NACA 66-210 (naca66210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66-210 (naca66210-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.14 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca66210-il-1000000-n5.txt Download as CSV file: xf-naca66210-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5484 0.14744 0.14567 -0.0126 1.0000 0.0033
-13.750 -0.5499 0.14152 0.13976 -0.0146 1.0000 0.0035
-11.750 -0.9819 0.02722 0.02395 -0.0514 0.9806 0.0040
-11.500 -0.9615 0.02463 0.02107 -0.0525 0.9705 0.0042
-11.250 -0.9393 0.02296 0.01919 -0.0532 0.9609 0.0043
-10.750 -0.8980 0.02104 0.01699 -0.0524 0.9421 0.0047
-10.500 -0.8795 0.02001 0.01578 -0.0515 0.9341 0.0049
-10.250 -0.8596 0.01922 0.01483 -0.0507 0.9265 0.0051
-10.000 -0.8392 0.01843 0.01390 -0.0499 0.9199 0.0054
-9.750 -0.8189 0.01759 0.01290 -0.0491 0.9131 0.0056
-9.500 -0.7974 0.01691 0.01208 -0.0484 0.9072 0.0058
-9.250 -0.7748 0.01635 0.01141 -0.0478 0.9011 0.0060
-9.000 -0.7535 0.01557 0.01051 -0.0471 0.8955 0.0065
-8.750 -0.7289 0.01533 0.01024 -0.0469 0.8907 0.0068
-8.500 -0.7048 0.01494 0.00978 -0.0465 0.8855 0.0072
-8.000 -0.6566 0.01411 0.00878 -0.0459 0.8764 0.0080
-7.750 -0.6324 0.01363 0.00820 -0.0455 0.8716 0.0084
-7.500 -0.6081 0.01322 0.00770 -0.0451 0.8673 0.0087
-7.250 -0.5829 0.01288 0.00730 -0.0449 0.8630 0.0090
-7.000 -0.5599 0.01221 0.00654 -0.0443 0.8583 0.0097
-6.750 -0.5346 0.01194 0.00623 -0.0441 0.8540 0.0103
-6.500 -0.5089 0.01168 0.00594 -0.0440 0.8503 0.0108
-6.250 -0.4832 0.01139 0.00561 -0.0438 0.8464 0.0114
-6.000 -0.4578 0.01106 0.00522 -0.0436 0.8425 0.0119
-5.750 -0.4323 0.01077 0.00487 -0.0434 0.8389 0.0124
-5.500 -0.4062 0.01053 0.00458 -0.0433 0.8356 0.0128
-5.250 -0.3801 0.01027 0.00429 -0.0432 0.8320 0.0131
-5.000 -0.3556 0.00977 0.00371 -0.0428 0.8284 0.0137
-4.750 -0.3302 0.00942 0.00330 -0.0425 0.8249 0.0146
-4.500 -0.3038 0.00919 0.00305 -0.0425 0.8217 0.0155
-4.250 -0.2769 0.00900 0.00286 -0.0425 0.8184 0.0167
-4.000 -0.2502 0.00881 0.00265 -0.0424 0.8152 0.0178
-3.750 -0.2233 0.00864 0.00244 -0.0424 0.8122 0.0186
-3.500 -0.1962 0.00850 0.00226 -0.0424 0.8095 0.0192
-3.250 -0.1695 0.00825 0.00200 -0.0424 0.8068 0.0221
-3.000 -0.1422 0.00810 0.00185 -0.0425 0.8039 0.0246
-2.750 -0.1148 0.00797 0.00172 -0.0426 0.8010 0.0269
-2.500 -0.0873 0.00787 0.00159 -0.0426 0.7983 0.0283
-2.000 -0.0323 0.00763 0.00137 -0.0428 0.7931 0.0396
-1.750 -0.0057 0.00735 0.00126 -0.0429 0.7904 0.0899
-1.500 0.0188 0.00672 0.00110 -0.0427 0.7877 0.2386
-1.250 0.0422 0.00592 0.00093 -0.0426 0.7851 0.4290
-1.000 0.0641 0.00501 0.00081 -0.0420 0.7827 0.6664
-0.750 0.0911 0.00489 0.00085 -0.0419 0.7805 0.7220
-0.500 0.1189 0.00485 0.00088 -0.0420 0.7779 0.7452
-0.250 0.1471 0.00485 0.00090 -0.0421 0.7746 0.7570
0.000 0.1754 0.00486 0.00091 -0.0423 0.7705 0.7652
0.250 0.2028 0.00486 0.00093 -0.0422 0.7612 0.7764
0.500 0.2306 0.00489 0.00092 -0.0422 0.7505 0.7821
0.750 0.2585 0.00491 0.00092 -0.0423 0.7407 0.7844
1.250 0.3137 0.00498 0.00094 -0.0424 0.7120 0.7893
1.500 0.3404 0.00507 0.00096 -0.0422 0.6841 0.7920
