NACA 66 (p51htip-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66 (p51htip-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.11 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51htip-il-1000000-n5.txt Download as CSV file: xf-p51htip-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.9678 0.05190 0.04975 -0.0652 1.0000 0.0064
-14.500 -1.0109 0.04067 0.03801 -0.0695 0.9556 0.0064
-14.250 -0.9977 0.03999 0.03726 -0.0692 0.9319 0.0066
-14.000 -1.0180 0.03651 0.03349 -0.0670 0.9124 0.0066
-13.750 -1.0277 0.03407 0.03081 -0.0647 0.8994 0.0066
-13.500 -1.0226 0.03293 0.02957 -0.0631 0.8896 0.0067
-13.250 -1.0268 0.03095 0.02738 -0.0605 0.8804 0.0068
-13.000 -1.0217 0.02981 0.02610 -0.0585 0.8728 0.0069
-12.750 -1.0185 0.02842 0.02456 -0.0561 0.8655 0.0069
-12.250 -1.0063 0.02613 0.02196 -0.0513 0.8532 0.0072
-12.000 -0.9995 0.02496 0.02062 -0.0487 0.8474 0.0072
-11.750 -0.9899 0.02379 0.01927 -0.0466 0.8427 0.0073
-11.500 -0.9753 0.02280 0.01815 -0.0451 0.8382 0.0075
-11.250 -0.9595 0.02186 0.01705 -0.0438 0.8336 0.0076
-10.750 -0.9242 0.02013 0.01502 -0.0416 0.8256 0.0080
-10.500 -0.9050 0.01934 0.01411 -0.0407 0.8217 0.0081
-10.250 -0.8844 0.01870 0.01335 -0.0399 0.8180 0.0082
-10.000 -0.8634 0.01810 0.01263 -0.0392 0.8148 0.0083
-9.750 -0.8445 0.01712 0.01153 -0.0382 0.8117 0.0086
-9.500 -0.8231 0.01648 0.01082 -0.0375 0.8085 0.0088
-9.250 -0.8006 0.01597 0.01023 -0.0370 0.8053 0.0091
-9.000 -0.7775 0.01553 0.00972 -0.0365 0.8023 0.0093
-8.500 -0.7308 0.01462 0.00868 -0.0356 0.7971 0.0097
-8.250 -0.7070 0.01421 0.00822 -0.0352 0.7944 0.0100
-8.000 -0.6833 0.01375 0.00769 -0.0348 0.7917 0.0103
-7.750 -0.6594 0.01334 0.00721 -0.0344 0.7891 0.0106
-7.500 -0.6353 0.01295 0.00675 -0.0340 0.7867 0.0109
-7.250 -0.6108 0.01260 0.00634 -0.0337 0.7844 0.0112
-7.000 -0.5867 0.01216 0.00585 -0.0333 0.7822 0.0117
-6.750 -0.5616 0.01185 0.00553 -0.0330 0.7797 0.0123
-6.500 -0.5358 0.01161 0.00528 -0.0329 0.7774 0.0130
-6.250 -0.5101 0.01137 0.00501 -0.0328 0.7752 0.0137
-6.000 -0.4844 0.01111 0.00471 -0.0326 0.7732 0.0143
-5.750 -0.4585 0.01088 0.00443 -0.0325 0.7713 0.0148
-5.500 -0.4333 0.01057 0.00409 -0.0322 0.7696 0.0155
-5.250 -0.4073 0.01031 0.00383 -0.0321 0.7679 0.0164
-5.000 -0.3809 0.01010 0.00362 -0.0321 0.7661 0.0172
-4.750 -0.3544 0.00990 0.00340 -0.0320 0.7644 0.0181
-4.500 -0.3278 0.00972 0.00320 -0.0320 0.7627 0.0190
