NACA 63-212 AIRFOIL (n63212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-212 AIRFOIL (n63212-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.94 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63212-il-1000000.txt Download as CSV file: xf-n63212-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-212 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4836 0.11475 0.11321 -0.0111 1.0000 0.0189
-12.500 -0.5837 0.11528 0.11357 -0.0113 1.0000 0.0166
-12.250 -0.8978 0.04360 0.04075 -0.0519 1.0000 0.0119
-12.000 -0.9077 0.04058 0.03758 -0.0519 1.0000 0.0118
-11.750 -0.9159 0.03808 0.03492 -0.0510 1.0000 0.0118
-11.500 -0.9264 0.03573 0.03241 -0.0489 1.0000 0.0118
-11.250 -0.9284 0.03403 0.03056 -0.0466 1.0000 0.0117
-11.000 -0.9308 0.03113 0.02741 -0.0447 1.0000 0.0118
-10.750 -0.9238 0.02900 0.02507 -0.0433 1.0000 0.0117
-10.500 -0.9114 0.02735 0.02325 -0.0422 1.0000 0.0117
-10.250 -0.9005 0.02506 0.02074 -0.0409 1.0000 0.0118
-10.000 -0.8865 0.02307 0.01856 -0.0398 1.0000 0.0118
-9.750 -0.8702 0.02140 0.01674 -0.0388 1.0000 0.0119
-9.500 -0.8529 0.01991 0.01514 -0.0378 1.0000 0.0121
-9.250 -0.8342 0.01886 0.01403 -0.0369 1.0000 0.0124
-9.000 -0.8135 0.01798 0.01310 -0.0362 0.9990 0.0126
-8.750 -0.7809 0.01696 0.01199 -0.0380 0.9886 0.0128
-8.500 -0.7473 0.01595 0.01090 -0.0399 0.9781 0.0130
-8.250 -0.7142 0.01511 0.00999 -0.0416 0.9654 0.0134
-8.000 -0.6861 0.01439 0.00917 -0.0421 0.9485 0.0136
-7.750 -0.6628 0.01380 0.00848 -0.0415 0.9313 0.0139
-7.500 -0.6402 0.01324 0.00782 -0.0408 0.9163 0.0140
-7.250 -0.6167 0.01276 0.00724 -0.0401 0.9031 0.0143
-7.000 -0.5928 0.01227 0.00666 -0.0396 0.8911 0.0144
-6.750 -0.5683 0.01185 0.00615 -0.0391 0.8801 0.0147
-6.500 -0.5430 0.01144 0.00567 -0.0388 0.8694 0.0148
-6.250 -0.5177 0.01098 0.00512 -0.0385 0.8597 0.0151
-6.000 -0.4926 0.01048 0.00452 -0.0382 0.8502 0.0158
-5.750 -0.4660 0.01014 0.00415 -0.0381 0.8409 0.0167
-5.500 -0.4392 0.00988 0.00384 -0.0380 0.8323 0.0177
-5.250 -0.4120 0.00964 0.00354 -0.0379 0.8234 0.0187
-5.000 -0.3849 0.00935 0.00322 -0.0378 0.8152 0.0211
-4.750 -0.3576 0.00909 0.00295 -0.0378 0.8068 0.0265
-4.500 -0.3302 0.00882 0.00270 -0.0378 0.7988 0.0382
-4.250 -0.3028 0.00855 0.00247 -0.0379 0.7908 0.0535
-4.000 -0.2754 0.00823 0.00226 -0.0380 0.7830 0.0830
-3.750 -0.2484 0.00780 0.00202 -0.0381 0.7752 0.1363
-3.500 -0.2217 0.00721 0.00175 -0.0384 0.7677 0.2251
-3.250 -0.1953 0.00654 0.00149 -0.0386 0.7599 0.3396
-3.000 -0.1679 0.00613 0.00135 -0.0388 0.7525 0.4232
-2.750 -0.1397 0.00594 0.00126 -0.0390 0.7449 0.4670
-2.500 -0.1113 0.00582 0.00121 -0.0392 0.7376 0.5001
-2.250 -0.0827 0.00574 0.00117 -0.0393 0.7300 0.5266
-2.000 -0.0541 0.00568 0.00113 -0.0395 0.7229 0.5501
-1.750 -0.0254 0.00564 0.00110 -0.0396 0.7152 0.5670
-1.500 0.0032 0.00559 0.00108 -0.0398 0.7080 0.5875
-1.250 0.0320 0.00556 0.00107 -0.0399 0.7005 0.6040
-1.000 0.0607 0.00555 0.00106 -0.0401 0.6933 0.6163
-0.750 0.0896 0.00555 0.00105 -0.0403 0.6855 0.6263
-0.500 0.1184 0.00555 0.00105 -0.0404 0.6783 0.6363
-0.250 0.1473 0.00555 0.00105 -0.0406 0.6704 0.6455
0.000 0.1761 0.00557 0.00105 -0.0407 0.6631 0.6547
0.250 0.2049 0.00557 0.00107 -0.0409 0.6550 0.6633
0.500 0.2337 0.00560 0.00108 -0.0411 0.6473 0.6719
0.750 0.2624 0.00561 0.00110 -0.0412 0.6388 0.6802
1.000 0.2912 0.00564 0.00113 -0.0414 0.6306 0.6886
1.250 0.3198 0.00567 0.00116 -0.0415 0.6216 0.6970
