NACA 66(3)-218 (naca663218-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(3)-218 (naca663218-il) Reynolds number: 500,000 Max Cl/Cd: 76.42 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca663218-il-500000.txt Download as CSV file: xf-naca663218-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.4713 0.09470 0.09197 -0.0840 0.8952 0.0286
-15.750 -0.4757 0.09026 0.08750 -0.0867 0.8927 0.0288
-15.500 -0.7386 0.06116 0.05738 -0.1074 0.9499 0.0233
-15.250 -0.7578 0.05644 0.05236 -0.1089 0.9374 0.0233
-15.000 -0.7697 0.05277 0.04848 -0.1086 0.9266 0.0232
-14.750 -0.7861 0.04944 0.04488 -0.1071 0.9163 0.0232
-14.500 -0.7966 0.04655 0.04178 -0.1053 0.9079 0.0231
-14.250 -0.8067 0.04428 0.03927 -0.1032 0.8999 0.0232
-14.000 -0.8141 0.04199 0.03675 -0.1009 0.8931 0.0233
-13.750 -0.8192 0.04008 0.03462 -0.0986 0.8865 0.0234
-13.500 -0.8281 0.03892 0.03321 -0.0954 0.8802 0.0235
-13.250 -0.8217 0.03622 0.03029 -0.0941 0.8756 0.0237
-13.000 -0.8043 0.03397 0.02788 -0.0938 0.8716 0.0240
-12.750 -0.7885 0.03259 0.02641 -0.0932 0.8676 0.0243
-12.500 -0.7719 0.03136 0.02504 -0.0925 0.8638 0.0245
-12.250 -0.7553 0.03028 0.02388 -0.0918 0.8601 0.0249
-12.000 -0.7362 0.02925 0.02277 -0.0913 0.8564 0.0251
-11.750 -0.7169 0.02833 0.02176 -0.0908 0.8529 0.0255
-11.500 -0.6964 0.02743 0.02076 -0.0903 0.8496 0.0259
-11.250 -0.6748 0.02661 0.01982 -0.0899 0.8464 0.0263
-11.000 -0.6534 0.02583 0.01897 -0.0896 0.8435 0.0267
-10.750 -0.6323 0.02510 0.01815 -0.0891 0.8403 0.0273
-10.500 -0.6139 0.02452 0.01748 -0.0883 0.8372 0.0278
-10.250 -0.5877 0.02365 0.01656 -0.0884 0.8348 0.0284
-10.000 -0.5673 0.02293 0.01585 -0.0878 0.8323 0.0292
-9.750 -0.5486 0.02234 0.01522 -0.0870 0.8296 0.0297
-9.500 -0.5306 0.02176 0.01463 -0.0862 0.8273 0.0305
-9.250 -0.5131 0.02116 0.01401 -0.0852 0.8246 0.0311
-9.000 -0.4956 0.02062 0.01343 -0.0842 0.8220 0.0320
-8.750 -0.4783 0.02009 0.01285 -0.0832 0.8195 0.0327
-8.500 -0.4639 0.01940 0.01212 -0.0817 0.8172 0.0336
-8.250 -0.4506 0.01873 0.01143 -0.0802 0.8149 0.0347
-8.000 -0.4345 0.01826 0.01095 -0.0789 0.8127 0.0362
-7.750 -0.4173 0.01783 0.01050 -0.0778 0.8107 0.0380
-7.500 -0.4015 0.01733 0.00997 -0.0765 0.8087 0.0393
-7.250 -0.3891 0.01669 0.00935 -0.0746 0.8064 0.0418
-7.000 -0.3723 0.01626 0.00891 -0.0733 0.8043 0.0440
-6.750 -0.3564 0.01581 0.00843 -0.0719 0.8022 0.0471
-6.500 -0.3409 0.01534 0.00798 -0.0703 0.8002 0.0522
-6.250 -0.3261 0.01486 0.00753 -0.0686 0.7984 0.0608
-6.000 -0.3153 0.01427 0.00706 -0.0663 0.7966 0.0860
-5.750 -0.3189 0.01324 0.00645 -0.0618 0.7945 0.1662
