NACA 66 (p51hroot-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66 (p51hroot-il) Reynolds number: 200,000 Max Cl/Cd: 43.6 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51hroot-il-200000-n5.txt Download as CSV file: xf-p51hroot-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5394 0.08224 0.07826 -0.0795 0.9137 0.0211
-13.250 -0.5903 0.07028 0.06604 -0.0867 0.9061 0.0206
-13.000 -0.6219 0.06392 0.05944 -0.0888 0.8994 0.0206
-12.750 -0.6496 0.05873 0.05400 -0.0892 0.8923 0.0206
-12.500 -0.6717 0.05476 0.04978 -0.0882 0.8862 0.0206
-12.250 -0.6910 0.05118 0.04594 -0.0866 0.8804 0.0207
-12.000 -0.7058 0.04814 0.04264 -0.0845 0.8747 0.0208
-11.750 -0.7175 0.04542 0.03965 -0.0819 0.8699 0.0209
-11.500 -0.7257 0.04300 0.03695 -0.0793 0.8653 0.0212
-11.250 -0.7306 0.04061 0.03427 -0.0766 0.8605 0.0214
-11.000 -0.7325 0.03841 0.03175 -0.0737 0.8563 0.0218
-10.750 -0.7321 0.03634 0.02931 -0.0708 0.8528 0.0223
-10.500 -0.7255 0.03450 0.02714 -0.0685 0.8496 0.0227
-10.250 -0.7176 0.03297 0.02531 -0.0663 0.8459 0.0235
-10.000 -0.7013 0.03176 0.02401 -0.0654 0.8430 0.0240
-9.750 -0.6855 0.03075 0.02289 -0.0643 0.8402 0.0245
-9.500 -0.6675 0.02966 0.02164 -0.0633 0.8378 0.0252
-9.250 -0.6465 0.02845 0.02025 -0.0627 0.8357 0.0259
-9.000 -0.6224 0.02726 0.01888 -0.0627 0.8334 0.0266
-8.750 -0.5972 0.02619 0.01763 -0.0628 0.8309 0.0276
-8.500 -0.5730 0.02530 0.01658 -0.0627 0.8286 0.0286
-8.250 -0.5458 0.02425 0.01555 -0.0633 0.8267 0.0297
-8.000 -0.5213 0.02348 0.01473 -0.0633 0.8247 0.0305
-7.750 -0.4973 0.02273 0.01393 -0.0631 0.8229 0.0315
-7.500 -0.4745 0.02205 0.01318 -0.0626 0.8212 0.0325
-7.250 -0.4529 0.02147 0.01251 -0.0619 0.8196 0.0339
-7.000 -0.4320 0.02087 0.01184 -0.0612 0.8181 0.0350
-6.750 -0.4137 0.02016 0.01116 -0.0602 0.8159 0.0361
-6.500 -0.3961 0.01965 0.01064 -0.0590 0.8137 0.0372
-6.250 -0.3790 0.01920 0.01017 -0.0576 0.8116 0.0385
-6.000 -0.3623 0.01880 0.00972 -0.0560 0.8095 0.0401
-5.750 -0.3450 0.01845 0.00932 -0.0545 0.8075 0.0417
-5.500 -0.3285 0.01802 0.00886 -0.0528 0.8056 0.0441
-5.250 -0.3100 0.01766 0.00846 -0.0515 0.8040 0.0469
-5.000 -0.2904 0.01735 0.00808 -0.0503 0.8027 0.0502
-4.750 -0.2714 0.01702 0.00776 -0.0491 0.8013 0.0553
-4.500 -0.2529 0.01672 0.00753 -0.0479 0.7993 0.0670
-4.250 -0.2382 0.01623 0.00727 -0.0461 0.7972 0.1083
-4.000 -0.2309 0.01540 0.00697 -0.0432 0.7950 0.2186
-3.750 -0.2259 0.01454 0.00668 -0.0398 0.7929 0.3442
-3.500 -0.2249 0.01357 0.00641 -0.0353 0.7907 0.4947
-3.250 -0.2125 0.01335 0.00695 -0.0317 0.7890 0.6616
-3.000 -0.1904 0.01360 0.00724 -0.0302 0.7877 0.7106
-2.750 -0.1654 0.01407 0.00773 -0.0290 0.7868 0.7411
-2.500 -0.1404 0.01454 0.00817 -0.0279 0.7859 0.7618
-2.250 -0.1126 0.01507 0.00870 -0.0273 0.7848 0.7745
-2.000 -0.0913 0.01534 0.00894 -0.0263 0.7827 0.7831
-1.750 -0.0655 0.01558 0.00917 -0.0260 0.7807 0.7867
-1.500 -0.0411 0.01571 0.00926 -0.0256 0.7786 0.7906
-1.250 -0.0186 0.01575 0.00925 -0.0250 0.7768 0.7954
-1.000 0.0053 0.01579 0.00925 -0.0246 0.7752 0.7991
-0.750 0.0322 0.01587 0.00931 -0.0246 0.7739 0.8012
-0.500 0.0592 0.01591 0.00932 -0.0247 0.7725 0.8034
-0.250 0.0860 0.01590 0.00928 -0.0248 0.7714 0.8054
0.000 0.1129 0.01590 0.00925 -0.0249 0.7703 0.8077
0.250 0.1401 0.01586 0.00918 -0.0251 0.7693 0.8101
0.500 0.1547 0.01615 0.00949 -0.0235 0.7651 0.8133
0.750 0.1753 0.01629 0.00965 -0.0227 0.7618 0.8155