-4.250 -0.3009 0.00955 0.00301 -0.0320 0.7610 0.0196
-4.000 -0.2746 0.00933 0.00277 -0.0320 0.7594 0.0213
-3.750 -0.2479 0.00916 0.00261 -0.0320 0.7579 0.0231
-3.500 -0.2209 0.00901 0.00244 -0.0320 0.7563 0.0244
-3.250 -0.1937 0.00887 0.00229 -0.0320 0.7548 0.0255
-3.000 -0.1663 0.00873 0.00215 -0.0322 0.7534 0.0266
-2.750 -0.1391 0.00857 0.00200 -0.0322 0.7520 0.0301
-2.500 -0.1117 0.00843 0.00188 -0.0323 0.7506 0.0339
-2.250 -0.0844 0.00828 0.00177 -0.0324 0.7492 0.0435
-2.000 -0.0581 0.00802 0.00165 -0.0324 0.7479 0.0827
-1.750 -0.0332 0.00761 0.00151 -0.0322 0.7465 0.1640
-1.500 -0.0098 0.00704 0.00135 -0.0318 0.7451 0.2893
-1.250 0.0067 0.00576 0.00106 -0.0305 0.7436 0.5688
-1.000 0.0300 0.00533 0.00107 -0.0298 0.7421 0.7007
-0.750 0.0576 0.00528 0.00109 -0.0298 0.7408 0.7295
-0.500 0.0859 0.00526 0.00112 -0.0300 0.7398 0.7473
-0.250 0.1143 0.00525 0.00115 -0.0302 0.7386 0.7616
0.000 0.1427 0.00525 0.00119 -0.0304 0.7374 0.7733
0.250 0.1716 0.00526 0.00120 -0.0308 0.7356 0.7788
0.500 0.2006 0.00527 0.00120 -0.0311 0.7327 0.7817
0.750 0.2292 0.00527 0.00120 -0.0314 0.7291 0.7839
1.000 0.2579 0.00528 0.00120 -0.0317 0.7253 0.7860
1.250 0.2867 0.00527 0.00122 -0.0321 0.7212 0.7883
1.500 0.3152 0.00527 0.00121 -0.0323 0.7141 0.7907
1.750 0.3437 0.00527 0.00122 -0.0326 0.7050 0.7931
2.000 0.3719 0.00530 0.00122 -0.0328 0.6920 0.7957
2.250 0.3996 0.00532 0.00123 -0.0329 0.6725 0.7981
2.500 0.4225 0.00564 0.00126 -0.0320 0.5886 0.8008
2.750 0.4320 0.00702 0.00179 -0.0292 0.3882 0.8043
3.000 0.4466 0.00800 0.00219 -0.0273 0.2463 0.8079
3.250 0.4655 0.00866 0.00248 -0.0261 0.1579 0.8110
3.500 0.4859 0.00917 0.00275 -0.0250 0.0940 0.8140
3.750 0.5072 0.00960 0.00301 -0.0241 0.0490 0.8173
4.000 0.5313 0.00986 0.00321 -0.0236 0.0347 0.8206
4.250 0.5558 0.01008 0.00341 -0.0233 0.0284 0.8241
4.500 0.5806 0.01027 0.00361 -0.0229 0.0261 0.8275
4.750 0.6046 0.01049 0.00383 -0.0224 0.0237 0.8311
5.000 0.6282 0.01073 0.00409 -0.0219 0.0211 0.8350
5.250 0.6524 0.01093 0.00430 -0.0214 0.0203 0.8388
5.500 0.6761 0.01115 0.00455 -0.0209 0.0190 0.8424
5.750 0.6991 0.01139 0.00481 -0.0202 0.0179 0.8464
6.000 0.7212 0.01167 0.00510 -0.0194 0.0166 0.8508
6.250 0.7429 0.01199 0.00545 -0.0186 0.0157 0.8553
6.500 0.7649 0.01224 0.00574 -0.0177 0.0153 0.8596
6.750 0.7859 0.01253 0.00608 -0.0167 0.0147 0.8646
7.000 0.8061 0.01280 0.00638 -0.0156 0.0141 0.8700
7.250 0.8246 0.01308 0.00670 -0.0141 0.0135 0.8756
