079 1.0000
13.250 1.2926 0.03002 0.02529 -0.0025 0.0078 1.0000
13.500 1.2961 0.03188 0.02727 -0.0010 0.0076 1.0000
13.750 1.3012 0.03363 0.02914 0.0002 0.0075 1.0000
14.000 1.3058 0.03547 0.03111 0.0012 0.0074 1.0000
14.250 1.3110 0.03727 0.03303 0.0021 0.0074 1.0000
14.500 1.3219 0.03851 0.03435 0.0026 0.0072 1.0000
14.750 1.3250 0.04061 0.03657 0.0032 0.0072 1.0000
15.000 1.3236 0.04328 0.03938 0.0038 0.0072 1.0000
15.250 1.3303 0.04510 0.04129 0.0040 0.0070 1.0000
15.500 1.3306 0.04771 0.04402 0.0042 0.0069 1.0000
15.750 1.3269 0.05088 0.04734 0.0041 0.0068 1.0000
16.000 1.3244 0.05407 0.05065 0.0037 0.0067 1.0000
16.250 1.3192 0.05776 0.05448 0.0030 0.0067 1.0000
16.500 1.3102 0.06216 0.05903 0.0018 0.0066 1.0000
16.750 1.3056 0.06620 0.06318 0.0004 0.0065 1.0000
17.000 1.2962 0.07116 0.06829 -0.0016 0.0065 1.0000
17.250 1.2833 0.07701 0.07429 -0.0043 0.0064 1.0000
17.500 1.2675 0.08381 0.08124 -0.0078 0.0064 1.0000
17.750 1.2435 0.09270 0.09032 -0.0129 0.0064 1.0000
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Polar data table (+)
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