NACA 65(1)-212 a=0.6 (naca651212a06-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: NACA 65(1)-212 a=0.6 (naca651212a06-il) Reynolds number: 500,000 Max Cl/Cd: 69.31 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca651212a06-il-500000-n5.txt Download as CSV file: xf-naca651212a06-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5868 0.09144 0.08919 -0.0309 1.0000 0.0098
-11.500 -0.7120 0.05718 0.05474 -0.0539 1.0000 0.0093
-11.250 -0.7773 0.04653 0.04375 -0.0562 1.0000 0.0093
-11.000 -0.8039 0.03980 0.03656 -0.0568 0.9411 0.0096
-10.750 -0.8262 0.03565 0.03197 -0.0525 0.9154 0.0099
-10.500 -0.8370 0.03165 0.02749 -0.0490 0.8999 0.0103
-10.250 -0.8360 0.02861 0.02400 -0.0464 0.8884 0.0107
-10.000 -0.8257 0.02652 0.02154 -0.0446 0.8785 0.0111
-9.750 -0.8116 0.02491 0.01962 -0.0431 0.8702 0.0115
-9.500 -0.7943 0.02390 0.01848 -0.0421 0.8624 0.0119
-9.250 -0.7743 0.02328 0.01776 -0.0413 0.8555 0.0122
-9.000 -0.7539 0.02253 0.01689 -0.0406 0.8484 0.0125
-8.750 -0.7332 0.02172 0.01593 -0.0398 0.8421 0.0128
-8.500 -0.7117 0.02080 0.01485 -0.0392 0.8357 0.0133
-8.250 -0.6899 0.01991 0.01378 -0.0385 0.8298 0.0138
-8.000 -0.6674 0.01902 0.01273 -0.0379 0.8242 0.0143
-7.750 -0.6440 0.01832 0.01188 -0.0374 0.8183 0.0148
-7.500 -0.6200 0.01782 0.01123 -0.0370 0.8131 0.0152
-7.250 -0.5982 0.01666 0.00997 -0.0363 0.8080 0.0157
-7.000 -0.5748 0.01600 0.00924 -0.0359 0.8026 0.0162
-6.750 -0.5508 0.01548 0.00865 -0.0354 0.7977 0.0166
-6.500 -0.5263 0.01498 0.00810 -0.0351 0.7929 0.0171
-6.250 -0.5016 0.01452 0.00757 -0.0347 0.7881 0.0178
-6.000 -0.4767 0.01411 0.00708 -0.0344 0.7837 0.0186
-5.750 -0.4518 0.01369 0.00658 -0.0341 0.7794 0.0194
-5.500 -0.4268 0.01324 0.00607 -0.0337 0.7747 0.0198
-5.250 -0.4018 0.01283 0.00559 -0.0334 0.7702 0.0203
-5.000 -0.3780 0.01226 0.00495 -0.0329 0.7663 0.0214
-4.750 -0.3522 0.01190 0.00457 -0.0327 0.7623 0.0224
-4.500 -0.3261 0.01160 0.00424 -0.0326 0.7581 0.0235
-4.250 -0.2998 0.01135 0.00394 -0.0324 0.7541 0.0250
-4.000 -0.2733 0.01114 0.00366 -0.0323 0.7504 0.0265
-3.750 -0.2468 0.01083 0.00332 -0.0322 0.7464 0.0286
-3.500 -0.2202 0.01057 0.00306 -0.0321 0.7426 0.0314
-3.250 -0.1932 0.01038 0.00282 -0.0321 0.7390 0.0345
-3.000 -0.1662 0.01019 0.00261 -0.0320 0.7357 0.0404
-2.750 -0.1394 0.00994 0.00243 -0.0320 0.7320 0.0572
-2.500 -0.1140 0.00947 0.00221 -0.0319 0.7281 0.1257
-2.250 -0.0902 0.00878 0.00196 -0.0316 0.7244 0.2520
-2.000 -0.0690 0.00780 0.00169 -0.0310 0.7213 0.4483
-1.750 -0.0450 0.00736 0.00168 -0.0305 0.7180 0.5707
-1.500 -0.0186 0.00722 0.00169 -0.0303 0.7142 0.6221
-1.250 0.0080 0.00713 0.00172 -0.0300 0.7106 0.6587
-1.000 0.0357 0.00710 0.00170 -0.0300 0.7073 0.6744
-0.750 0.0637 0.00710 0.00168 -0.0300 0.7043 0.6865
-0.500 0.0920 0.00707 0.00167 -0.0302 0.7007 0.6956
-0.250 0.1204 0.00706 0.00166 -0.0304 0.6970 0.7015
0.000 0.1486 0.00706 0.00166 -0.0305 0.6936 0.7077
0.500 0.2051 0.00708 0.00169 -0.0308 0.6870 0.7206
0.750 0.2335 0.00709 0.00173 -0.0310 0.6833 0.7277
1.000 0.2617 0.00711 0.00177 -0.0311 0.6796 0.7342
1.250 0.2900 0.00714 0.00180 -0.0312 0.6763 0.7414
1.500 0.3183 0.00717 0.00185 -0.0314 0.6731 0.7480
