NACA 66-210 (naca66210-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: NACA 66-210 (naca66210-il) Reynolds number: 200,000 Max Cl/Cd: 46.65 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca66210-il-200000-n5.txt Download as CSV file: xf-naca66210-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5195 0.08602 0.08244 -0.0421 1.0000 0.0150
-9.750 -0.5290 0.07952 0.07599 -0.0466 1.0000 0.0147
-9.500 -0.5539 0.07029 0.06679 -0.0536 1.0000 0.0141
-9.250 -0.5879 0.06298 0.05937 -0.0544 1.0000 0.0134
-9.000 -0.6100 0.06032 0.05667 -0.0506 1.0000 0.0134
-8.750 -0.6235 0.05704 0.05328 -0.0485 0.9963 0.0134
-8.500 -0.6190 0.05113 0.04705 -0.0507 0.9869 0.0134
-8.250 -0.6088 0.04694 0.04259 -0.0524 0.9798 0.0137
-8.000 -0.5859 0.04607 0.04162 -0.0543 0.9760 0.0149
-7.750 -0.5707 0.04270 0.03795 -0.0549 0.9692 0.0160
-7.500 -0.5534 0.03824 0.03306 -0.0555 0.9644 0.0166
-7.250 -0.5385 0.03423 0.02857 -0.0548 0.9573 0.0169
-7.000 -0.5178 0.03052 0.02433 -0.0546 0.9526 0.0174
-6.750 -0.4970 0.02770 0.02102 -0.0538 0.9471 0.0182
-6.500 -0.4726 0.02617 0.01905 -0.0534 0.9420 0.0194
-6.250 -0.4485 0.02377 0.01644 -0.0538 0.9384 0.0209
-6.000 -0.4240 0.02232 0.01475 -0.0535 0.9340 0.0217
-5.750 -0.3989 0.02104 0.01327 -0.0532 0.9295 0.0226
-5.500 -0.3719 0.01986 0.01191 -0.0532 0.9260 0.0237
-5.250 -0.3440 0.01902 0.01093 -0.0534 0.9232 0.0258
-5.000 -0.3201 0.01823 0.01002 -0.0527 0.9180 0.0271
-4.750 -0.2946 0.01737 0.00903 -0.0523 0.9139 0.0279
-4.500 -0.2689 0.01657 0.00816 -0.0521 0.9105 0.0287
-4.250 -0.2477 0.01548 0.00705 -0.0511 0.9064 0.0308
-4.000 -0.2253 0.01491 0.00646 -0.0504 0.9018 0.0332
-3.750 -0.2008 0.01447 0.00598 -0.0500 0.8983 0.0368
-3.500 -0.1754 0.01407 0.00546 -0.0497 0.8954 0.0399
-3.250 -0.1523 0.01367 0.00500 -0.0490 0.8911 0.0435
-3.000 -0.1281 0.01334 0.00465 -0.0485 0.8870 0.0515
-2.750 -0.1034 0.01292 0.00432 -0.0481 0.8837 0.0736
-2.500 -0.0874 0.01142 0.00386 -0.0470 0.8807 0.3374
-2.250 -0.0798 0.01017 0.00406 -0.0432 0.8755 0.6806
-2.000 -0.0596 0.01037 0.00449 -0.0407 0.8721 0.7721
-1.750 -0.0363 0.01059 0.00472 -0.0391 0.8692 0.8043
-1.500 -0.0109 0.01073 0.00479 -0.0381 0.8669 0.8206
-1.250 0.0120 0.01091 0.00496 -0.0368 0.8633 0.8348
-1.000 0.0349 0.01109 0.00513 -0.0354 0.8600 0.8476
-0.750 0.0609 0.01112 0.00512 -0.0351 0.8571 0.8544
-0.500 0.0884 0.01112 0.00507 -0.0350 0.8547 0.8574
-0.250 0.1166 0.01110 0.00501 -0.0352 0.8526 0.8604
0.000 0.1422 0.01114 0.00505 -0.0351 0.8491 0.8640
