NACA 66(2)-415 (naca662415-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(2)-415 (naca662415-il) Reynolds number: 200,000 Max Cl/Cd: 55.31 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca662415-il-200000-n5.txt Download as CSV file: xf-naca662415-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-415
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3884 0.08377 0.07990 -0.0975 0.9556 0.0237
-12.000 -0.4388 0.06521 0.06110 -0.1130 0.9478 0.0229
-11.750 -0.4705 0.05732 0.05291 -0.1179 0.9372 0.0227
-11.500 -0.4878 0.05278 0.04813 -0.1192 0.9275 0.0229
-11.250 -0.5040 0.04886 0.04392 -0.1190 0.9185 0.0230
-11.000 -0.5196 0.04578 0.04059 -0.1168 0.9090 0.0231
-10.500 -0.5438 0.04075 0.03500 -0.1101 0.8933 0.0234
-10.250 -0.5500 0.03850 0.03243 -0.1066 0.8875 0.0238
-10.000 -0.5501 0.03628 0.02988 -0.1037 0.8820 0.0241
-9.750 -0.5467 0.03421 0.02744 -0.1010 0.8765 0.0245
-9.500 -0.5400 0.03233 0.02510 -0.0985 0.8722 0.0253
-9.250 -0.5268 0.03065 0.02314 -0.0970 0.8689 0.0259
-9.000 -0.5103 0.02934 0.02172 -0.0960 0.8650 0.0264
-8.750 -0.4920 0.02816 0.02039 -0.0951 0.8614 0.0269
-8.500 -0.4718 0.02703 0.01909 -0.0944 0.8584 0.0275
-8.250 -0.4498 0.02591 0.01781 -0.0939 0.8560 0.0281
-8.000 -0.4263 0.02483 0.01655 -0.0935 0.8539 0.0288
-7.750 -0.4039 0.02396 0.01554 -0.0930 0.8510 0.0297
-7.500 -0.3814 0.02324 0.01464 -0.0924 0.8480 0.0308
-7.250 -0.3577 0.02253 0.01380 -0.0920 0.8452 0.0315
-7.000 -0.3315 0.02138 0.01266 -0.0921 0.8429 0.0324
-6.750 -0.3076 0.02065 0.01190 -0.0918 0.8407 0.0334
-6.500 -0.2841 0.01999 0.01121 -0.0914 0.8386 0.0343
-6.250 -0.2622 0.01947 0.01065 -0.0907 0.8363 0.0356
-6.000 -0.2423 0.01906 0.01021 -0.0896 0.8333 0.0371
-5.750 -0.2219 0.01866 0.00975 -0.0886 0.8306 0.0384
-5.500 -0.2034 0.01811 0.00919 -0.0874 0.8281 0.0396
-5.250 -0.1845 0.01761 0.00869 -0.0862 0.8258 0.0410
-5.000 -0.1639 0.01722 0.00825 -0.0853 0.8239 0.0429
-4.750 -0.1419 0.01689 0.00787 -0.0845 0.8223 0.0455
-4.500 -0.1212 0.01662 0.00756 -0.0836 0.8202 0.0480
-4.250 -0.1030 0.01636 0.00731 -0.0822 0.8173 0.0513
-4.000 -0.0824 0.01614 0.00707 -0.0812 0.8147 0.0556
-3.750 -0.0615 0.01586 0.00683 -0.0803 0.8122 0.0651
-3.500 -0.0419 0.01540 0.00655 -0.0792 0.8102 0.1016
-3.250 -0.0292 0.01437 0.00618 -0.0774 0.8083 0.2591
-3.000 -0.0211 0.01299 0.00581 -0.0749 0.8065 0.4932
-2.750 -0.0054 0.01298 0.00655 -0.0718 0.8047 0.6828
-2.500 0.0143 0.01350 0.00715 -0.0698 0.8021 0.7252
-2.250 0.0358 0.01396 0.00759 -0.0683 0.7997 0.7486
-2.000 0.0591 0.01437 0.00800 -0.0669 0.7976 0.7612
-1.750 0.0830 0.01472 0.00833 -0.0657 0.7956 0.7728
-1.500 0.1080 0.01493 0.00847 -0.0650 0.7940 0.7840
-1.250 0.1340 0.01512 0.00865 -0.0644 0.7927 0.7879
-1.000 0.1614 0.01517 0.00865 -0.0645 0.7915 0.7909
-0.750 0.1895 0.01518 0.00861 -0.0648 0.7904 0.7939
-0.500 0.2141 0.01524 0.00863 -0.0647 0.7886 0.7974
-0.250 0.2325 0.01540 0.00878 -0.0636 0.7849 0.8006
0.000 0.2551 0.01553 0.00892 -0.0629 0.7825 0.8020
0.250 0.2800 0.01561 0.00898 -0.0626 0.7803 0.8036
0.500 0.3071 0.01563 0.00900 -0.0627 0.7785 0.8054
0.750 0.3360 0.01560 0.00896 -0.0632 0.7768 0.8070
1.000 0.3664 0.01554 0.00889 -0.0640 0.7754 0.8086
1.250 0.3975 0.01548 0.00882 -0.0649 0.7742 0.8103
1.500 0.4084 0.01586 0.00925 -0.0623 0.7684 0.8132
1.750 0.4332 0.01592 0.00933 -0.0622 0.7652 0.8158
