NACA 66(3)-218 (naca663218-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 66(3)-218 (naca663218-il) Reynolds number: 500,000 Max Cl/Cd: 72.3 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca663218-il-500000-n5.txt Download as CSV file: xf-naca663218-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -0.7615 0.11292 0.10989 -0.0640 1.0000 0.0149
-18.750 -0.8054 0.10004 0.09674 -0.0714 1.0000 0.0148
-18.500 -0.8335 0.09104 0.08754 -0.0764 1.0000 0.0148
-18.250 -0.8549 0.08376 0.08007 -0.0803 1.0000 0.0149
-18.000 -0.8693 0.07686 0.07297 -0.0848 0.9695 0.0149
-17.750 -0.8758 0.07036 0.06622 -0.0904 0.9593 0.0150
-17.500 -0.8748 0.06518 0.06081 -0.0953 0.9504 0.0151
-17.250 -0.8743 0.06043 0.05584 -0.0992 0.9408 0.0152
-17.000 -0.8713 0.05679 0.05200 -0.1018 0.9293 0.0153
-16.750 -0.8710 0.05367 0.04866 -0.1030 0.9175 0.0154
-16.500 -0.8717 0.05093 0.04572 -0.1033 0.9063 0.0155
-16.250 -0.8706 0.04861 0.04322 -0.1031 0.8968 0.0155
-16.000 -0.8692 0.04641 0.04084 -0.1027 0.8880 0.0156
-15.750 -0.8660 0.04441 0.03871 -0.1022 0.8809 0.0157
-15.500 -0.8617 0.04259 0.03676 -0.1016 0.8738 0.0158
-15.250 -0.8560 0.04094 0.03499 -0.1009 0.8678 0.0159
-15.000 -0.8493 0.03939 0.03336 -0.1003 0.8623 0.0161
-14.750 -0.8411 0.03804 0.03190 -0.0996 0.8568 0.0162
-14.500 -0.8326 0.03674 0.03050 -0.0988 0.8519 0.0163
-14.250 -0.8228 0.03551 0.02920 -0.0980 0.8475 0.0165
-14.000 -0.8125 0.03438 0.02799 -0.0973 0.8430 0.0167
-13.750 -0.8015 0.03327 0.02679 -0.0964 0.8386 0.0168
-13.500 -0.7902 0.03224 0.02566 -0.0956 0.8346 0.0170
-13.250 -0.7780 0.03126 0.02460 -0.0948 0.8310 0.0173
-13.000 -0.7649 0.03036 0.02362 -0.0940 0.8272 0.0177
-12.750 -0.7522 0.02940 0.02259 -0.0930 0.8235 0.0178
-12.500 -0.7388 0.02855 0.02165 -0.0921 0.8200 0.0180
-12.250 -0.7251 0.02772 0.02072 -0.0912 0.8167 0.0183
-12.000 -0.7109 0.02690 0.01983 -0.0903 0.8138 0.0185
-11.750 -0.6962 0.02614 0.01900 -0.0894 0.8106 0.0188
-11.500 -0.6816 0.02540 0.01819 -0.0884 0.8073 0.0189
-11.250 -0.6694 0.02451 0.01726 -0.0871 0.8040 0.0192
-11.000 -0.6548 0.02382 0.01652 -0.0861 0.8010 0.0195
-10.750 -0.6404 0.02313 0.01577 -0.0850 0.7983 0.0197
-10.500 -0.6245 0.02251 0.01513 -0.0841 0.7957 0.0203
-10.250 -0.6084 0.02190 0.01449 -0.0831 0.7931 0.0207
-10.000 -0.5925 0.02131 0.01385 -0.0821 0.7905 0.0211
-9.750 -0.5763 0.02074 0.01324 -0.0811 0.7879 0.0215
-9.500 -0.5596 0.02021 0.01265 -0.0801 0.7856 0.0221
-9.250 -0.5429 0.01970 0.01208 -0.0790 0.7834 0.0225
-9.000 -0.5277 0.01911 0.01145 -0.0778 0.7813 0.0232
-8.750 -0.5108 0.01860 0.01095 -0.0767 0.7793 0.0238
-8.500 -0.4930 0.01815 0.01048 -0.0758 0.7772 0.0245
-8.250 -0.4750 0.01772 0.01003 -0.0748 0.7751 0.0257
-8.000 -0.4570 0.01730 0.00957 -0.0738 0.7730 0.0266
-7.750 -0.4397 0.01685 0.00911 -0.0727 0.7710 0.0278
