NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-210 (naca65210-il) Reynolds number: 1,000,000 Max Cl/Cd: 69.18 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65210-il-1000000-n5.txt Download as CSV file: xf-naca65210-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-210
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.9905 0.03931 0.03699 -0.0534 1.0000 0.0037
-12.500 -1.0185 0.03488 0.03228 -0.0502 1.0000 0.0037
-12.250 -1.0351 0.03094 0.02800 -0.0470 1.0000 0.0037
-12.000 -1.0363 0.02794 0.02468 -0.0449 1.0000 0.0038
-11.750 -1.0307 0.02553 0.02200 -0.0431 1.0000 0.0039
-11.500 -1.0190 0.02377 0.02003 -0.0418 1.0000 0.0041
-11.250 -1.0022 0.02268 0.01883 -0.0409 1.0000 0.0043
-11.000 -0.9848 0.02161 0.01763 -0.0399 1.0000 0.0045
-10.750 -0.9662 0.02071 0.01663 -0.0390 1.0000 0.0046
-10.500 -0.9469 0.01992 0.01574 -0.0382 1.0000 0.0048
-10.250 -0.9278 0.01904 0.01475 -0.0372 0.9997 0.0050
-10.000 -0.8995 0.01817 0.01376 -0.0382 0.9921 0.0053
-9.750 -0.8698 0.01723 0.01266 -0.0395 0.9848 0.0055
-9.500 -0.8392 0.01650 0.01182 -0.0409 0.9773 0.0058
-9.250 -0.8088 0.01577 0.01097 -0.0421 0.9689 0.0060
-9.000 -0.7803 0.01502 0.01013 -0.0429 0.9594 0.0065
-8.750 -0.7525 0.01470 0.00977 -0.0434 0.9491 0.0069
-8.500 -0.7272 0.01433 0.00933 -0.0432 0.9378 0.0072
-8.250 -0.7028 0.01391 0.00882 -0.0428 0.9271 0.0077
-8.000 -0.6784 0.01351 0.00832 -0.0425 0.9172 0.0081
-7.750 -0.6542 0.01310 0.00780 -0.0420 0.9075 0.0085
-7.500 -0.6292 0.01276 0.00738 -0.0417 0.8978 0.0088
-7.250 -0.6055 0.01218 0.00670 -0.0412 0.8887 0.0093
-6.750 -0.5543 0.01166 0.00610 -0.0408 0.8716 0.0105
-6.500 -0.5284 0.01143 0.00581 -0.0407 0.8638 0.0112
-6.250 -0.5025 0.01111 0.00543 -0.0405 0.8561 0.0117
-6.000 -0.4767 0.01080 0.00504 -0.0403 0.8488 0.0122
-5.750 -0.4505 0.01053 0.00471 -0.0402 0.8410 0.0126
-5.500 -0.4239 0.01034 0.00445 -0.0401 0.8337 0.0129
-5.250 -0.3988 0.00980 0.00383 -0.0398 0.8260 0.0138
-5.000 -0.3725 0.00949 0.00346 -0.0397 0.8194 0.0146
-4.750 -0.3457 0.00925 0.00320 -0.0397 0.8123 0.0154
-4.500 -0.3187 0.00906 0.00297 -0.0397 0.8057 0.0164
-4.250 -0.2915 0.00888 0.00274 -0.0397 0.7984 0.0174
-4.000 -0.2644 0.00870 0.00251 -0.0397 0.7918 0.0182
-3.750 -0.2369 0.00855 0.00232 -0.0397 0.7852 0.0187
-3.500 -0.2097 0.00832 0.00204 -0.0397 0.7791 0.0208
-3.250 -0.1821 0.00815 0.00186 -0.0398 0.7728 0.0235
-3.000 -0.1545 0.00803 0.00171 -0.0399 0.7663 0.0259
-2.750 -0.1267 0.00793 0.00158 -0.0400 0.7601 0.0276
-2.500 -0.0990 0.00779 0.00144 -0.0401 0.7537 0.0346
-2.250 -0.0713 0.00766 0.00132 -0.0402 0.7482 0.0447
-2.000 -0.0439 0.00740 0.00120 -0.0403 0.7420 0.0895
-1.750 -0.0175 0.00691 0.00104 -0.0405 0.7362 0.1985
-1.500 0.0082 0.00613 0.00084 -0.0407 0.7303 0.3779
-1.250 0.0335 0.00539 0.00073 -0.0408 0.7244 0.5707
-1.000 0.0609 0.00521 0.00074 -0.0408 0.7189 0.6343
-0.750 0.0890 0.00516 0.00074 -0.0409 0.7128 0.6569
-0.500 0.1172 0.00516 0.00073 -0.0411 0.7073 0.6705
-0.250 0.1456 0.00513 0.00074 -0.0412 0.7015 0.6866
0.000 0.1739 0.00514 0.00075 -0.0414 0.6956 0.6967
0.250 0.2023 0.00515 0.00076 -0.0415 0.6901 0.7029
0.500 0.2308 0.00516 0.00078 -0.0417 0.6841 0.7089
0.750 0.2589 0.00519 0.00080 -0.0418 0.6750 0.7148
1.000 0.2867 0.00525 0.00082 -0.0419 0.6564 0.7211
1.250 0.3145 0.00530 0.00085 -0.0419 0.6412 0.7268
