NACA 66 (p51hroot-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66 (p51hroot-il) Reynolds number: 100,000 Max Cl/Cd: 27.08 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51hroot-il-100000-n5.txt Download as CSV file: xf-p51hroot-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5280 0.08135 0.07605 -0.0853 0.9755 0.0339
-12.500 -0.5512 0.07405 0.06856 -0.0908 0.9677 0.0338
-12.250 -0.5690 0.06840 0.06268 -0.0943 0.9607 0.0336
-12.000 -0.5882 0.06367 0.05769 -0.0959 0.9524 0.0337
-11.750 -0.6011 0.05980 0.05355 -0.0965 0.9455 0.0336
-11.500 -0.6196 0.05646 0.04990 -0.0950 0.9361 0.0338
-11.250 -0.6310 0.05363 0.04677 -0.0931 0.9286 0.0338
-11.000 -0.6422 0.05115 0.04400 -0.0902 0.9205 0.0339
-10.750 -0.6519 0.04884 0.04134 -0.0867 0.9141 0.0341
-10.500 -0.6570 0.04695 0.03916 -0.0833 0.9077 0.0342
-10.250 -0.6594 0.04485 0.03666 -0.0801 0.9027 0.0344
-10.000 -0.6562 0.04292 0.03435 -0.0773 0.8985 0.0347
-9.750 -0.6441 0.04089 0.03219 -0.0762 0.8944 0.0354
-9.500 -0.6299 0.03945 0.03064 -0.0752 0.8909 0.0364
-9.250 -0.6142 0.03810 0.02912 -0.0741 0.8877 0.0376
-9.000 -0.5971 0.03660 0.02736 -0.0730 0.8851 0.0389
-8.750 -0.5775 0.03503 0.02551 -0.0722 0.8820 0.0397
-8.500 -0.5548 0.03356 0.02378 -0.0718 0.8788 0.0406
-8.250 -0.5312 0.03236 0.02230 -0.0715 0.8760 0.0420
-8.000 -0.5016 0.03093 0.02084 -0.0724 0.8742 0.0437
-7.750 -0.4738 0.02984 0.01972 -0.0729 0.8723 0.0455
-7.500 -0.4426 0.02873 0.01854 -0.0739 0.8708 0.0471
-7.250 -0.4135 0.02777 0.01749 -0.0744 0.8694 0.0488
-7.000 -0.3895 0.02710 0.01669 -0.0741 0.8677 0.0510
-6.750 -0.3740 0.02647 0.01614 -0.0728 0.8647 0.0534
-6.500 -0.3604 0.02605 0.01572 -0.0709 0.8616 0.0558
-6.250 -0.3472 0.02565 0.01524 -0.0688 0.8585 0.0581
-6.000 -0.3335 0.02525 0.01474 -0.0667 0.8558 0.0608
-5.750 -0.3199 0.02476 0.01425 -0.0646 0.8535 0.0645
-5.500 -0.3033 0.02438 0.01382 -0.0629 0.8518 0.0709
-5.250 -0.2957 0.02424 0.01371 -0.0600 0.8484 0.0773
-5.000 -0.2872 0.02407 0.01357 -0.0570 0.8452 0.0889
-4.750 -0.2795 0.02363 0.01339 -0.0540 0.8423 0.1243
-4.500 -0.2805 0.02268 0.01315 -0.0496 0.8392 0.2528
-4.250 -0.2877 0.02160 0.01287 -0.0439 0.8364 0.4072
-4.000 -0.2580 0.02209 0.01459 -0.0417 0.8358 0.6550
-3.750 -0.2694 0.02257 0.01504 -0.0349 0.8314 0.6878
-3.500 -0.2700 0.02334 0.01580 -0.0292 0.8274 0.7240
-3.250 -0.2565 0.02464 0.01708 -0.0247 0.8247 0.7637
-3.000 -0.1941 0.02699 0.01933 -0.0273 0.8252 0.7929
-2.750 -0.1705 0.02735 0.01958 -0.0264 0.8234 0.8019
-2.500 -0.1418 0.02763 0.01973 -0.0265 0.8221 0.8079
-2.250 -0.1297 0.02757 0.01957 -0.0240 0.8202 0.8164
-2.000 -0.0936 0.02773 0.01962 -0.0256 0.8192 0.8196
-1.750 -0.1329 0.02804 0.01996 -0.0142 0.8116 0.8318
-1.500 -0.1070 0.02827 0.02011 -0.0142 0.8091 0.8347
-1.250 -0.0823 0.02841 0.02017 -0.0140 0.8070 0.8384
-1.000 -0.0619 0.02840 0.02009 -0.0130 0.8049 0.8432
-0.750 -0.0482 0.02817 0.01979 -0.0109 0.8029 0.8491
-0.500 -0.0468 0.02855 0.02017 -0.0066 0.7977 0.8534
-0.250 -0.0425 0.02870 0.02029 -0.0029 0.7929 0.8592
0.000 -0.0353 0.02847 0.02001 0.0003 0.7895 0.8648