-5.500 -0.3264 0.01231 0.00592 -0.0564 0.7923 0.2473
-5.250 -0.3377 0.01168 0.00560 -0.0498 0.7899 0.3169
-5.000 -0.3452 0.01086 0.00521 -0.0439 0.7876 0.4096
-4.750 -0.3498 0.00993 0.00477 -0.0384 0.7856 0.5184
-4.500 -0.3415 0.00952 0.00487 -0.0348 0.7840 0.6386
-4.250 -0.3165 0.00963 0.00496 -0.0344 0.7829 0.6681
-4.000 -0.2900 0.00978 0.00506 -0.0342 0.7818 0.6842
-3.750 -0.2619 0.00998 0.00525 -0.0343 0.7808 0.6954
-3.500 -0.2341 0.01022 0.00546 -0.0343 0.7797 0.7063
-3.250 -0.2073 0.01062 0.00581 -0.0340 0.7784 0.7189
-3.000 -0.1771 0.01118 0.00646 -0.0341 0.7775 0.7297
-2.750 -0.1497 0.01149 0.00678 -0.0340 0.7764 0.7376
-2.500 -0.1190 0.01202 0.00737 -0.0342 0.7754 0.7436
-2.250 -0.0917 0.01227 0.00760 -0.0342 0.7742 0.7491
-2.000 -0.0657 0.01235 0.00765 -0.0342 0.7730 0.7530
-1.750 -0.0376 0.01245 0.00775 -0.0345 0.7719 0.7548
-1.500 -0.0096 0.01256 0.00786 -0.0347 0.7707 0.7565
-1.250 0.0185 0.01266 0.00796 -0.0350 0.7694 0.7585
-1.000 0.0464 0.01275 0.00804 -0.0352 0.7683 0.7608
-0.750 0.0738 0.01280 0.00808 -0.0355 0.7673 0.7629
-0.500 0.1010 0.01280 0.00806 -0.0358 0.7663 0.7650
-0.250 0.1284 0.01277 0.00800 -0.0362 0.7652 0.7670
0.000 0.1563 0.01275 0.00794 -0.0367 0.7641 0.7688
0.250 0.1847 0.01270 0.00787 -0.0372 0.7629 0.7701
0.500 0.2128 0.01275 0.00792 -0.0375 0.7615 0.7711
0.750 0.2373 0.01279 0.00801 -0.0373 0.7597 0.7722
1.000 0.2623 0.01284 0.00809 -0.0372 0.7576 0.7731
1.250 0.2887 0.01284 0.00812 -0.0373 0.7553 0.7741
1.500 0.3163 0.01280 0.00809 -0.0376 0.7530 0.7750
1.750 0.3451 0.01274 0.00804 -0.0381 0.7511 0.7762
2.000 0.3745 0.01268 0.00798 -0.0386 0.7494 0.7774
2.250 0.4044 0.01260 0.00791 -0.0393 0.7478 0.7785
2.500 0.4355 0.01252 0.00782 -0.0402 0.7461 0.7795
2.750 0.4612 0.01250 0.00784 -0.0401 0.7429 0.7807
3.000 0.4866 0.01240 0.00778 -0.0400 0.7386 0.7820
3.250 0.5170 0.01215 0.00754 -0.0406 0.7348 0.7831
3.500 0.5509 0.01181 0.00718 -0.0418 0.7312 0.7842
3.750 0.5804 0.01160 0.00697 -0.0423 0.7262 0.7852
4.000 0.6071 0.01128 0.00668 -0.0421 0.7188 0.7863
4.250 0.6379 0.01075 0.00613 -0.0424 0.7090 0.7875
4.500 0.6667 0.01029 0.00562 -0.0424 0.6966 0.7887
4.750 0.6873 0.01013 0.00556 -0.0410 0.6856 0.7900
5.000 0.7107 0.00999 0.00546 -0.0402 0.6743 0.7912
5.250 0.7325 0.00989 0.00540 -0.0391 0.6599 0.7926
5.500 0.7504 0.00982 0.00534 -0.0372 0.6357 0.7941
5.750 0.7551 0.00991 0.00523 -0.0327 0.5758 0.7961
6.000 0.7358 0.01046 0.00544 -0.0237 0.5184 0.7988
6.250 0.7193 0.01140 0.00610 -0.0159 0.4646 0.8016
6.500 0.7063 0.01250 0.00694 -0.0093 0.4111 0.8040
6.750 0.6949 0.01365 0.00784 -0.0034 0.3548 0.8065
