NACA 65(3)-218 (naca653218-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 65(3)-218 (naca653218-il) Reynolds number: 500,000 Max Cl/Cd: 85.72 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca653218-il-500000.txt Download as CSV file: xf-naca653218-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.3828 0.16002 0.15791 -0.0177 1.0000 0.0312
-17.500 -0.7664 0.10460 0.10166 -0.0527 1.0000 0.0238
-17.250 -0.7657 0.10086 0.09790 -0.0549 1.0000 0.0240
-17.000 -0.7557 0.09895 0.09603 -0.0559 1.0000 0.0244
-16.750 -0.8678 0.07771 0.07403 -0.0682 1.0000 0.0232
-16.500 -0.8923 0.07210 0.06822 -0.0706 1.0000 0.0232
-16.250 -0.9078 0.06708 0.06304 -0.0717 1.0000 0.0231
-16.000 -0.9262 0.06285 0.05862 -0.0727 1.0000 0.0232
-15.750 -0.9402 0.05882 0.05441 -0.0731 1.0000 0.0232
-15.500 -0.9585 0.05466 0.05004 -0.0731 1.0000 0.0233
-15.250 -0.9663 0.05134 0.04654 -0.0728 1.0000 0.0234
-15.000 -0.9695 0.04816 0.04320 -0.0723 1.0000 0.0235
-14.750 -0.9654 0.04579 0.04076 -0.0719 1.0000 0.0238
-14.500 -0.9603 0.04388 0.03876 -0.0714 1.0000 0.0240
-14.250 -0.9547 0.04209 0.03690 -0.0708 1.0000 0.0243
-14.000 -0.9464 0.04067 0.03544 -0.0702 1.0000 0.0246
-13.750 -0.9378 0.03920 0.03390 -0.0696 1.0000 0.0249
-13.500 -0.9294 0.03773 0.03235 -0.0688 1.0000 0.0252
-13.250 -0.9206 0.03628 0.03081 -0.0680 1.0000 0.0256
-13.000 -0.9099 0.03484 0.02926 -0.0671 1.0000 0.0259
-12.750 -0.8978 0.03352 0.02784 -0.0663 1.0000 0.0262
-12.500 -0.8763 0.03207 0.02627 -0.0672 0.9812 0.0266
-12.250 -0.8424 0.03062 0.02466 -0.0704 0.9661 0.0271
-12.000 -0.8077 0.02934 0.02321 -0.0737 0.9526 0.0274
-11.750 -0.7706 0.02806 0.02189 -0.0756 0.9423 0.0282
-11.500 -0.7453 0.02722 0.02100 -0.0762 0.9263 0.0289
-11.000 -0.7110 0.02578 0.01941 -0.0746 0.8974 0.0299
-10.750 -0.6952 0.02509 0.01864 -0.0735 0.8857 0.0305
-10.500 -0.6797 0.02441 0.01786 -0.0723 0.8754 0.0310
-10.250 -0.6643 0.02372 0.01710 -0.0712 0.8652 0.0315
-10.000 -0.6491 0.02305 0.01634 -0.0700 0.8565 0.0320
-9.750 -0.6336 0.02243 0.01564 -0.0688 0.8478 0.0324
-9.500 -0.6241 0.02139 0.01455 -0.0670 0.8400 0.0333
-9.250 -0.6130 0.02053 0.01366 -0.0654 0.8318 0.0341
-9.000 -0.6006 0.01984 0.01291 -0.0639 0.8247 0.0350
-8.750 -0.5873 0.01915 0.01219 -0.0625 0.8170 0.0358
-8.500 -0.5743 0.01851 0.01147 -0.0610 0.8102 0.0368
-8.250 -0.5602 0.01792 0.01082 -0.0595 0.8036 0.0378
-8.000 -0.5493 0.01719 0.01004 -0.0576 0.7970 0.0386
-7.750 -0.5413 0.01641 0.00920 -0.0553 0.7910 0.0400
-7.500 -0.5290 0.01582 0.00859 -0.0534 0.7851 0.0416
-7.250 -0.5163 0.01532 0.00804 -0.0514 0.7792 0.0434
-7.000 -0.5053 0.01491 0.00755 -0.0490 0.7739 0.0455
-6.750 -0.4948 0.01444 0.00710 -0.0465 0.7684 0.0488