0.250 -0.0057 0.02848 0.01998 -0.0005 0.7876 0.8667
0.500 0.0273 0.02852 0.01998 -0.0018 0.7862 0.8684
1.000 0.0334 0.02880 0.02025 0.0057 0.7748 0.8776
1.250 0.0534 0.02865 0.02009 0.0066 0.7720 0.8818
1.500 0.0873 0.02869 0.02012 0.0052 0.7702 0.8833
2.000 0.1119 0.02910 0.02057 0.0093 0.7588 0.8905
2.250 0.1394 0.02907 0.02056 0.0090 0.7559 0.8937
2.500 0.1686 0.02897 0.02048 0.0085 0.7538 0.8969
2.750 0.1720 0.02933 0.02088 0.0119 0.7449 0.9013
3.000 0.2008 0.02937 0.02097 0.0113 0.7411 0.9037
3.250 0.2342 0.02930 0.02096 0.0101 0.7386 0.9059
3.750 0.2668 0.02953 0.02131 0.0130 0.7254 0.9152
4.000 0.3053 0.02934 0.02121 0.0111 0.7225 0.9170
4.250 0.3205 0.02946 0.02142 0.0127 0.7120 0.9217
4.500 0.3599 0.02887 0.02092 0.0112 0.7072 0.9238
4.750 0.3723 0.02881 0.02095 0.0135 0.6963 0.9299
5.000 0.4131 0.02816 0.02043 0.0118 0.6911 0.9315
5.250 0.4308 0.02836 0.02075 0.0127 0.6800 0.9362
5.500 0.4737 0.02729 0.01985 0.0112 0.6742 0.9382
5.750 0.4928 0.02671 0.01939 0.0130 0.6589 0.9446
6.000 0.5082 0.02658 0.01939 0.0144 0.6318 0.9505
6.250 0.5232 0.02623 0.01914 0.0163 0.5952 0.9584
6.500 0.5925 0.02188 0.01366 0.0162 0.4059 0.9553
6.750 0.5972 0.02328 0.01436 0.0184 0.2887 0.9624
7.000 0.6039 0.02498 0.01523 0.0198 0.1538 0.9694
7.250 0.6216 0.02631 0.01604 0.0198 0.0781 0.9746
7.750 0.6681 0.02823 0.01786 0.0186 0.0519 0.9854
8.000 0.6913 0.02922 0.01891 0.0178 0.0482 0.9914
8.250 0.7102 0.03016 0.01994 0.0177 0.0460 1.0000
8.500 0.7074 0.03060 0.02040 0.0219 0.0448 1.0000
8.750 0.7113 0.03130 0.02111 0.0247 0.0437 1.0000
9.000 0.7187 0.03225 0.02205 0.0268 0.0427 1.0000
9.250 0.7308 0.03316 0.02302 0.0283 0.0419 1.0000
9.500 0.7455 0.03409 0.02401 0.0294 0.0409 1.0000
9.750 0.7623 0.03504 0.02502 0.0304 0.0394 1.0000
10.000 0.7804 0.03602 0.02602 0.0311 0.0380 1.0000
10.250 0.8016 0.03708 0.02708 0.0315 0.0370 1.0000
10.500 0.8270 0.03820 0.02818 0.0315 0.0363 1.0000
10.750 0.8539 0.03946 0.02953 0.0314 0.0352 1.0000
11.000 0.8778 0.04079 0.03105 0.0316 0.0343 1.0000
11.250 0.8995 0.04227 0.03273 0.0318 0.0331 1.0000
11.500 0.9220 0.04398 0.03462 0.0320 0.0325 1.0000
11.750 0.9413 0.04584 0.03668 0.0323 0.0320 1.0000
12.000 0.9572 0.04778 0.03878 0.0329 0.0314 1.0000
12.250 0.9698 0.04974 0.04090 0.0337 0.0308 1.0000
12.500 0.9841 0.05193 0.04315 0.0340 0.0301 1.0000
12.750 0.9849 0.05438 0.04589 0.0357 0.0298 1.0000
13.000 0.9796 0.05705 0.04891 0.0376 0.0295 1.0000
13.250 0.9711 0.06002 0.05221 0.0395 0.0292 1.0000
13.500 0.9626 0.06314 0.05560 0.0409 0.0291 1.0000
13.750 0.9500 0.06669 0.05945 0.0422 0.0290 1.0000
14.000 0.9358 0.07049 0.06350 0.0430 0.0289 1.0000
14.250 0.9177 0.07481 0.06808 0.0435 0.0289 1.0000
14.500 0.9000 0.07932 0.07282 0.0433 0.0290 1.0000
14.750 0.8782 0.08459 0.07833 0.0423 0.0290 1.0000
15.000 0.8555 0.09046 0.08441 0.0405 0.0291 1.0000
15.250 0.8346 0.09678 0.09090 0.0378 0.0293 1.0000
15.500 0.8078 0.10479 0.09909 0.0336 0.0294 1.0000
15.750 0.7810 0.11401 0.10845 0.0281 0.0296 1.0000
16.000 0.7625 0.12265 0.11718 0.0229 0.0299 1.0000
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