1.750 0.3467 0.00720 0.00192 -0.0316 0.6692 0.7554
2.000 0.3751 0.00723 0.00198 -0.0318 0.6652 0.7618
2.250 0.4032 0.00727 0.00202 -0.0319 0.6604 0.7681
2.500 0.4311 0.00729 0.00207 -0.0320 0.6503 0.7741
2.750 0.4584 0.00729 0.00207 -0.0319 0.6361 0.7800
3.000 0.4852 0.00736 0.00207 -0.0317 0.6136 0.7859
3.250 0.5109 0.00742 0.00208 -0.0314 0.5794 0.7910
3.500 0.5344 0.00771 0.00215 -0.0307 0.5161 0.7968
3.750 0.5523 0.00848 0.00244 -0.0293 0.3996 0.8028
4.000 0.5675 0.00954 0.00296 -0.0276 0.2689 0.8101
4.500 0.5980 0.01120 0.00404 -0.0238 0.0869 0.8310
4.750 0.6117 0.01176 0.00455 -0.0209 0.0510 0.8464
5.000 0.6390 0.01227 0.00492 -0.0214 0.0370 0.8942
5.250 0.6619 0.01266 0.00527 -0.0208 0.0304 0.9007
5.500 0.6850 0.01295 0.00559 -0.0201 0.0273 0.9060
5.750 0.7069 0.01331 0.00595 -0.0193 0.0243 0.9102
6.000 0.7278 0.01368 0.00635 -0.0182 0.0222 0.9141
6.250 0.7496 0.01400 0.00672 -0.0173 0.0209 0.9178
6.500 0.7704 0.01435 0.00712 -0.0163 0.0196 0.9212
6.750 0.7902 0.01472 0.00753 -0.0151 0.0186 0.9248
7.000 0.8086 0.01519 0.00802 -0.0137 0.0175 0.9283
7.250 0.8249 0.01579 0.00867 -0.0120 0.0167 0.9314
7.500 0.8426 0.01625 0.00920 -0.0105 0.0164 0.9344
7.750 0.8584 0.01673 0.00975 -0.0087 0.0160 0.9377
8.000 0.8725 0.01726 0.01035 -0.0066 0.0155 0.9411
8.250 0.8870 0.01783 0.01098 -0.0047 0.0151 0.9444
8.500 0.9033 0.01839 0.01159 -0.0033 0.0144 0.9474
8.750 0.9202 0.01900 0.01226 -0.0020 0.0140 0.9505
9.000 0.9379 0.01969 0.01302 -0.0011 0.0137 0.9539
9.250 0.9571 0.02049 0.01388 -0.0006 0.0134 0.9576
9.750 0.9986 0.02261 0.01614 -0.0008 0.0127 0.9704
10.000 1.0146 0.02393 0.01755 0.0000 0.0125 1.0000
10.250 1.0299 0.02487 0.01860 0.0012 0.0124 1.0000
10.500 1.0449 0.02583 0.01966 0.0024 0.0122 1.0000
10.750 1.0595 0.02695 0.02089 0.0036 0.0120 1.0000
11.000 1.0737 0.02804 0.02211 0.0047 0.0117 1.0000
11.250 1.0872 0.02911 0.02328 0.0058 0.0115 1.0000
11.500 1.0996 0.03028 0.02458 0.0070 0.0111 1.0000
11.750 1.1110 0.03167 0.02610 0.0082 0.0109 1.0000
12.000 1.1210 0.03318 0.02777 0.0094 0.0107 1.0000
12.250 1.1297 0.03472 0.02945 0.0106 0.0105 1.0000
12.500 1.1374 0.03625 0.03110 0.0117 0.0103 1.0000
12.750 1.1430 0.03809 0.03309 0.0128 0.0102 1.0000
13.000 1.1483 0.03981 0.03493 0.0138 0.0100 1.0000
13.250 1.1520 0.04174 0.03699 0.0147 0.0099 1.0000
13.500 1.1541 0.04390 0.03928 0.0155 0.0098 1.0000
13.750 1.1556 0.04604 0.04153 0.0161 0.0096 1.0000
14.000 1.1551 0.04852 0.04413 0.0166 0.0095 1.0000
14.250 1.1508 0.05157 0.04733 0.0169 0.0094 1.0000
14.500 1.1437 0.05498 0.05089 0.0169 0.0092 1.0000
14.750 1.1283 0.05974 0.05587 0.0165 0.0092 1.0000
15.000 1.1195 0.06381 0.06013 0.0155 0.0090 1.0000
15.250 1.1034 0.06929 0.06582 0.0139 0.0090 1.0000
15.500 1.0834 0.07578 0.07254 0.0114 0.0090 1.0000
15.750 1.0681 0.08210 0.07905 0.0083 0.0089 1.0000
16.000 1.0475 0.08993 0.08706 0.0041 0.0089 1.0000
16.250 1.0195 0.10025 0.09760 -0.0021 0.0089 1.0000
16.500 0.9863 0.11312 0.11066 -0.0101 0.0090 1.0000
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Polar data table (+)
Polar graphs
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