NACA 63-212 AIRFOIL (n63212-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-212 AIRFOIL (n63212-il) Reynolds number: 500,000 Max Cl/Cd: 81.69 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63212-il-500000.txt Download as CSV file: xf-n63212-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5662 0.12264 0.12023 -0.0084 1.0000 0.0260
-12.250 -0.5642 0.11840 0.11600 -0.0103 1.0000 0.0266
-9.500 -0.8082 0.03374 0.02917 -0.0420 1.0000 0.0192
-9.250 -0.7950 0.03166 0.02686 -0.0409 1.0000 0.0191
-9.000 -0.7810 0.02945 0.02443 -0.0397 1.0000 0.0191
-8.750 -0.7657 0.02753 0.02230 -0.0385 1.0000 0.0191
-8.500 -0.7516 0.02507 0.01966 -0.0370 1.0000 0.0189
-8.000 -0.7041 0.02157 0.01578 -0.0372 0.9934 0.0190
-7.750 -0.6723 0.01929 0.01333 -0.0388 0.9874 0.0192
-7.500 -0.6393 0.01756 0.01151 -0.0405 0.9813 0.0195
-7.250 -0.6061 0.01634 0.01025 -0.0423 0.9734 0.0200
-7.000 -0.5738 0.01543 0.00928 -0.0437 0.9638 0.0205
-6.750 -0.5432 0.01470 0.00852 -0.0447 0.9528 0.0212
-6.500 -0.5164 0.01414 0.00790 -0.0447 0.9402 0.0220
-6.250 -0.4926 0.01364 0.00730 -0.0440 0.9270 0.0228
-6.000 -0.4692 0.01315 0.00673 -0.0433 0.9143 0.0236
-5.750 -0.4462 0.01253 0.00603 -0.0425 0.9026 0.0246
-5.500 -0.4228 0.01194 0.00538 -0.0418 0.8920 0.0265
-5.250 -0.3978 0.01157 0.00494 -0.0413 0.8822 0.0290
-5.000 -0.3727 0.01105 0.00439 -0.0409 0.8720 0.0348
-4.750 -0.3474 0.01058 0.00391 -0.0406 0.8631 0.0497
-4.500 -0.3218 0.01009 0.00354 -0.0404 0.8538 0.0790
-4.250 -0.2969 0.00943 0.00317 -0.0403 0.8449 0.1499
-4.000 -0.2729 0.00850 0.00274 -0.0403 0.8364 0.2774
-3.750 -0.2480 0.00773 0.00248 -0.0403 0.8277 0.4097
-3.500 -0.2212 0.00748 0.00234 -0.0402 0.8199 0.4679
-3.250 -0.1935 0.00732 0.00228 -0.0402 0.8113 0.5106
-3.000 -0.1659 0.00725 0.00222 -0.0401 0.8039 0.5423
-2.750 -0.1376 0.00719 0.00215 -0.0402 0.7954 0.5635
-2.500 -0.1099 0.00715 0.00211 -0.0400 0.7882 0.5836
-2.250 -0.0817 0.00710 0.00209 -0.0400 0.7797 0.6037
-2.000 -0.0537 0.00712 0.00207 -0.0399 0.7725 0.6234
-1.750 -0.0253 0.00711 0.00207 -0.0400 0.7642 0.6395
-1.500 0.0027 0.00712 0.00206 -0.0399 0.7571 0.6513
-1.250 0.0313 0.00709 0.00204 -0.0400 0.7488 0.6609
-1.000 0.0597 0.00713 0.00200 -0.0400 0.7417 0.6709
-0.750 0.0881 0.00710 0.00201 -0.0400 0.7335 0.6793
-0.500 0.1166 0.00713 0.00198 -0.0401 0.7265 0.6883
-0.250 0.1451 0.00711 0.00199 -0.0402 0.7183 0.6966
0.000 0.1734 0.00715 0.00198 -0.0402 0.7112 0.7051
0.250 0.2020 0.00714 0.00201 -0.0403 0.7030 0.7135
0.500 0.2303 0.00718 0.00202 -0.0403 0.6958 0.7217
0.750 0.2589 0.00718 0.00205 -0.0404 0.6875 0.7306
1.000 0.2870 0.00722 0.00208 -0.0404 0.6801 0.7386
1.250 0.3156 0.00723 0.00212 -0.0405 0.6714 0.7478
