NACA 66(3)-218 (naca663218-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(3)-218 (naca663218-il) Reynolds number: 200,000 Max Cl/Cd: 41.47 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca663218-il-200000-n5.txt Download as CSV file: xf-naca663218-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(3)-218
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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.6453 0.09591 0.09157 -0.0806 1.0000 0.0226
-16.250 -0.6729 0.08742 0.08292 -0.0856 1.0000 0.0225
-15.750 -0.7194 0.07195 0.06693 -0.0959 0.9640 0.0225
-15.500 -0.7358 0.06598 0.06064 -0.0996 0.9546 0.0225
-15.250 -0.7483 0.06106 0.05542 -0.1020 0.9460 0.0225
-15.000 -0.7614 0.05673 0.05075 -0.1032 0.9367 0.0226
-14.750 -0.7633 0.05382 0.04766 -0.1036 0.9283 0.0228
-14.500 -0.7611 0.05150 0.04520 -0.1037 0.9205 0.0231
-14.250 -0.7593 0.04942 0.04298 -0.1033 0.9130 0.0233
-14.000 -0.7565 0.04759 0.04102 -0.1027 0.9059 0.0236
-13.750 -0.7547 0.04555 0.03877 -0.1018 0.8998 0.0238
-13.500 -0.7514 0.04373 0.03678 -0.1006 0.8933 0.0240
-13.250 -0.7456 0.04206 0.03492 -0.0996 0.8878 0.0243
-13.000 -0.7387 0.04042 0.03309 -0.0984 0.8828 0.0247
-12.750 -0.7288 0.03884 0.03133 -0.0974 0.8777 0.0249
-12.500 -0.7166 0.03737 0.02966 -0.0965 0.8734 0.0251
-12.250 -0.7025 0.03601 0.02809 -0.0956 0.8697 0.0256
-12.000 -0.6863 0.03477 0.02666 -0.0949 0.8661 0.0260
-11.750 -0.6688 0.03365 0.02538 -0.0943 0.8623 0.0264
-11.500 -0.6498 0.03263 0.02420 -0.0938 0.8587 0.0268
-11.250 -0.6288 0.03164 0.02313 -0.0934 0.8556 0.0273
-11.000 -0.6097 0.03079 0.02225 -0.0929 0.8527 0.0278
-10.750 -0.5913 0.03002 0.02142 -0.0923 0.8499 0.0283
-10.500 -0.5735 0.02927 0.02065 -0.0917 0.8466 0.0293
-10.250 -0.5553 0.02856 0.01987 -0.0910 0.8434 0.0303
-10.000 -0.5367 0.02785 0.01908 -0.0903 0.8404 0.0311
-9.750 -0.5185 0.02717 0.01830 -0.0895 0.8376 0.0318
-9.500 -0.5026 0.02637 0.01748 -0.0884 0.8350 0.0327
-9.250 -0.4870 0.02566 0.01674 -0.0873 0.8324 0.0335
-9.000 -0.4716 0.02499 0.01607 -0.0863 0.8293 0.0346
-8.750 -0.4561 0.02436 0.01540 -0.0852 0.8264 0.0357
-8.500 -0.4407 0.02375 0.01472 -0.0840 0.8237 0.0369
-8.250 -0.4262 0.02311 0.01406 -0.0827 0.8212 0.0389
-8.000 -0.4114 0.02250 0.01343 -0.0814 0.8190 0.0407
-7.750 -0.3956 0.02197 0.01283 -0.0801 0.8170 0.0433
-7.500 -0.3805 0.02142 0.01224 -0.0788 0.8150 0.0454
-7.250 -0.3656 0.02090 0.01174 -0.0775 0.8125 0.0487
-7.000 -0.3501 0.02042 0.01125 -0.0761 0.8100 0.0534
-6.750 -0.3350 0.01993 0.01078 -0.0747 0.8077 0.0604