-6.500 -0.4778 0.01405 0.00667 -0.0450 0.7631 0.0533
-6.250 -0.4628 0.01354 0.00619 -0.0432 0.7584 0.0646
-6.000 -0.4522 0.01274 0.00564 -0.0409 0.7538 0.1100
-5.750 -0.4446 0.01164 0.00501 -0.0383 0.7490 0.2028
-5.500 -0.4364 0.01041 0.00431 -0.0359 0.7444 0.3195
-5.250 -0.4266 0.00923 0.00374 -0.0336 0.7404 0.4593
-5.000 -0.4034 0.00898 0.00367 -0.0331 0.7365 0.5206
-4.750 -0.3765 0.00891 0.00364 -0.0330 0.7323 0.5463
-4.500 -0.3488 0.00890 0.00359 -0.0331 0.7283 0.5627
-4.250 -0.3206 0.00892 0.00354 -0.0333 0.7247 0.5761
-4.000 -0.2924 0.00898 0.00355 -0.0334 0.7214 0.5868
-3.750 -0.2644 0.00902 0.00361 -0.0336 0.7180 0.5992
-3.500 -0.2362 0.00911 0.00367 -0.0337 0.7144 0.6117
-3.250 -0.2080 0.00926 0.00381 -0.0337 0.7109 0.6239
-3.000 -0.1796 0.00939 0.00395 -0.0337 0.7077 0.6340
-2.750 -0.1508 0.00952 0.00399 -0.0340 0.7045 0.6409
-2.500 -0.1221 0.00949 0.00395 -0.0343 0.7014 0.6451
-2.250 -0.0931 0.00946 0.00394 -0.0347 0.6982 0.6482
-2.000 -0.0640 0.00945 0.00391 -0.0351 0.6951 0.6510
-1.750 -0.0348 0.00944 0.00386 -0.0355 0.6923 0.6539
-1.500 -0.0056 0.00945 0.00380 -0.0359 0.6895 0.6569
-1.250 0.0236 0.00950 0.00377 -0.0364 0.6866 0.6596
-1.000 0.0525 0.00943 0.00373 -0.0368 0.6836 0.6621
-0.750 0.0815 0.00941 0.00372 -0.0372 0.6807 0.6646
-0.500 0.1106 0.00941 0.00373 -0.0376 0.6779 0.6673
-0.250 0.1399 0.00942 0.00372 -0.0381 0.6753 0.6700
0.000 0.1692 0.00944 0.00371 -0.0385 0.6728 0.6727
0.250 0.1986 0.00951 0.00374 -0.0391 0.6701 0.6756
0.500 0.2274 0.00951 0.00375 -0.0395 0.6675 0.6784
0.750 0.2562 0.00949 0.00378 -0.0398 0.6648 0.6811
1.000 0.2851 0.00950 0.00383 -0.0402 0.6621 0.6837
1.250 0.3143 0.00952 0.00386 -0.0407 0.6594 0.6864
1.500 0.3436 0.00956 0.00389 -0.0411 0.6569 0.6894
1.750 0.3730 0.00964 0.00395 -0.0416 0.6545 0.6927
2.000 0.4019 0.00970 0.00403 -0.0421 0.6520 0.6957
2.250 0.4302 0.00970 0.00411 -0.0424 0.6492 0.6986
2.500 0.4589 0.00973 0.00419 -0.0427 0.6463 0.7015
2.750 0.4878 0.00977 0.00427 -0.0431 0.6435 0.7047
3.000 0.5170 0.00980 0.00430 -0.0435 0.6403 0.7081
3.250 0.5463 0.00989 0.00436 -0.0440 0.6365 0.7115
3.500 0.5737 0.00985 0.00443 -0.0440 0.6321 0.7149
3.750 0.6017 0.00982 0.00446 -0.0442 0.6270 0.7182
4.000 0.6301 0.00979 0.00439 -0.0443 0.6195 0.7218
4.250 0.6564 0.00967 0.00434 -0.0440 0.6098 0.7257
4.500 0.6834 0.00962 0.00428 -0.0439 0.5998 0.7294
4.750 0.7095 0.00954 0.00422 -0.0436 0.5886 0.7330
5.000 0.7353 0.00951 0.00429 -0.0433 0.5773 0.7367
5.250 0.7613 0.00953 0.00434 -0.0431 0.5658 0.7410
5.500 0.7870 0.00959 0.00440 -0.0428 0.5535 0.7456
5.750 0.8117 0.00964 0.00448 -0.0424 0.5373 0.7498
6.000 0.8349 0.00974 0.00461 -0.0416 0.5141 0.7539