1.500 0.3435 0.00727 0.00217 -0.0404 0.6635 0.7557
1.750 0.3720 0.00730 0.00222 -0.0405 0.6544 0.7648
2.000 0.3998 0.00732 0.00229 -0.0404 0.6456 0.7728
2.250 0.4279 0.00738 0.00233 -0.0404 0.6358 0.7817
2.500 0.4555 0.00740 0.00240 -0.0403 0.6232 0.7901
2.750 0.4832 0.00744 0.00245 -0.0402 0.6102 0.7987
3.000 0.5107 0.00749 0.00252 -0.0400 0.5959 0.8077
3.250 0.5376 0.00755 0.00257 -0.0397 0.5770 0.8161
3.500 0.5647 0.00765 0.00265 -0.0395 0.5561 0.8258
3.750 0.5913 0.00772 0.00276 -0.0392 0.5382 0.8342
4.000 0.6182 0.00783 0.00287 -0.0390 0.5187 0.8437
4.250 0.6442 0.00797 0.00300 -0.0386 0.4934 0.8533
4.500 0.6690 0.00819 0.00315 -0.0380 0.4560 0.8629
4.750 0.6926 0.00859 0.00335 -0.0373 0.3981 0.8736
5.000 0.7124 0.00938 0.00373 -0.0362 0.3018 0.8853
5.250 0.7297 0.01037 0.00428 -0.0348 0.1996 0.8976
5.500 0.7474 0.01124 0.00480 -0.0333 0.1233 0.9113
5.750 0.7648 0.01199 0.00530 -0.0316 0.0722 0.9277
6.000 0.7827 0.01252 0.00574 -0.0298 0.0518 0.9483
6.250 0.8096 0.01302 0.00625 -0.0300 0.0421 0.9771
6.500 0.8385 0.01353 0.00679 -0.0307 0.0371 1.0000
6.750 0.8614 0.01439 0.00764 -0.0303 0.0326 1.0000
7.000 0.8868 0.01487 0.00816 -0.0302 0.0305 1.0000
7.250 0.9110 0.01542 0.00873 -0.0300 0.0283 1.0000
7.500 0.9309 0.01637 0.00968 -0.0292 0.0263 1.0000
7.750 0.9515 0.01723 0.01060 -0.0284 0.0252 1.0000
8.000 0.9734 0.01791 0.01134 -0.0277 0.0243 1.0000
8.250 0.9943 0.01867 0.01216 -0.0269 0.0233 1.0000
8.500 1.0147 0.01946 0.01299 -0.0261 0.0225 1.0000
8.750 1.0343 0.02032 0.01387 -0.0252 0.0218 1.0000
9.000 1.0526 0.02135 0.01493 -0.0242 0.0211 1.0000
9.250 1.0680 0.02350 0.01713 -0.0230 0.0202 1.0000
9.500 1.0883 0.02409 0.01783 -0.0221 0.0198 1.0000
9.750 1.1076 0.02513 0.01897 -0.0212 0.0194 1.0000
10.000 1.1264 0.02635 0.02030 -0.0203 0.0189 1.0000
10.250 1.1444 0.02765 0.02173 -0.0193 0.0185 1.0000
10.500 1.1613 0.02908 0.02329 -0.0183 0.0182 1.0000
10.750 1.1761 0.03051 0.02485 -0.0170 0.0178 1.0000
11.000 1.1890 0.03206 0.02652 -0.0155 0.0175 1.0000
11.250 1.1997 0.03368 0.02829 -0.0139 0.0173 1.0000
11.500 1.2073 0.03521 0.02994 -0.0120 0.0170 1.0000
11.750 1.2133 0.03693 0.03179 -0.0102 0.0168 1.0000
12.000 1.2189 0.03851 0.03344 -0.0087 0.0164 1.0000
12.250 1.2204 0.04138 0.03646 -0.0073 0.0161 1.0000
12.500 1.2104 0.04566 0.04103 -0.0055 0.0159 1.0000
12.750 1.1999 0.04925 0.04486 -0.0041 0.0159 1.0000
13.000 1.1849 0.05281 0.04866 -0.0032 0.0158 1.0000
13.250 1.1714 0.05670 0.05276 -0.0030 0.0157 1.0000
13.500 1.1566 0.06084 0.05711 -0.0035 0.0157 1.0000
13.750 1.1378 0.06624 0.06272 -0.0047 0.0158 1.0000
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Polar data table (+)
Polar graphs
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