-7.500 -0.4220 0.01643 0.00867 -0.0716 0.7692 0.0288
-7.250 -0.4037 0.01605 0.00826 -0.0706 0.7674 0.0303
-7.000 -0.3847 0.01572 0.00788 -0.0696 0.7658 0.0319
-6.750 -0.3669 0.01533 0.00750 -0.0685 0.7642 0.0339
-6.500 -0.3484 0.01498 0.00714 -0.0674 0.7626 0.0369
-6.250 -0.3301 0.01462 0.00681 -0.0663 0.7609 0.0402
-6.000 -0.3123 0.01426 0.00648 -0.0651 0.7591 0.0461
-5.750 -0.2953 0.01388 0.00614 -0.0637 0.7573 0.0557
-5.500 -0.2801 0.01345 0.00578 -0.0621 0.7554 0.0732
-5.250 -0.2683 0.01291 0.00539 -0.0598 0.7537 0.1042
-5.000 -0.2614 0.01227 0.00496 -0.0567 0.7520 0.1531
-4.750 -0.2584 0.01173 0.00461 -0.0527 0.7504 0.2034
-4.500 -0.2557 0.01123 0.00432 -0.0485 0.7488 0.2579
-4.250 -0.2507 0.01061 0.00399 -0.0449 0.7474 0.3278
-4.000 -0.2451 0.00992 0.00364 -0.0413 0.7459 0.4079
-3.750 -0.2393 0.00913 0.00326 -0.0378 0.7444 0.5005
-3.500 -0.2310 0.00851 0.00323 -0.0343 0.7429 0.6279
-3.250 -0.2055 0.00857 0.00333 -0.0340 0.7417 0.6650
-3.000 -0.1787 0.00867 0.00342 -0.0339 0.7406 0.6840
-2.750 -0.1509 0.00878 0.00355 -0.0340 0.7395 0.6954
-2.500 -0.1234 0.00889 0.00363 -0.0340 0.7384 0.7056
-2.250 -0.0947 0.00902 0.00376 -0.0343 0.7374 0.7120
-2.000 -0.0663 0.00906 0.00377 -0.0346 0.7364 0.7160
-1.750 -0.0380 0.00907 0.00372 -0.0350 0.7353 0.7191
-1.500 -0.0093 0.00909 0.00372 -0.0354 0.7343 0.7220
-1.250 0.0199 0.00913 0.00376 -0.0358 0.7333 0.7244
-1.000 0.0490 0.00916 0.00377 -0.0363 0.7325 0.7262
-0.750 0.0781 0.00918 0.00377 -0.0369 0.7316 0.7274
-0.500 0.1068 0.00919 0.00376 -0.0374 0.7308 0.7284
-0.250 0.1351 0.00920 0.00378 -0.0378 0.7299 0.7296
0.000 0.1634 0.00921 0.00380 -0.0382 0.7290 0.7308
0.250 0.1917 0.00923 0.00382 -0.0386 0.7280 0.7319
0.500 0.2200 0.00924 0.00384 -0.0390 0.7268 0.7329
0.750 0.2482 0.00926 0.00386 -0.0394 0.7255 0.7339
1.000 0.2766 0.00928 0.00389 -0.0398 0.7243 0.7349
1.250 0.3050 0.00928 0.00390 -0.0403 0.7226 0.7359
1.500 0.3337 0.00927 0.00388 -0.0407 0.7204 0.7368
1.750 0.3627 0.00923 0.00384 -0.0412 0.7180 0.7376
2.000 0.3922 0.00921 0.00382 -0.0417 0.7157 0.7385
2.250 0.4200 0.00922 0.00388 -0.0420 0.7134 0.7395
2.500 0.4469 0.00924 0.00396 -0.0421 0.7109 0.7406
2.750 0.4740 0.00923 0.00400 -0.0422 0.7072 0.7417
3.000 0.5020 0.00918 0.00397 -0.0424 0.7029 0.7428
3.250 0.5315 0.00913 0.00390 -0.0428 0.6984 0.7438
3.500 0.5555 0.00910 0.00396 -0.0423 0.6916 0.7450
3.750 0.5825 0.00902 0.00388 -0.0423 0.6837 0.7461
4.000 0.6063 0.00899 0.00390 -0.0416 0.6731 0.7474
4.250 0.6293 0.00894 0.00386 -0.0408 0.6565 0.7487
4.500 0.6464 0.00894 0.00376 -0.0387 0.6145 0.7501
4.750 0.6360 0.00953 0.00388 -0.0313 0.5282 0.7521
5.000 0.6208 0.01020 0.00427 -0.0232 0.4744 0.7540
5.250 0.6129 0.01101 0.00489 -0.0170 0.4274 0.7559
5.500 0.6053 0.01199 0.00565 -0.0112 0.3752 0.7578