7.000 0.6878 0.01487 0.00879 0.0015 0.2984 0.8089
7.250 0.6830 0.01612 0.00976 0.0059 0.2384 0.8115
7.500 0.6800 0.01742 0.01071 0.0098 0.1743 0.8142
7.750 0.6783 0.01876 0.01168 0.0133 0.1076 0.8171
8.000 0.6817 0.01996 0.01259 0.0161 0.0643 0.8197
8.250 0.6926 0.02079 0.01333 0.0178 0.0500 0.8219
8.500 0.7054 0.02150 0.01403 0.0194 0.0433 0.8243
8.750 0.7203 0.02214 0.01471 0.0207 0.0398 0.8266
9.000 0.7315 0.02301 0.01558 0.0223 0.0363 0.8293
9.250 0.7470 0.02366 0.01628 0.0234 0.0346 0.8320
9.500 0.7614 0.02440 0.01704 0.0246 0.0325 0.8349
9.750 0.7727 0.02535 0.01798 0.0260 0.0311 0.8377
10.000 0.7850 0.02621 0.01890 0.0274 0.0299 0.8406
10.250 0.7990 0.02696 0.01973 0.0285 0.0285 0.8436
10.500 0.8125 0.02779 0.02059 0.0297 0.0276 0.8468
10.750 0.8245 0.02874 0.02157 0.0309 0.0268 0.8503
11.000 0.8331 0.02999 0.02284 0.0324 0.0261 0.8538
11.250 0.8463 0.03091 0.02382 0.0334 0.0255 0.8572
11.500 0.8602 0.03177 0.02477 0.0345 0.0249 0.8609
11.750 0.8735 0.03273 0.02580 0.0355 0.0243 0.8648
12.000 0.8876 0.03367 0.02679 0.0364 0.0239 0.8692
12.250 0.9017 0.03463 0.02782 0.0372 0.0234 0.8734
12.500 0.9153 0.03556 0.02881 0.0382 0.0229 0.8779
12.750 0.9293 0.03654 0.02982 0.0390 0.0225 0.8829
13.000 0.9452 0.03753 0.03084 0.0396 0.0222 0.8877
13.250 0.9681 0.03853 0.03187 0.0399 0.0216 0.8914
13.500 0.9769 0.03962 0.03312 0.0411 0.0212 0.8977
13.750 0.9927 0.04071 0.03431 0.0417 0.0210 0.9037
14.000 1.0061 0.04184 0.03558 0.0426 0.0207 0.9099
14.250 1.0164 0.04310 0.03697 0.0435 0.0203 0.9179
14.500 1.0298 0.04439 0.03840 0.0444 0.0201 0.9259
14.750 1.0410 0.04577 0.03992 0.0452 0.0200 0.9363
15.000 1.0537 0.04746 0.04179 0.0455 0.0197 0.9486
15.250 1.0699 0.04946 0.04395 0.0443 0.0195 0.9618
15.500 1.0866 0.05143 0.04604 0.0424 0.0191 0.9933
15.750 1.0906 0.05367 0.04842 0.0433 0.0192 1.0000
16.000 1.0962 0.05600 0.05086 0.0435 0.0190 1.0000
16.250 1.0986 0.05859 0.05358 0.0437 0.0189 1.0000
16.500 1.1007 0.06105 0.05613 0.0437 0.0187 1.0000
16.750 1.0991 0.06408 0.05931 0.0438 0.0186 1.0000
17.000 1.0851 0.06875 0.06427 0.0439 0.0188 1.0000
17.250 1.0765 0.07272 0.06840 0.0436 0.0187 1.0000
17.500 1.0644 0.07721 0.07308 0.0429 0.0187 1.0000
17.750 1.0168 0.08699 0.08332 0.0406 0.0190 1.0000
18.000 0.9453 0.10196 0.09883 0.0350 0.0199 1.0000
18.250 0.9110 0.11199 0.10909 0.0296 0.0199 1.0000
18.500 0.8601 0.12658 0.12394 0.0210 0.0205 1.0000
18.750 0.8095 0.14318 0.14074 0.0109 0.0211 1.0000
19.000 0.7961 0.15096 0.14853 0.0067 0.0215 1.0000
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