NACA 66(1)-212 (naca661212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(1)-212 (naca661212-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.96 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca661212-il-1000000.txt Download as CSV file: xf-naca661212-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7969 0.04102 0.03857 -0.0662 0.9937 0.0099
-11.250 -0.8098 0.03401 0.03106 -0.0693 0.9726 0.0102
-11.000 -0.7770 0.03480 0.03189 -0.0714 0.9629 0.0104
-10.750 -0.7621 0.03451 0.03151 -0.0706 0.9477 0.0105
-10.500 -0.7707 0.03148 0.02815 -0.0667 0.9319 0.0107
-10.250 -0.7447 0.03303 0.02979 -0.0666 0.9248 0.0109
-10.000 -0.7448 0.03053 0.02700 -0.0634 0.9148 0.0112
-9.750 -0.7427 0.02765 0.02379 -0.0604 0.9062 0.0115
-9.250 -0.7211 0.02336 0.01890 -0.0562 0.8932 0.0125
-9.000 -0.7053 0.02166 0.01694 -0.0547 0.8876 0.0128
-8.750 -0.6851 0.02100 0.01611 -0.0537 0.8827 0.0130
-8.500 -0.6699 0.01786 0.01262 -0.0523 0.8777 0.0137
-8.250 -0.6480 0.01726 0.01195 -0.0517 0.8732 0.0141
-8.000 -0.6252 0.01667 0.01127 -0.0512 0.8692 0.0145
-7.750 -0.6016 0.01630 0.01085 -0.0508 0.8652 0.0150
-7.500 -0.5776 0.01595 0.01046 -0.0504 0.8613 0.0157
-7.250 -0.5538 0.01523 0.00964 -0.0500 0.8577 0.0161
-7.000 -0.5297 0.01461 0.00891 -0.0495 0.8542 0.0166
-6.750 -0.5052 0.01411 0.00835 -0.0492 0.8509 0.0170
-6.500 -0.4803 0.01370 0.00788 -0.0488 0.8474 0.0173
-6.250 -0.4613 0.01234 0.00644 -0.0476 0.8439 0.0183
-6.000 -0.4375 0.01196 0.00602 -0.0471 0.8406 0.0191
-5.750 -0.4121 0.01173 0.00579 -0.0470 0.8377 0.0200
-5.500 -0.3877 0.01137 0.00541 -0.0466 0.8346 0.0208
-5.250 -0.3631 0.01102 0.00502 -0.0462 0.8317 0.0216
-5.000 -0.3378 0.01077 0.00472 -0.0459 0.8290 0.0224
-4.750 -0.3134 0.01042 0.00431 -0.0455 0.8263 0.0231
-4.500 -0.2909 0.00984 0.00370 -0.0447 0.8237 0.0252
-4.250 -0.2650 0.00961 0.00346 -0.0446 0.8212 0.0268
-4.000 -0.2387 0.00941 0.00326 -0.0445 0.8187 0.0287
-3.750 -0.2121 0.00924 0.00307 -0.0445 0.8163 0.0299
-3.500 -0.1869 0.00891 0.00269 -0.0442 0.8140 0.0332
-3.250 -0.1606 0.00873 0.00248 -0.0441 0.8117 0.0367
-3.000 -0.1335 0.00860 0.00234 -0.0441 0.8094 0.0395
-2.750 -0.1073 0.00835 0.00215 -0.0440 0.8073 0.0542
-2.500 -0.0880 0.00737 0.00186 -0.0431 0.8048 0.2406
-2.250 -0.0712 0.00607 0.00150 -0.0419 0.8024 0.5018
-2.000 -0.0500 0.00538 0.00141 -0.0410 0.8003 0.6793
-1.750 -0.0222 0.00536 0.00144 -0.0411 0.7985 0.7110
-1.500 0.0058 0.00538 0.00149 -0.0412 0.7966 0.7324
-1.250 0.0338 0.00545 0.00158 -0.0413 0.7947 0.7507
-1.000 0.0621 0.00547 0.00163 -0.0414 0.7929 0.7605
-0.750 0.0907 0.00553 0.00167 -0.0416 0.7909 0.7687
-0.500 0.1189 0.00555 0.00173 -0.0418 0.7891 0.7758
-0.250 0.1474 0.00563 0.00180 -0.0419 0.7872 0.7842
0.000 0.1758 0.00562 0.00181 -0.0421 0.7846 0.7885
0.250 0.2044 0.00567 0.00183 -0.0424 0.7811 0.7915