1.000 0.2014 0.01629 0.00967 -0.0225 0.7591 0.8170
1.250 0.2345 0.01593 0.00928 -0.0233 0.7560 0.8185
1.500 0.2705 0.01547 0.00880 -0.0244 0.7533 0.8198
1.750 0.2854 0.01571 0.00910 -0.0225 0.7466 0.8223
2.000 0.3111 0.01564 0.00906 -0.0223 0.7430 0.8244
2.250 0.3436 0.01528 0.00870 -0.0231 0.7396 0.8263
2.500 0.3769 0.01496 0.00837 -0.0240 0.7371 0.8285
2.750 0.3911 0.01512 0.00860 -0.0220 0.7293 0.8319
3.000 0.4205 0.01490 0.00843 -0.0222 0.7249 0.8333
3.250 0.4547 0.01448 0.00803 -0.0231 0.7202 0.8347
3.500 0.4709 0.01456 0.00822 -0.0212 0.7115 0.8371
3.750 0.5051 0.01411 0.00779 -0.0220 0.7053 0.8388
4.000 0.5217 0.01402 0.00778 -0.0200 0.6922 0.8418
4.250 0.5407 0.01382 0.00763 -0.0183 0.6763 0.8450
4.500 0.5576 0.01369 0.00756 -0.0163 0.6574 0.8487
4.750 0.5669 0.01373 0.00768 -0.0129 0.6282 0.8519
5.000 0.5851 0.01342 0.00647 -0.0098 0.4825 0.8545
5.250 0.5679 0.01430 0.00690 -0.0020 0.4003 0.8606
5.500 0.5530 0.01558 0.00771 0.0045 0.3118 0.8667
5.750 0.5459 0.01682 0.00855 0.0095 0.2292 0.8719
6.000 0.5448 0.01801 0.00935 0.0133 0.1493 0.8777
6.250 0.5498 0.01904 0.01006 0.0161 0.0882 0.8830
6.500 0.5586 0.01989 0.01073 0.0185 0.0515 0.8878
6.750 0.5730 0.02049 0.01130 0.0200 0.0428 0.8934
7.000 0.5882 0.02109 0.01191 0.0214 0.0377 0.8993
7.250 0.6034 0.02168 0.01256 0.0229 0.0352 0.9049
7.500 0.6196 0.02224 0.01320 0.0241 0.0336 0.9116
7.750 0.6357 0.02285 0.01388 0.0253 0.0324 0.9180
8.000 0.6513 0.02351 0.01461 0.0265 0.0314 0.9256
8.250 0.6673 0.02425 0.01542 0.0275 0.0307 0.9336
8.500 0.6828 0.02514 0.01635 0.0283 0.0299 0.9431
8.750 0.7035 0.02593 0.01724 0.0282 0.0290 0.9521
9.000 0.7252 0.02682 0.01821 0.0277 0.0282 0.9621
9.250 0.7480 0.02779 0.01925 0.0269 0.0276 0.9733
9.500 0.7709 0.02872 0.02023 0.0261 0.0270 0.9913
9.750 0.7870 0.02962 0.02113 0.0267 0.0261 1.0000
10.000 0.8021 0.03057 0.02207 0.0275 0.0256 1.0000
10.250 0.8189 0.03149 0.02302 0.0282 0.0248 1.0000
10.500 0.8369 0.03238 0.02397 0.0288 0.0245 1.0000
10.750 0.8554 0.03331 0.02498 0.0294 0.0239 1.0000
11.000 0.8736 0.03425 0.02600 0.0299 0.0233 1.0000
11.250 0.8910 0.03523 0.02704 0.0305 0.0226 1.0000
11.500 0.9081 0.03625 0.02810 0.0310 0.0221 1.0000
11.750 0.9253 0.03732 0.02919 0.0315 0.0216 1.0000
12.000 0.9443 0.03853 0.03045 0.0318 0.0213 1.0000
12.250 0.9617 0.03991 0.03203 0.0324 0.0209 1.0000
12.500 0.9773 0.04146 0.03377 0.0331 0.0205 1.0000
12.750 0.9918 0.04314 0.03563 0.0337 0.0203 1.0000
13.000 1.0032 0.04499 0.03768 0.0346 0.0200 1.0000
13.250 1.0117 0.04702 0.03992 0.0355 0.0197 1.0000
13.500 1.0178 0.04918 0.04230 0.0365 0.0196 1.0000
13.750 1.0206 0.05154 0.04486 0.0376 0.0193 1.0000
14.000 1.0213 0.05403 0.04754 0.0386 0.0192 1.0000
14.250 1.0212 0.05646 0.05013 0.0394 0.0189 1.0000
14.500 1.0181 0.05927 0.05313 0.0402 0.0188 1.0000
14.750 1.0153 0.06196 0.05596 0.0407 0.0186 1.0000
15.000 1.0096 0.06507 0.05924 0.0411 0.0185 1.0000
15.250 1.0028 0.06841 0.06274 0.0411 0.0184 1.0000
15.500 1.0001 0.07142 0.06583 0.0409 0.0182 1.0000
15.750 0.9835 0.07635 0.07099 0.0403 0.0182 1.0000
16.000 0.9631 0.08193 0.07683 0.0388 0.0181 1.0000
16.250 0.9399 0.08855 0.08370 0.0364 0.0181 1.0000
16.500 0.9236 0.09465 0.08997 0.0338 0.0182 1.0000
16.750 0.8915 0.10410 0.09969 0.0286 0.0181 1.0000
17.000 0.8703 0.11245 0.10820 0.0237 0.0182 1.0000
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