-6.500 -0.3216 0.01937 0.01028 -0.0730 0.8055 0.0736
-6.250 -0.3106 0.01873 0.00978 -0.0710 0.8034 0.0991
-6.000 -0.3062 0.01784 0.00919 -0.0680 0.8014 0.1569
-5.750 -0.3048 0.01693 0.00859 -0.0644 0.7993 0.2238
-5.500 -0.3094 0.01615 0.00813 -0.0596 0.7964 0.2894
-5.250 -0.3209 0.01558 0.00788 -0.0533 0.7931 0.3503
-5.000 -0.3310 0.01493 0.00761 -0.0470 0.7901 0.4281
-4.750 -0.3346 0.01434 0.00756 -0.0414 0.7878 0.5251
-4.500 -0.3077 0.01491 0.00864 -0.0402 0.7866 0.6323
-4.250 -0.2908 0.01509 0.00876 -0.0381 0.7850 0.6640
-4.000 -0.2700 0.01557 0.00920 -0.0365 0.7838 0.6909
-3.750 -0.2386 0.01657 0.01020 -0.0361 0.7829 0.7107
-3.500 -0.2149 0.01694 0.01049 -0.0351 0.7819 0.7223
-3.250 -0.1800 0.01761 0.01113 -0.0358 0.7810 0.7269
-3.000 -0.1628 0.01783 0.01132 -0.0342 0.7785 0.7338
-2.750 -0.1446 0.01791 0.01135 -0.0328 0.7761 0.7389
-2.500 -0.1177 0.01815 0.01156 -0.0327 0.7744 0.7409
-2.250 -0.0921 0.01833 0.01171 -0.0324 0.7729 0.7433
-2.000 -0.0685 0.01842 0.01176 -0.0319 0.7714 0.7464
-1.750 -0.0498 0.01832 0.01161 -0.0308 0.7698 0.7512
-1.500 -0.0302 0.01816 0.01138 -0.0299 0.7685 0.7552
-1.250 -0.0027 0.01823 0.01143 -0.0300 0.7674 0.7566
-1.000 0.0251 0.01826 0.01142 -0.0302 0.7664 0.7580
-0.750 0.0525 0.01827 0.01140 -0.0304 0.7654 0.7595
-0.500 0.0793 0.01828 0.01139 -0.0306 0.7646 0.7613
-0.250 0.0845 0.01871 0.01187 -0.0272 0.7602 0.7645
0.000 0.0984 0.01881 0.01197 -0.0253 0.7569 0.7674
0.250 0.1177 0.01874 0.01186 -0.0244 0.7545 0.7704
0.500 0.1418 0.01863 0.01173 -0.0243 0.7527 0.7722
0.750 0.1690 0.01860 0.01170 -0.0245 0.7512 0.7730
1.000 0.1972 0.01857 0.01168 -0.0248 0.7501 0.7740
1.250 0.2266 0.01853 0.01165 -0.0253 0.7490 0.7751
1.500 0.2568 0.01848 0.01160 -0.0260 0.7480 0.7762
2.000 0.2690 0.01927 0.01251 -0.0194 0.7368 0.7800
2.250 0.2986 0.01914 0.01239 -0.0200 0.7351 0.7813
2.500 0.3302 0.01897 0.01223 -0.0209 0.7337 0.7826
2.750 0.3630 0.01878 0.01207 -0.0221 0.7325 0.7839
3.000 0.3971 0.01857 0.01188 -0.0235 0.7314 0.7853
3.500 0.4104 0.01920 0.01262 -0.0171 0.7186 0.7902
3.750 0.4476 0.01885 0.01232 -0.0188 0.7171 0.7910
4.250 0.4707 0.01904 0.01265 -0.0133 0.7042 0.7940
4.500 0.5124 0.01849 0.01217 -0.0156 0.7018 0.7949
4.750 0.5617 0.01774 0.01149 -0.0191 0.6995 0.7957
5.000 0.5420 0.01836 0.01218 -0.0111 0.6879 0.7987
5.250 0.5912 0.01742 0.01130 -0.0144 0.6840 0.7996
5.500 0.5853 0.01774 0.01168 -0.0088 0.6704 0.8026
5.750 0.6038 0.01716 0.01111 -0.0068 0.6509 0.8049
6.000 0.5836 0.01859 0.01260 -0.0001 0.6263 0.8082
