NACA 66-210 (naca66210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-210 (naca66210-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.18 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66210-il-1000000.txt Download as CSV file: xf-naca66210-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-210
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5948 0.04229 0.03996 -0.0636 0.9702 0.0095
-8.500 -0.5944 0.03780 0.03518 -0.0631 0.9554 0.0090
-8.250 -0.5981 0.03189 0.02883 -0.0597 0.9415 0.0091
-8.000 -0.6200 0.02163 0.01747 -0.0531 0.9274 0.0097
-7.750 -0.6022 0.02020 0.01586 -0.0520 0.9206 0.0101
-7.500 -0.5806 0.01953 0.01506 -0.0513 0.9152 0.0105
-7.250 -0.5581 0.01882 0.01424 -0.0508 0.9099 0.0109
-7.000 -0.5362 0.01756 0.01278 -0.0500 0.9047 0.0113
-6.750 -0.5135 0.01629 0.01130 -0.0493 0.9001 0.0119
-6.500 -0.4893 0.01532 0.01019 -0.0488 0.8955 0.0126
-6.250 -0.4640 0.01494 0.00971 -0.0485 0.8910 0.0132
-6.000 -0.4417 0.01320 0.00776 -0.0476 0.8867 0.0141
-5.750 -0.4175 0.01246 0.00697 -0.0472 0.8824 0.0148
-5.500 -0.3924 0.01200 0.00647 -0.0469 0.8780 0.0154
-5.250 -0.3674 0.01152 0.00593 -0.0466 0.8741 0.0162
-5.000 -0.3422 0.01109 0.00545 -0.0462 0.8704 0.0171
-4.750 -0.3163 0.01077 0.00508 -0.0461 0.8666 0.0181
-4.500 -0.2895 0.01062 0.00491 -0.0460 0.8629 0.0188
-4.250 -0.2674 0.00973 0.00392 -0.0451 0.8592 0.0199
-4.000 -0.2428 0.00923 0.00337 -0.0447 0.8558 0.0215
-3.750 -0.2166 0.00896 0.00308 -0.0446 0.8522 0.0230
-3.500 -0.1900 0.00874 0.00284 -0.0445 0.8486 0.0251
-3.250 -0.1630 0.00861 0.00268 -0.0445 0.8455 0.0266
-3.000 -0.1371 0.00826 0.00225 -0.0442 0.8424 0.0300
-2.750 -0.1103 0.00803 0.00203 -0.0442 0.8394 0.0342
-2.500 -0.0829 0.00789 0.00186 -0.0443 0.8364 0.0375
-2.250 -0.0562 0.00764 0.00168 -0.0442 0.8335 0.0574
-2.000 -0.0356 0.00651 0.00140 -0.0436 0.8304 0.3141
-1.750 -0.0169 0.00517 0.00114 -0.0428 0.8273 0.6276
-1.500 0.0088 0.00494 0.00119 -0.0424 0.8244 0.7213
-1.250 0.0367 0.00493 0.00121 -0.0425 0.8217 0.7459
-1.000 0.0646 0.00492 0.00123 -0.0425 0.8192 0.7620
-0.750 0.0920 0.00496 0.00131 -0.0424 0.8168 0.7829
-0.500 0.1199 0.00502 0.00136 -0.0424 0.8142 0.7942
-0.250 0.1481 0.00504 0.00139 -0.0426 0.8110 0.8019
0.000 0.1757 0.00505 0.00143 -0.0425 0.8070 0.8100
0.250 0.2038 0.00509 0.00145 -0.0426 0.8031 0.8166
0.500 0.2317 0.00507 0.00144 -0.0426 0.7973 0.8199
0.750 0.2593 0.00504 0.00140 -0.0426 0.7889 0.8224
1.000 0.2873 0.00503 0.00139 -0.0427 0.7814 0.8250
1.250 0.3150 0.00503 0.00136 -0.0427 0.7715 0.8278
1.500 0.3428 0.00503 0.00135 -0.0427 0.7608 0.8305
1.750 0.3697 0.00503 0.00133 -0.0425 0.7440 0.8333
2.000 0.3965 0.00505 0.00133 -0.0423 0.7217 0.8361
2.250 0.4224 0.00514 0.00136 -0.0420 0.6891 0.8391
2.500 0.4399 0.00584 0.00149 -0.0401 0.5423 0.8427
2.750 0.4529 0.00710 0.00191 -0.0378 0.3371 0.8466
3.000 0.4666 0.00833 0.00235 -0.0357 0.1368 0.8504
3.250 0.4868 0.00906 0.00270 -0.0345 0.0417 0.8543
3.500 0.5119 0.00935 0.00298 -0.0342 0.0327 0.8582
3.750 0.5378 0.00953 0.00319 -0.0339 0.0304 0.8617
4.000 0.5629 0.00976 0.00345 -0.0335 0.0271 0.8654
4.250 0.5850 0.01034 0.00412 -0.0325 0.0227 0.8696
4.500 0.6112 0.01050 0.00428 -0.0324 0.0217 0.8736
4.750 0.6358 0.01074 0.00456 -0.0319 0.0202 0.8776
5.000 0.6600 0.01104 0.00490 -0.0314 0.0188 0.8819
5.250 0.6838 0.01141 0.00528 -0.0308 0.0176 0.8867
5.500 0.7039 0.01208 0.00604 -0.0295 0.0165 0.8915
5.750 0.7211 0.01315 0.00722 -0.0276 0.0157 0.8972
6.250 0.7685 0.01380 0.00797 -0.0264 0.0147 0.9075
6.500 0.7909 0.01431 0.00855 -0.0256 0.0140 0.9132
6.750 0.8126 0.01497 0.00928 -0.0246 0.0135 0.9189
7.000 0.8343 0.01553 0.00991 -0.0236 0.0129 0.9251
7.250 0.8563 0.01618 0.01062 -0.0228 0.0125 0.9315
7.500 0.8768 0.01684 0.01136 -0.0216 0.0121 0.9388
7.750 0.8970 0.01779 0.01239 -0.0205 0.0116 0.9468
8.000 0.9157 0.02044 0.01533 -0.0192 0.0109 0.9554
8.250 0.9369 0.02083 0.01585 -0.0182 0.0106 0.9686
8.500 0.9645 0.02199 0.01718 -0.0187 0.0101 0.9831
8.750 0.9884 0.02378 0.01919 -0.0187 0.0096 1.0000
9.000 1.0064 0.02596 0.02162 -0.0176 0.0092 1.0000
9.250 1.0232 0.02772 0.02358 -0.0164 0.0089 1.0000
9.500 1.0375 0.02963 0.02569 -0.0149 0.0086 1.0000
9.750 1.0544 0.03027 0.02643 -0.0139 0.0084 1.0000
10.000 1.0711 0.03070 0.02691 -0.0128 0.0081 1.0000
10.250 1.0830 0.03174 0.02804 -0.0112 0.0079 1.0000
10.500 1.0387 0.04036 0.03744 -0.0028 0.0074 1.0000
10.750 1.0083 0.04570 0.04314 0.0034 0.0073 1.0000
11.000 0.9765 0.05153 0.04927 0.0081 0.0072 1.0000
11.250 0.9407 0.05767 0.05564 0.0112 0.0072 1.0000
11.500 0.9096 0.06318 0.06131 0.0121 0.0073 1.0000
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Polar data table (+)
Polar graphs
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