7.500 0.8431 0.01337 0.00702 -0.0127 0.0128 0.8823
7.750 0.8596 0.01380 0.00749 -0.0109 0.0121 0.8893
8.000 0.8761 0.01423 0.00798 -0.0092 0.0118 0.8973
8.250 0.8934 0.01462 0.00844 -0.0076 0.0116 0.9052
8.500 0.9106 0.01501 0.00890 -0.0061 0.0113 0.9144
8.750 0.9270 0.01542 0.00940 -0.0044 0.0111 0.9248
9.000 0.9427 0.01589 0.00994 -0.0026 0.0109 0.9375
9.250 0.9597 0.01637 0.01051 -0.0012 0.0106 0.9540
9.500 0.9844 0.01689 0.01109 -0.0015 0.0103 0.9722
9.750 1.0116 0.01747 0.01173 -0.0025 0.0099 1.0000
10.000 1.0295 0.01800 0.01229 -0.0014 0.0097 1.0000
10.250 1.0469 0.01857 0.01290 -0.0003 0.0095 1.0000
10.500 1.0637 0.01919 0.01354 0.0008 0.0092 1.0000
10.750 1.0785 0.01998 0.01439 0.0021 0.0090 1.0000
11.000 1.0912 0.02098 0.01546 0.0037 0.0087 1.0000
11.250 1.1072 0.02166 0.01621 0.0048 0.0086 1.0000
11.500 1.1225 0.02244 0.01706 0.0060 0.0085 1.0000
11.750 1.1366 0.02331 0.01802 0.0073 0.0084 1.0000
12.000 1.1513 0.02413 0.01892 0.0084 0.0082 1.0000
12.250 1.1644 0.02509 0.01996 0.0097 0.0081 1.0000
12.500 1.1779 0.02601 0.02097 0.0108 0.0080 1.0000
12.750 1.1896 0.02709 0.02215 0.0121 0.0078 1.0000
13.000 1.2013 0.02818 0.02333 0.0134 0.0077 1.0000
13.250 1.2111 0.02942 0.02467 0.0147 0.0076 1.0000
13.500 1.2216 0.03058 0.02592 0.0158 0.0074 1.0000
13.750 1.2311 0.03184 0.02729 0.0170 0.0073 1.0000
14.000 1.2392 0.03323 0.02877 0.0182 0.0072 1.0000
14.250 1.2485 0.03449 0.03011 0.0192 0.0071 1.0000
14.500 1.2566 0.03587 0.03157 0.0202 0.0069 1.0000
14.750 1.2645 0.03729 0.03306 0.0211 0.0068 1.0000
15.000 1.2707 0.03888 0.03474 0.0219 0.0067 1.0000
15.250 1.2726 0.04097 0.03695 0.0229 0.0067 1.0000
15.500 1.2776 0.04275 0.03880 0.0235 0.0066 1.0000
15.750 1.2772 0.04518 0.04135 0.0242 0.0065 1.0000
16.000 1.2712 0.04835 0.04466 0.0248 0.0064 1.0000
16.250 1.2651 0.05168 0.04814 0.0250 0.0063 1.0000
16.500 1.2550 0.05567 0.05229 0.0248 0.0063 1.0000
16.750 1.2410 0.06051 0.05730 0.0240 0.0062 1.0000
17.000 1.2317 0.06504 0.06199 0.0227 0.0062 1.0000
17.250 1.2203 0.07021 0.06732 0.0208 0.0061 1.0000
17.500 1.2002 0.07726 0.07455 0.0176 0.0061 1.0000
17.750 1.1836 0.08431 0.08176 0.0138 0.0061 1.0000
18.000 1.1589 0.09346 0.09109 0.0085 0.0061 1.0000
18.250 1.1151 0.10774 0.10560 -0.0002 0.0062 1.0000
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Polar data table (+)
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