6.250 0.6544 0.01578 0.00935 -0.0045 0.5372 0.8084
6.500 0.6618 0.01624 0.00936 -0.0009 0.4659 0.8105
6.750 0.6568 0.01725 0.01007 0.0040 0.4074 0.8132
7.000 0.6509 0.01843 0.01096 0.0086 0.3502 0.8161
7.250 0.6473 0.01965 0.01190 0.0125 0.2962 0.8192
7.500 0.6457 0.02092 0.01287 0.0159 0.2410 0.8222
7.750 0.6468 0.02218 0.01382 0.0188 0.1852 0.8250
8.000 0.6491 0.02340 0.01476 0.0215 0.1313 0.8272
8.250 0.6541 0.02458 0.01570 0.0239 0.0891 0.8297
8.500 0.6637 0.02555 0.01654 0.0256 0.0667 0.8324
8.750 0.6762 0.02640 0.01735 0.0270 0.0549 0.8352
9.000 0.6893 0.02724 0.01817 0.0282 0.0474 0.8382
9.250 0.7032 0.02808 0.01901 0.0292 0.0426 0.8413
9.500 0.7166 0.02888 0.01988 0.0304 0.0398 0.8438
9.750 0.7293 0.02973 0.02079 0.0317 0.0372 0.8467
10.000 0.7409 0.03070 0.02179 0.0330 0.0347 0.8501
10.250 0.7543 0.03159 0.02276 0.0340 0.0330 0.8538
10.500 0.7668 0.03258 0.02378 0.0350 0.0311 0.8576
10.750 0.7770 0.03366 0.02491 0.0363 0.0302 0.8610
11.000 0.7880 0.03470 0.02603 0.0375 0.0292 0.8645
11.250 0.7996 0.03576 0.02719 0.0386 0.0282 0.8684
11.500 0.8118 0.03686 0.02835 0.0396 0.0272 0.8726
11.750 0.8238 0.03798 0.02953 0.0404 0.0265 0.8767
12.000 0.8347 0.03914 0.03075 0.0415 0.0259 0.8807
12.250 0.8458 0.04040 0.03202 0.0424 0.0253 0.8853
12.500 0.8594 0.04155 0.03326 0.0431 0.0248 0.8903
12.750 0.8732 0.04267 0.03450 0.0438 0.0242 0.8951
13.000 0.8861 0.04384 0.03579 0.0445 0.0234 0.9006
13.250 0.8992 0.04506 0.03710 0.0451 0.0228 0.9068
13.500 0.9118 0.04629 0.03842 0.0457 0.0223 0.9133
13.750 0.9234 0.04762 0.03982 0.0462 0.0217 0.9215
14.000 0.9366 0.04894 0.04122 0.0466 0.0214 0.9301
14.250 0.9514 0.05034 0.04268 0.0467 0.0212 0.9399
14.750 0.9823 0.05387 0.04659 0.0455 0.0205 0.9652
15.250 0.9990 0.05791 0.05098 0.0457 0.0201 1.0000
15.500 1.0037 0.06039 0.05365 0.0458 0.0198 1.0000
15.750 1.0069 0.06309 0.05654 0.0458 0.0196 1.0000
16.000 1.0081 0.06600 0.05962 0.0457 0.0195 1.0000
16.250 1.0058 0.06930 0.06312 0.0455 0.0192 1.0000
16.500 1.0019 0.07288 0.06692 0.0450 0.0192 1.0000
16.750 0.9952 0.07689 0.07113 0.0443 0.0191 1.0000
17.000 0.9857 0.08141 0.07586 0.0432 0.0190 1.0000
17.250 0.9737 0.08646 0.08113 0.0417 0.0189 1.0000
17.500 0.9582 0.09224 0.08714 0.0395 0.0189 1.0000
17.750 0.9398 0.09882 0.09395 0.0366 0.0189 1.0000
18.000 0.9170 0.10657 0.10195 0.0328 0.0190 1.0000
18.250 0.8880 0.11608 0.11171 0.0274 0.0190 1.0000
18.500 0.8390 0.13099 0.12695 0.0185 0.0193 1.0000
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