2.000 0.4617 0.01588 0.00931 -0.0626 0.7628 0.8175
2.250 0.4923 0.01579 0.00927 -0.0632 0.7609 0.8188
2.500 0.5244 0.01569 0.00919 -0.0641 0.7592 0.8201
2.750 0.5384 0.01600 0.00958 -0.0619 0.7540 0.8222
3.000 0.5594 0.01613 0.00977 -0.0610 0.7496 0.8244
3.250 0.5895 0.01603 0.00973 -0.0615 0.7468 0.8262
3.500 0.6250 0.01576 0.00951 -0.0630 0.7443 0.8278
3.750 0.6429 0.01578 0.00960 -0.0614 0.7366 0.8306
4.000 0.6837 0.01502 0.00886 -0.0633 0.7287 0.8324
4.250 0.7006 0.01481 0.00873 -0.0610 0.7167 0.8347
4.500 0.7217 0.01451 0.00850 -0.0594 0.7040 0.8368
4.750 0.7412 0.01428 0.00834 -0.0576 0.6893 0.8392
5.000 0.7597 0.01393 0.00800 -0.0554 0.6653 0.8420
5.250 0.7649 0.01383 0.00788 -0.0509 0.6234 0.8458
5.750 0.7710 0.01484 0.00771 -0.0414 0.4287 0.8524
6.000 0.7633 0.01597 0.00851 -0.0357 0.3600 0.8568
6.250 0.7577 0.01725 0.00942 -0.0309 0.2895 0.8618
6.500 0.7544 0.01860 0.01039 -0.0267 0.2161 0.8665
6.750 0.7531 0.01992 0.01135 -0.0229 0.1439 0.8709
7.000 0.7561 0.02121 0.01230 -0.0199 0.0847 0.8756
7.250 0.7668 0.02219 0.01314 -0.0180 0.0593 0.8802
7.500 0.7788 0.02297 0.01389 -0.0161 0.0496 0.8840
7.750 0.7927 0.02367 0.01463 -0.0145 0.0445 0.8885
8.000 0.8063 0.02449 0.01546 -0.0131 0.0412 0.8936
8.250 0.8213 0.02520 0.01626 -0.0118 0.0385 0.8984
8.500 0.8344 0.02598 0.01711 -0.0102 0.0361 0.9038
8.750 0.8453 0.02701 0.01818 -0.0086 0.0341 0.9103
9.000 0.8581 0.02783 0.01909 -0.0070 0.0327 0.9170
9.250 0.8713 0.02869 0.02003 -0.0056 0.0311 0.9250
9.500 0.8839 0.02959 0.02100 -0.0042 0.0295 0.9338
9.750 0.8967 0.03059 0.02206 -0.0031 0.0283 0.9441
10.000 0.9093 0.03190 0.02338 -0.0022 0.0273 0.9565
10.250 0.9279 0.03283 0.02445 -0.0022 0.0264 0.9801
10.750 0.9617 0.03502 0.02678 -0.0012 0.0247 1.0000
11.000 0.9790 0.03615 0.02797 -0.0008 0.0238 1.0000
11.250 0.9959 0.03732 0.02916 -0.0005 0.0230 1.0000
11.500 1.0133 0.03859 0.03041 -0.0002 0.0222 1.0000
11.750 1.0316 0.03984 0.03177 0.0002 0.0216 1.0000
12.000 1.0499 0.04115 0.03322 0.0005 0.0209 1.0000
12.250 1.0679 0.04256 0.03478 0.0009 0.0204 1.0000
12.500 1.0851 0.04411 0.03647 0.0013 0.0200 1.0000
12.750 1.0999 0.04573 0.03826 0.0018 0.0195 1.0000
13.000 1.1129 0.04751 0.04019 0.0024 0.0191 1.0000
13.250 1.1243 0.04942 0.04226 0.0030 0.0188 1.0000
13.500 1.1333 0.05145 0.04444 0.0037 0.0186 1.0000
13.750 1.1404 0.05358 0.04673 0.0044 0.0183 1.0000
14.000 1.1457 0.05597 0.04928 0.0052 0.0182 1.0000
14.250 1.1490 0.05849 0.05196 0.0058 0.0180 1.0000
14.500 1.1502 0.06128 0.05492 0.0065 0.0178 1.0000
14.750 1.1494 0.06436 0.05817 0.0070 0.0177 1.0000
15.000 1.1404 0.06812 0.06219 0.0075 0.0175 1.0000
15.250 1.1284 0.07229 0.06664 0.0078 0.0174 1.0000
15.500 1.1130 0.07705 0.07169 0.0076 0.0173 1.0000
15.750 1.0968 0.08226 0.07716 0.0068 0.0173 1.0000
16.000 1.0768 0.08825 0.08343 0.0052 0.0171 1.0000
16.250 1.0566 0.09476 0.09019 0.0028 0.0171 1.0000
16.500 1.0334 0.10233 0.09801 -0.0006 0.0170 1.0000
16.750 1.0115 0.11036 0.10624 -0.0049 0.0171 1.0000
17.000 0.9856 0.11992 0.11601 -0.0106 0.0172 1.0000
17.250 0.9576 0.13101 0.12728 -0.0178 0.0173 1.0000
17.500 0.9294 0.14347 0.13988 -0.0258 0.0175 1.0000
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Polar data table (+)
Polar graphs
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