0.500 0.2329 0.00564 0.00182 -0.0426 0.7776 0.7936
0.750 0.2616 0.00563 0.00182 -0.0430 0.7742 0.7954
1.000 0.2900 0.00561 0.00176 -0.0431 0.7678 0.7972
1.250 0.3181 0.00557 0.00172 -0.0433 0.7600 0.7991
1.500 0.3461 0.00553 0.00167 -0.0434 0.7530 0.8011
1.750 0.3741 0.00550 0.00168 -0.0435 0.7458 0.8030
2.000 0.4015 0.00548 0.00165 -0.0434 0.7329 0.8049
2.250 0.4288 0.00547 0.00163 -0.0434 0.7174 0.8069
2.500 0.4558 0.00550 0.00163 -0.0433 0.6979 0.8090
2.750 0.4814 0.00560 0.00164 -0.0429 0.6624 0.8112
3.000 0.4954 0.00640 0.00185 -0.0404 0.5212 0.8137
3.250 0.5049 0.00757 0.00231 -0.0373 0.3477 0.8168
3.500 0.5161 0.00867 0.00276 -0.0347 0.1913 0.8197
3.750 0.5285 0.00973 0.00323 -0.0323 0.0544 0.8229
4.000 0.5519 0.01005 0.00347 -0.0317 0.0392 0.8256
4.250 0.5764 0.01031 0.00373 -0.0312 0.0343 0.8281
4.500 0.6009 0.01051 0.00397 -0.0308 0.0318 0.8308
4.750 0.6239 0.01081 0.00428 -0.0300 0.0285 0.8336
5.000 0.6464 0.01116 0.00468 -0.0292 0.0260 0.8366
5.250 0.6706 0.01139 0.00493 -0.0287 0.0245 0.8398
5.500 0.6940 0.01167 0.00521 -0.0281 0.0229 0.8429
5.750 0.7152 0.01206 0.00563 -0.0271 0.0211 0.8464
6.000 0.7329 0.01267 0.00633 -0.0254 0.0198 0.8502
6.250 0.7551 0.01298 0.00668 -0.0246 0.0193 0.8541
6.500 0.7770 0.01333 0.00705 -0.0237 0.0184 0.8580
6.750 0.7972 0.01371 0.00750 -0.0225 0.0177 0.8620
7.000 0.8182 0.01401 0.00783 -0.0215 0.0169 0.8662
7.250 0.8378 0.01436 0.00819 -0.0203 0.0161 0.8710
7.500 0.8518 0.01505 0.00894 -0.0180 0.0155 0.8761
7.750 0.8640 0.01620 0.01020 -0.0155 0.0150 0.8817
8.000 0.8836 0.01667 0.01073 -0.0143 0.0147 0.8872
8.250 0.9021 0.01723 0.01138 -0.0129 0.0145 0.8929
8.500 0.9211 0.01790 0.01213 -0.0117 0.0142 0.8992
8.750 0.9408 0.01867 0.01298 -0.0106 0.0139 0.9053
9.000 0.9599 0.01939 0.01380 -0.0094 0.0135 0.9122
9.250 0.9789 0.02010 0.01460 -0.0082 0.0132 0.9193
9.500 0.9945 0.02052 0.01509 -0.0064 0.0127 0.9286
9.750 1.0094 0.02097 0.01562 -0.0045 0.0124 0.9393
10.000 1.0252 0.02172 0.01648 -0.0028 0.0122 0.9529
10.250 1.0468 0.02251 0.01736 -0.0027 0.0119 0.9725
10.500 1.0717 0.02673 0.02193 -0.0036 0.0112 0.9781
10.750 1.0875 0.02746 0.02280 -0.0025 0.0111 1.0000
11.000 1.0992 0.02895 0.02446 -0.0008 0.0110 1.0000
11.250 1.1090 0.03032 0.02599 0.0012 0.0108 1.0000
11.500 1.1144 0.03230 0.02818 0.0035 0.0107 1.0000
11.750 1.1153 0.03461 0.03073 0.0062 0.0105 1.0000
12.000 1.1117 0.03720 0.03355 0.0092 0.0103 1.0000
12.250 1.1154 0.03848 0.03494 0.0112 0.0100 1.0000
12.500 1.0975 0.04252 0.03929 0.0147 0.0099 1.0000
12.750 1.0711 0.04745 0.04455 0.0181 0.0098 1.0000
13.000 1.0727 0.04887 0.04604 0.0192 0.0095 1.0000
13.250 1.0507 0.05334 0.05073 0.0210 0.0094 1.0000
13.500 0.9854 0.06401 0.06182 0.0216 0.0095 1.0000
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