1.500 0.3486 0.00569 0.00120 -0.0417 0.6126 0.7052
1.750 0.3771 0.00574 0.00125 -0.0418 0.6018 0.7135
2.250 0.4340 0.00584 0.00134 -0.0420 0.5768 0.7299
2.500 0.4623 0.00591 0.00140 -0.0421 0.5618 0.7377
2.750 0.4903 0.00601 0.00147 -0.0421 0.5425 0.7459
3.000 0.5182 0.00611 0.00154 -0.0421 0.5195 0.7538
3.250 0.5462 0.00622 0.00163 -0.0422 0.5011 0.7621
3.500 0.5739 0.00635 0.00173 -0.0422 0.4819 0.7698
3.750 0.6013 0.00654 0.00185 -0.0421 0.4520 0.7784
4.000 0.6274 0.00685 0.00202 -0.0420 0.4035 0.7864
4.250 0.6521 0.00741 0.00228 -0.0417 0.3293 0.7952
4.500 0.6752 0.00812 0.00265 -0.0412 0.2446 0.8037
4.750 0.6984 0.00884 0.00304 -0.0408 0.1679 0.8126
5.000 0.7221 0.00946 0.00342 -0.0403 0.1109 0.8219
5.250 0.7463 0.00998 0.00378 -0.0399 0.0724 0.8311
5.500 0.7713 0.01042 0.00412 -0.0396 0.0497 0.8411
5.750 0.7964 0.01075 0.00444 -0.0392 0.0392 0.8513
6.000 0.8212 0.01111 0.00481 -0.0388 0.0324 0.8620
6.250 0.8465 0.01139 0.00512 -0.0384 0.0290 0.8733
6.500 0.8704 0.01178 0.00555 -0.0378 0.0253 0.8857
6.750 0.8946 0.01203 0.00587 -0.0371 0.0233 0.8989
7.000 0.9172 0.01241 0.00628 -0.0363 0.0213 0.9139
7.250 0.9379 0.01285 0.00680 -0.0350 0.0199 0.9319
7.500 0.9585 0.01308 0.00713 -0.0336 0.0192 0.9603
7.750 0.9868 0.01346 0.00756 -0.0341 0.0182 1.0000
8.000 1.0117 0.01391 0.00801 -0.0339 0.0174 1.0000
8.250 1.0347 0.01451 0.00863 -0.0334 0.0166 1.0000
8.500 1.0538 0.01547 0.00966 -0.0324 0.0158 1.0000
8.750 1.0777 0.01589 0.01012 -0.0320 0.0154 1.0000
9.000 1.1003 0.01640 0.01067 -0.0314 0.0150 1.0000
9.250 1.1218 0.01699 0.01131 -0.0307 0.0146 1.0000
9.500 1.1428 0.01759 0.01195 -0.0300 0.0142 1.0000
9.750 1.1628 0.01823 0.01264 -0.0291 0.0138 1.0000
10.000 1.1819 0.01891 0.01336 -0.0281 0.0134 1.0000
10.250 1.1997 0.01965 0.01414 -0.0269 0.0132 1.0000
10.500 1.2143 0.02059 0.01512 -0.0254 0.0128 1.0000
10.750 1.2217 0.02189 0.01651 -0.0228 0.0125 1.0000
11.000 1.2238 0.02375 0.01850 -0.0197 0.0122 1.0000
11.250 1.2360 0.02459 0.01941 -0.0180 0.0121 1.0000
11.500 1.2483 0.02541 0.02031 -0.0164 0.0120 1.0000
11.750 1.2589 0.02646 0.02145 -0.0148 0.0118 1.0000
12.000 1.2705 0.02736 0.02243 -0.0135 0.0116 1.0000
12.250 1.2800 0.02857 0.02372 -0.0121 0.0114 1.0000
12.500 1.2877 0.03002 0.02527 -0.0107 0.0112 1.0000
12.750 1.2945 0.03160 0.02695 -0.0095 0.0111 1.0000
13.000 1.3022 0.03304 0.02848 -0.0085 0.0108 1.0000
13.250 1.3073 0.03484 0.03038 -0.0075 0.0107 1.0000
13.500 1.3127 0.03662 0.03226 -0.0067 0.0105 1.0000
13.750 1.3153 0.03882 0.03457 -0.0060 0.0104 1.0000
14.000 1.3184 0.04097 0.03682 -0.0056 0.0103 1.0000
14.250 1.3195 0.04343 0.03939 -0.0054 0.0102 1.0000
14.500 1.3202 0.04601 0.04207 -0.0053 0.0101 1.0000
14.750 1.3204 0.04874 0.04489 -0.0056 0.0100 1.0000
15.000 1.3186 0.05180 0.04803 -0.0060 0.0098 1.0000
15.250 1.3126 0.05560 0.05198 -0.0068 0.0098 1.0000
15.500 1.3047 0.05981 0.05630 -0.0080 0.0097 1.0000
15.750 1.2967 0.06427 0.06091 -0.0095 0.0097 1.0000
16.000 1.2819 0.07002 0.06682 -0.0118 0.0096 1.0000
16.250 1.2666 0.07620 0.07317 -0.0146 0.0095 1.0000
16.500 1.2475 0.08346 0.08060 -0.0184 0.0095 1.0000
16.750 1.2293 0.09101 0.08832 -0.0226 0.0095 1.0000
17.000 1.2123 0.09881 0.09628 -0.0272 0.0095 1.0000
17.250 1.1888 0.10842 0.10607 -0.0331 0.0094 1.0000
17.500 1.1690 0.11781 0.11560 -0.0391 0.0095 1.0000
17.750 1.1481 0.12805 0.12601 -0.0457 0.0096 1.0000
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