NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66-209 (naca66209-il) Reynolds number: 1,000,000 Max Cl/Cd: 64.93 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca66209-il-1000000-n5.txt Download as CSV file: xf-naca66209-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.7845 0.02153 0.01778 -0.0503 0.9445 0.0040
-9.250 -0.7683 0.01933 0.01522 -0.0491 0.9361 0.0042
-9.000 -0.7486 0.01800 0.01365 -0.0483 0.9285 0.0043
-8.750 -0.7281 0.01677 0.01219 -0.0474 0.9219 0.0044
-8.500 -0.7078 0.01546 0.01065 -0.0466 0.9150 0.0047
-8.250 -0.6835 0.01506 0.01019 -0.0463 0.9097 0.0051
-8.000 -0.6595 0.01449 0.00953 -0.0459 0.9042 0.0053
-7.750 -0.6349 0.01410 0.00903 -0.0456 0.8990 0.0057
-7.500 -0.6099 0.01375 0.00862 -0.0454 0.8942 0.0062
-7.250 -0.5850 0.01331 0.00809 -0.0451 0.8890 0.0066
-7.000 -0.5596 0.01301 0.00770 -0.0449 0.8842 0.0070
-6.750 -0.5348 0.01251 0.00710 -0.0446 0.8796 0.0072
-6.500 -0.5112 0.01175 0.00625 -0.0441 0.8746 0.0080
-6.250 -0.4853 0.01152 0.00597 -0.0440 0.8704 0.0085
-6.000 -0.4594 0.01122 0.00562 -0.0439 0.8664 0.0090
-5.750 -0.4336 0.01089 0.00524 -0.0437 0.8622 0.0096
-5.500 -0.4073 0.01068 0.00499 -0.0436 0.8581 0.0103
-5.250 -0.3814 0.01038 0.00463 -0.0434 0.8543 0.0108
-5.000 -0.3551 0.01012 0.00433 -0.0434 0.8503 0.0111
-4.750 -0.3301 0.00961 0.00372 -0.0430 0.8460 0.0116
-4.500 -0.3048 0.00916 0.00321 -0.0427 0.8423 0.0130
-4.250 -0.2781 0.00894 0.00297 -0.0427 0.8390 0.0140
-4.000 -0.2513 0.00872 0.00273 -0.0427 0.8355 0.0149
-3.750 -0.2245 0.00850 0.00246 -0.0426 0.8320 0.0157
-3.500 -0.1976 0.00831 0.00224 -0.0426 0.8288 0.0166
-3.250 -0.1704 0.00816 0.00205 -0.0426 0.8257 0.0173
-3.000 -0.1434 0.00793 0.00180 -0.0426 0.8223 0.0194
-2.750 -0.1161 0.00777 0.00165 -0.0427 0.8188 0.0237
-2.500 -0.0887 0.00766 0.00151 -0.0427 0.8157 0.0267
-2.000 -0.0335 0.00744 0.00127 -0.0429 0.8102 0.0334
-1.750 -0.0058 0.00733 0.00119 -0.0431 0.8072 0.0394
-1.500 0.0208 0.00701 0.00107 -0.0431 0.8042 0.1050
-1.250 0.0449 0.00623 0.00091 -0.0430 0.8012 0.3065
-1.000 0.0655 0.00492 0.00072 -0.0425 0.7982 0.6442
-0.750 0.0920 0.00472 0.00077 -0.0423 0.7955 0.7227
-0.500 0.1198 0.00468 0.00079 -0.0424 0.7926 0.7466
-0.250 0.1476 0.00466 0.00080 -0.0424 0.7890 0.7626
0.000 0.1752 0.00466 0.00080 -0.0424 0.7807 0.7740
0.250 0.2026 0.00468 0.00080 -0.0423 0.7681 0.7831
0.500 0.2297 0.00470 0.00081 -0.0422 0.7565 0.7937
0.750 0.2574 0.00473 0.00083 -0.0422 0.7445 0.8005
1.000 0.2848 0.00477 0.00084 -0.0422 0.7294 0.8035
1.250 0.3114 0.00486 0.00085 -0.0420 0.6998 0.8067