1.500 0.3422 0.00538 0.00089 -0.0420 0.6229 0.7331
1.750 0.3686 0.00557 0.00094 -0.0418 0.5784 0.7390
2.000 0.3932 0.00598 0.00105 -0.0413 0.4921 0.7455
2.250 0.4141 0.00693 0.00136 -0.0405 0.3317 0.7517
2.500 0.4364 0.00771 0.00166 -0.0400 0.2040 0.7580
2.750 0.4601 0.00834 0.00194 -0.0395 0.1086 0.7649
3.000 0.4846 0.00882 0.00220 -0.0392 0.0457 0.7716
3.250 0.5113 0.00903 0.00237 -0.0391 0.0328 0.7786
3.500 0.5381 0.00920 0.00255 -0.0391 0.0285 0.7851
3.750 0.5648 0.00940 0.00275 -0.0390 0.0241 0.7922
4.000 0.5916 0.00956 0.00296 -0.0389 0.0224 0.7992
4.250 0.6183 0.00973 0.00317 -0.0388 0.0204 0.8071
4.500 0.6445 0.00994 0.00339 -0.0386 0.0181 0.8145
4.750 0.6702 0.01025 0.00372 -0.0384 0.0156 0.8222
5.000 0.6962 0.01045 0.00399 -0.0382 0.0151 0.8295
5.250 0.7221 0.01070 0.00429 -0.0380 0.0144 0.8375
5.500 0.7475 0.01097 0.00461 -0.0376 0.0136 0.8458
5.750 0.7728 0.01124 0.00492 -0.0373 0.0129 0.8541
6.000 0.7977 0.01153 0.00526 -0.0369 0.0122 0.8630
6.250 0.8219 0.01189 0.00568 -0.0364 0.0116 0.8717
6.500 0.8450 0.01237 0.00623 -0.0357 0.0111 0.8816
6.750 0.8661 0.01302 0.00701 -0.0346 0.0106 0.8927
7.000 0.8889 0.01342 0.00748 -0.0339 0.0105 0.9039
7.250 0.9120 0.01373 0.00786 -0.0332 0.0103 0.9156
7.500 0.9342 0.01410 0.00832 -0.0323 0.0100 0.9284
7.750 0.9553 0.01451 0.00882 -0.0312 0.0098 0.9432
8.000 0.9775 0.01493 0.00933 -0.0304 0.0095 0.9640
8.250 1.0048 0.01543 0.00989 -0.0308 0.0091 1.0000
8.500 1.0287 0.01584 0.01034 -0.0304 0.0087 1.0000
8.750 1.0531 0.01615 0.01066 -0.0302 0.0082 1.0000
9.000 1.0762 0.01662 0.01117 -0.0298 0.0079 1.0000
9.250 1.0977 0.01727 0.01187 -0.0291 0.0075 1.0000
9.500 1.1158 0.01836 0.01307 -0.0279 0.0071 1.0000
9.750 1.1374 0.01895 0.01373 -0.0273 0.0070 1.0000
10.000 1.1591 0.01947 0.01433 -0.0267 0.0068 1.0000
10.250 1.1795 0.02014 0.01509 -0.0259 0.0066 1.0000
10.500 1.1994 0.02082 0.01585 -0.0250 0.0063 1.0000
10.750 1.2189 0.02149 0.01660 -0.0241 0.0060 1.0000
11.000 1.2389 0.02201 0.01719 -0.0233 0.0057 1.0000
11.250 1.2593 0.02239 0.01760 -0.0226 0.0054 1.0000
11.500 1.2767 0.02307 0.01835 -0.0214 0.0052 1.0000
11.750 1.2939 0.02351 0.01881 -0.0202 0.0050 1.0000
12.000 1.3064 0.02436 0.01974 -0.0183 0.0048 1.0000
12.250 1.3160 0.02544 0.02093 -0.0162 0.0046 1.0000
12.500 1.3257 0.02651 0.02212 -0.0142 0.0045 1.0000
12.750 1.3350 0.02762 0.02335 -0.0123 0.0044 1.0000
13.000 1.3419 0.02895 0.02482 -0.0104 0.0043 1.0000
13.250 1.3493 0.03025 0.02624 -0.0086 0.0042 1.0000
13.500 1.3544 0.03178 0.02792 -0.0069 0.0041 1.0000
13.750 1.3586 0.03343 0.02970 -0.0053 0.0040 1.0000
14.000 1.3616 0.03525 0.03166 -0.0039 0.0039 1.0000
14.250 1.3653 0.03703 0.03356 -0.0027 0.0038 1.0000
14.500 1.3672 0.03907 0.03572 -0.0017 0.0036 1.0000
14.750 1.3679 0.04132 0.03808 -0.0010 0.0035 1.0000
15.000 1.3619 0.04440 0.04133 -0.0003 0.0035 1.0000
15.250 1.3552 0.04773 0.04482 -0.0002 0.0035 1.0000
15.500 1.3488 0.05120 0.04843 -0.0004 0.0034 1.0000
15.750 1.3384 0.05541 0.05279 -0.0012 0.0033 1.0000
16.000 1.3249 0.06035 0.05788 -0.0027 0.0033 1.0000
16.250 1.3056 0.06660 0.06431 -0.0053 0.0033 1.0000
16.500 1.2796 0.07474 0.07264 -0.0096 0.0033 1.0000
16.750 1.2128 0.09339 0.09166 -0.0215 0.0035 1.0000
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Polar data table (+)
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