1.750 0.3571 0.00592 0.00112 -0.0403 0.5137 0.7950
2.000 0.3732 0.00698 0.00148 -0.0385 0.3307 0.7981
2.250 0.3927 0.00777 0.00176 -0.0374 0.1962 0.8012
2.500 0.4143 0.00839 0.00201 -0.0365 0.0951 0.8044
2.750 0.4381 0.00883 0.00222 -0.0360 0.0392 0.8075
3.000 0.4645 0.00901 0.00238 -0.0359 0.0315 0.8103
3.250 0.4907 0.00918 0.00254 -0.0358 0.0277 0.8131
3.500 0.5168 0.00936 0.00274 -0.0356 0.0245 0.8162
3.750 0.5433 0.00950 0.00290 -0.0355 0.0236 0.8196
4.000 0.5696 0.00967 0.00309 -0.0354 0.0216 0.8231
4.250 0.5952 0.00988 0.00330 -0.0352 0.0192 0.8264
4.500 0.6202 0.01015 0.00359 -0.0348 0.0164 0.8300
4.750 0.6458 0.01036 0.00382 -0.0345 0.0158 0.8337
5.000 0.6712 0.01060 0.00409 -0.0343 0.0148 0.8374
5.250 0.6961 0.01086 0.00439 -0.0339 0.0139 0.8409
5.500 0.7208 0.01112 0.00467 -0.0335 0.0131 0.8448
5.750 0.7451 0.01144 0.00501 -0.0330 0.0122 0.8490
6.250 0.7897 0.01244 0.00618 -0.0313 0.0111 0.8577
6.500 0.8129 0.01283 0.00662 -0.0307 0.0110 0.8626
7.000 0.8582 0.01368 0.00761 -0.0292 0.0107 0.8723
7.250 0.8815 0.01402 0.00800 -0.0287 0.0104 0.8776
7.500 0.9040 0.01444 0.00849 -0.0280 0.0100 0.8826
7.750 0.9258 0.01489 0.00903 -0.0271 0.0097 0.8882
8.000 0.9478 0.01535 0.00955 -0.0263 0.0093 0.8941
8.250 0.9694 0.01578 0.01005 -0.0255 0.0090 0.8999
8.500 0.9913 0.01616 0.01048 -0.0247 0.0087 0.9065
8.750 1.0131 0.01648 0.01083 -0.0239 0.0082 0.9131
9.000 1.0322 0.01712 0.01154 -0.0227 0.0078 0.9210
9.250 1.0487 0.01811 0.01270 -0.0211 0.0074 0.9292
9.500 1.0681 0.01865 0.01334 -0.0199 0.0073 0.9383
9.750 1.0871 0.01908 0.01387 -0.0186 0.0071 0.9494
10.250 1.1327 0.02036 0.01539 -0.0181 0.0066 1.0000
10.500 1.1518 0.02098 0.01609 -0.0171 0.0063 1.0000
10.750 1.1697 0.02157 0.01674 -0.0159 0.0060 1.0000
11.000 1.1878 0.02196 0.01717 -0.0147 0.0057 1.0000
11.250 1.2050 0.02244 0.01770 -0.0134 0.0055 1.0000
11.500 1.2227 0.02281 0.01810 -0.0122 0.0053 1.0000
11.750 1.2372 0.02359 0.01896 -0.0107 0.0051 1.0000
12.000 1.2490 0.02466 0.02014 -0.0088 0.0048 1.0000
12.250 1.2619 0.02557 0.02116 -0.0072 0.0047 1.0000
12.500 1.2731 0.02664 0.02236 -0.0055 0.0046 1.0000
12.750 1.2817 0.02795 0.02381 -0.0035 0.0045 1.0000
13.000 1.2903 0.02921 0.02521 -0.0017 0.0044 1.0000
13.250 1.2984 0.03048 0.02661 0.0001 0.0042 1.0000
13.500 1.3051 0.03188 0.02814 0.0019 0.0041 1.0000
13.750 1.3097 0.03347 0.02987 0.0037 0.0040 1.0000
14.000 1.3111 0.03539 0.03194 0.0056 0.0039 1.0000
14.250 1.3157 0.03701 0.03368 0.0070 0.0037 1.0000
14.500 1.3159 0.03908 0.03590 0.0085 0.0036 1.0000
14.750 1.3171 0.04112 0.03805 0.0097 0.0036 1.0000
15.000 1.3151 0.04353 0.04058 0.0108 0.0035 1.0000
15.250 1.3011 0.04740 0.04467 0.0118 0.0035 1.0000
15.500 1.2942 0.05064 0.04804 0.0122 0.0034 1.0000
15.750 1.2857 0.05430 0.05182 0.0120 0.0033 1.0000
16.000 1.2698 0.05917 0.05686 0.0111 0.0033 1.0000
16.250 1.2345 0.06766 0.06561 0.0078 0.0033 1.0000
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Polar data table (+)
Polar graphs
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