5.750 0.6041 0.01290 0.00638 -0.0068 0.3284 0.7597
6.000 0.6039 0.01388 0.00714 -0.0028 0.2790 0.7616
6.250 0.6064 0.01485 0.00788 0.0006 0.2303 0.7637
6.500 0.6121 0.01575 0.00857 0.0035 0.1870 0.7658
6.750 0.6172 0.01673 0.00930 0.0063 0.1376 0.7680
7.000 0.6242 0.01768 0.01002 0.0087 0.0949 0.7702
7.500 0.6488 0.01913 0.01125 0.0121 0.0507 0.7738
7.750 0.6642 0.01972 0.01182 0.0134 0.0416 0.7756
8.000 0.6805 0.02028 0.01237 0.0145 0.0360 0.7775
8.250 0.6974 0.02082 0.01292 0.0155 0.0325 0.7796
8.500 0.7136 0.02141 0.01352 0.0166 0.0298 0.7818
8.750 0.7311 0.02195 0.01408 0.0175 0.0277 0.7840
9.000 0.7474 0.02257 0.01471 0.0184 0.0258 0.7863
9.250 0.7638 0.02318 0.01535 0.0194 0.0245 0.7885
9.500 0.7806 0.02378 0.01598 0.0203 0.0233 0.7906
9.750 0.7965 0.02441 0.01665 0.0212 0.0222 0.7929
10.000 0.8108 0.02517 0.01744 0.0224 0.0209 0.7953
10.250 0.8268 0.02584 0.01816 0.0233 0.0203 0.7979
10.500 0.8426 0.02654 0.01890 0.0241 0.0192 0.8007
10.750 0.8577 0.02730 0.01971 0.0250 0.0188 0.8035
11.000 0.8726 0.02809 0.02052 0.0259 0.0181 0.8062
11.250 0.8856 0.02900 0.02147 0.0269 0.0175 0.8089
11.500 0.8997 0.02984 0.02238 0.0279 0.0170 0.8118
11.750 0.9130 0.03075 0.02336 0.0288 0.0167 0.8151
12.000 0.9260 0.03170 0.02438 0.0298 0.0163 0.8187
12.250 0.9395 0.03265 0.02538 0.0306 0.0159 0.8223
12.500 0.9518 0.03370 0.02648 0.0315 0.0156 0.8256
12.750 0.9635 0.03477 0.02763 0.0324 0.0154 0.8293
13.000 0.9756 0.03584 0.02877 0.0332 0.0150 0.8332
13.250 0.9865 0.03704 0.03002 0.0341 0.0148 0.8372
13.500 0.9968 0.03832 0.03136 0.0349 0.0147 0.8411
13.750 1.0042 0.03982 0.03292 0.0359 0.0143 0.8451
14.000 1.0143 0.04113 0.03432 0.0366 0.0142 0.8495
14.250 1.0232 0.04259 0.03587 0.0374 0.0142 0.8542
14.750 1.0405 0.04561 0.03909 0.0388 0.0138 0.8638
15.000 1.0493 0.04713 0.04073 0.0394 0.0135 0.8695
15.250 1.0562 0.04890 0.04258 0.0400 0.0136 0.8752
15.500 1.0637 0.05056 0.04437 0.0406 0.0133 0.8817
15.750 1.0696 0.05243 0.04636 0.0411 0.0132 0.8889
16.000 1.0755 0.05434 0.04838 0.0415 0.0132 0.8966
16.250 1.0809 0.05633 0.05049 0.0419 0.0129 0.9062
16.500 1.0860 0.05840 0.05269 0.0422 0.0129 0.9171
16.750 1.0912 0.06071 0.05512 0.0420 0.0128 0.9296
17.000 1.0986 0.06332 0.05787 0.0410 0.0127 0.9445
17.250 1.1093 0.06627 0.06096 0.0386 0.0125 0.9609
17.500 1.1116 0.06898 0.06379 0.0380 0.0125 1.0000
17.750 1.1140 0.07187 0.06676 0.0373 0.0123 1.0000
18.000 1.1155 0.07492 0.06989 0.0365 0.0122 1.0000
18.250 1.1164 0.07813 0.07318 0.0355 0.0121 1.0000
18.500 1.1155 0.08163 0.07679 0.0344 0.0121 1.0000
18.750 1.1137 0.08533 0.08059 0.0332 0.0120 1.0000
19.000 1.1107 0.08931 0.08467 0.0317 0.0119 1.0000
19.250 1.1079 0.09335 0.08882 0.0299 0.0119 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 66(3)-218 (naca663218-il)