1.500 0.3335 0.00531 0.00090 -0.0409 0.5916 0.8100
1.750 0.3502 0.00640 0.00122 -0.0392 0.3966 0.8134
2.000 0.3677 0.00748 0.00155 -0.0378 0.1979 0.8168
2.250 0.3895 0.00817 0.00181 -0.0371 0.0768 0.8205
2.500 0.4148 0.00849 0.00198 -0.0368 0.0385 0.8243
2.750 0.4416 0.00864 0.00212 -0.0367 0.0315 0.8276
3.000 0.4680 0.00881 0.00228 -0.0366 0.0272 0.8309
3.250 0.4943 0.00899 0.00250 -0.0364 0.0231 0.8345
3.500 0.5211 0.00913 0.00265 -0.0364 0.0220 0.8382
3.750 0.5475 0.00931 0.00283 -0.0363 0.0191 0.8416
4.000 0.5731 0.00954 0.00306 -0.0360 0.0155 0.8453
4.250 0.5986 0.00981 0.00337 -0.0357 0.0142 0.8495
4.500 0.6243 0.01005 0.00366 -0.0354 0.0137 0.8538
4.750 0.6496 0.01031 0.00396 -0.0351 0.0132 0.8578
5.000 0.6746 0.01059 0.00429 -0.0347 0.0126 0.8621
5.250 0.6996 0.01090 0.00465 -0.0343 0.0121 0.8666
5.500 0.7242 0.01122 0.00502 -0.0339 0.0116 0.8708
5.750 0.7485 0.01154 0.00540 -0.0334 0.0111 0.8755
6.000 0.7727 0.01190 0.00578 -0.0330 0.0103 0.8806
6.250 0.7947 0.01251 0.00648 -0.0320 0.0096 0.8859
6.500 0.8148 0.01336 0.00746 -0.0308 0.0091 0.8920
6.750 0.8389 0.01371 0.00786 -0.0303 0.0089 0.8975
7.000 0.8623 0.01406 0.00830 -0.0297 0.0086 0.9032
7.250 0.8862 0.01439 0.00869 -0.0292 0.0082 0.9092
7.500 0.9087 0.01487 0.00925 -0.0285 0.0078 0.9152
7.750 0.9309 0.01539 0.00985 -0.0277 0.0075 0.9221
8.000 0.9531 0.01582 0.01036 -0.0269 0.0071 0.9290
8.250 0.9753 0.01619 0.01078 -0.0261 0.0067 0.9373
8.500 0.9974 0.01645 0.01110 -0.0253 0.0064 0.9463
8.750 1.0189 0.01685 0.01158 -0.0245 0.0061 0.9579
9.000 1.0424 0.01769 0.01254 -0.0243 0.0056 0.9747
9.250 1.0683 0.01828 0.01322 -0.0245 0.0054 1.0000
9.500 1.0907 0.01884 0.01387 -0.0240 0.0051 1.0000
9.750 1.1124 0.01949 0.01460 -0.0234 0.0048 1.0000
10.000 1.1336 0.02018 0.01538 -0.0227 0.0045 1.0000
10.250 1.1547 0.02077 0.01604 -0.0221 0.0042 1.0000
10.500 1.1751 0.02145 0.01681 -0.0213 0.0040 1.0000
10.750 1.1954 0.02204 0.01745 -0.0205 0.0038 1.0000
11.000 1.2139 0.02290 0.01843 -0.0195 0.0036 1.0000
11.250 1.2278 0.02437 0.02009 -0.0180 0.0033 1.0000
11.500 1.2413 0.02578 0.02167 -0.0164 0.0032 1.0000
11.750 1.2545 0.02704 0.02311 -0.0147 0.0031 1.0000
12.000 1.2601 0.02887 0.02517 -0.0121 0.0031 1.0000
12.250 1.2621 0.03090 0.02743 -0.0090 0.0030 1.0000
12.500 1.2614 0.03306 0.02982 -0.0059 0.0030 1.0000
12.750 1.2554 0.03576 0.03278 -0.0026 0.0029 1.0000
13.000 1.2311 0.04047 0.03787 0.0016 0.0029 1.0000
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Polar data table (+)
Polar graphs
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