0.250 0.1684 0.01117 0.00507 -0.0351 0.8457 0.8678
0.500 0.1953 0.01119 0.00510 -0.0350 0.8427 0.8704
0.750 0.2232 0.01118 0.00510 -0.0351 0.8401 0.8731
1.000 0.2505 0.01117 0.00511 -0.0351 0.8366 0.8763
1.250 0.2756 0.01120 0.00518 -0.0347 0.8311 0.8805
1.500 0.3028 0.01119 0.00521 -0.0346 0.8273 0.8835
1.750 0.3313 0.01116 0.00522 -0.0347 0.8242 0.8862
2.000 0.3555 0.01113 0.00526 -0.0340 0.8158 0.8899
2.250 0.3819 0.01089 0.00506 -0.0333 0.8028 0.8936
2.500 0.4078 0.01060 0.00478 -0.0323 0.7843 0.8970
2.750 0.4326 0.01040 0.00461 -0.0312 0.7638 0.9005
3.000 0.4561 0.01020 0.00439 -0.0297 0.7284 0.9048
3.250 0.4749 0.01018 0.00394 -0.0271 0.5978 0.9098
3.500 0.4728 0.01166 0.00418 -0.0214 0.3548 0.9164
4.000 0.4928 0.01406 0.00521 -0.0161 0.0626 0.9305
4.250 0.5137 0.01455 0.00564 -0.0150 0.0470 0.9374
4.500 0.5369 0.01497 0.00613 -0.0144 0.0401 0.9432
4.750 0.5581 0.01559 0.00681 -0.0134 0.0358 0.9505
5.000 0.5836 0.01603 0.00736 -0.0133 0.0326 0.9565
5.250 0.6087 0.01660 0.00799 -0.0133 0.0294 0.9637
5.500 0.6355 0.01738 0.00883 -0.0137 0.0273 0.9704
5.750 0.6616 0.01855 0.01005 -0.0141 0.0255 0.9783
6.000 0.6897 0.02002 0.01158 -0.0147 0.0243 0.9864
6.250 0.7203 0.02113 0.01280 -0.0157 0.0237 0.9989
6.500 0.7441 0.02224 0.01402 -0.0152 0.0230 1.0000
6.750 0.7680 0.02326 0.01520 -0.0148 0.0218 1.0000
7.000 0.7920 0.02437 0.01645 -0.0145 0.0205 1.0000
7.250 0.8166 0.02589 0.01816 -0.0142 0.0198 1.0000
7.500 0.8399 0.02752 0.02000 -0.0137 0.0191 1.0000
7.750 0.8616 0.02932 0.02204 -0.0131 0.0185 1.0000
8.000 0.8812 0.03109 0.02403 -0.0122 0.0178 1.0000
8.250 0.8985 0.03299 0.02610 -0.0114 0.0170 1.0000
8.500 0.9109 0.03575 0.02925 -0.0097 0.0160 1.0000
8.750 0.9219 0.03861 0.03256 -0.0076 0.0155 1.0000
9.000 0.9281 0.04204 0.03643 -0.0051 0.0151 1.0000
9.250 0.9295 0.04578 0.04058 -0.0023 0.0149 1.0000
9.500 0.9260 0.04971 0.04488 0.0008 0.0147 1.0000
9.750 0.9175 0.05367 0.04916 0.0040 0.0145 1.0000
10.000 0.9039 0.05719 0.05291 0.0075 0.0143 1.0000
10.250 0.8878 0.06080 0.05673 0.0104 0.0141 1.0000
10.500 0.8690 0.06482 0.06093 0.0123 0.0141 1.0000
10.750 0.8489 0.06931 0.06559 0.0129 0.0142 1.0000
11.000 0.8276 0.07445 0.07087 0.0121 0.0145 1.0000
11.250 0.8057 0.08079 0.07734 0.0093 0.0143 1.0000
11.500 0.7836 0.08878 0.08541 0.0042 0.0147 1.0000
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Polar data table (+)
Polar graphs
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