6.250 0.8533 0.01002 0.00478 -0.0400 0.4750 0.7586
6.500 0.8589 0.01082 0.00521 -0.0364 0.3983 0.7638
6.750 0.8544 0.01193 0.00594 -0.0312 0.3191 0.7690
7.000 0.8458 0.01292 0.00664 -0.0253 0.2573 0.7749
7.250 0.8383 0.01406 0.00750 -0.0199 0.2029 0.7818
7.500 0.8326 0.01526 0.00848 -0.0153 0.1525 0.7881
7.750 0.8278 0.01660 0.00957 -0.0111 0.1042 0.7952
8.000 0.8254 0.01796 0.01073 -0.0076 0.0679 0.8023
8.250 0.8299 0.01904 0.01176 -0.0050 0.0520 0.8091
8.500 0.8391 0.01998 0.01269 -0.0032 0.0455 0.8166
8.750 0.8474 0.02094 0.01368 -0.0012 0.0414 0.8237
9.000 0.8585 0.02182 0.01461 0.0004 0.0393 0.8320
9.250 0.8694 0.02268 0.01554 0.0020 0.0370 0.8402
9.500 0.8753 0.02390 0.01680 0.0039 0.0349 0.8499
9.750 0.8844 0.02489 0.01789 0.0056 0.0340 0.8592
10.000 0.8953 0.02582 0.01890 0.0070 0.0329 0.8699
10.250 0.9043 0.02682 0.01998 0.0086 0.0317 0.8817
10.500 0.9122 0.02788 0.02113 0.0103 0.0308 0.8954
10.750 0.9167 0.02914 0.02247 0.0123 0.0300 0.9130
11.000 0.9206 0.03058 0.02402 0.0140 0.0292 0.9396
11.250 0.9468 0.03181 0.02537 0.0116 0.0286 0.9868
11.500 0.9587 0.03302 0.02661 0.0122 0.0278 1.0000
11.750 0.9711 0.03428 0.02790 0.0126 0.0273 1.0000
12.000 0.9839 0.03550 0.02913 0.0130 0.0263 1.0000
12.250 0.9950 0.03688 0.03052 0.0136 0.0259 1.0000
12.500 1.0051 0.03833 0.03196 0.0142 0.0252 1.0000
12.750 1.0159 0.03975 0.03338 0.0151 0.0248 1.0000
13.000 1.0295 0.04097 0.03467 0.0155 0.0244 1.0000
13.250 1.0430 0.04224 0.03600 0.0159 0.0241 1.0000
13.500 1.0563 0.04353 0.03735 0.0162 0.0237 1.0000
13.750 1.0701 0.04481 0.03868 0.0167 0.0234 1.0000
14.000 1.0831 0.04616 0.04010 0.0170 0.0230 1.0000
14.250 1.0969 0.04748 0.04147 0.0174 0.0228 1.0000
14.500 1.1094 0.04893 0.04298 0.0176 0.0223 1.0000
14.750 1.1211 0.05047 0.04456 0.0178 0.0220 1.0000
15.000 1.1323 0.05203 0.04616 0.0180 0.0217 1.0000
15.250 1.1454 0.05353 0.04771 0.0182 0.0214 1.0000
15.500 1.1674 0.05468 0.04884 0.0186 0.0208 1.0000
15.750 1.1756 0.05679 0.05108 0.0188 0.0206 1.0000
16.000 1.1772 0.05928 0.05373 0.0188 0.0205 1.0000
16.250 1.1818 0.06173 0.05632 0.0189 0.0204 1.0000
16.500 1.1844 0.06440 0.05914 0.0187 0.0203 1.0000
16.750 1.1846 0.06742 0.06232 0.0185 0.0201 1.0000
17.000 1.1822 0.07082 0.06590 0.0181 0.0200 1.0000
17.250 1.1779 0.07448 0.06974 0.0174 0.0199 1.0000
17.500 1.1714 0.07860 0.07404 0.0166 0.0198 1.0000
17.750 1.1637 0.08295 0.07857 0.0154 0.0197 1.0000
18.000 1.1526 0.08795 0.08376 0.0138 0.0196 1.0000
18.250 1.1397 0.09338 0.08939 0.0119 0.0197 1.0000
18.500 1.1242 0.09937 0.09558 0.0094 0.0196 1.0000
18.750 1.1022 0.10677 0.10320 0.0059 0.0196 1.0000
19.000 1.0820 0.11418 0.11080 0.0021 0.0197 1.0000
19.250 1.0542 0.12343 0.12028 -0.0032 0.0198 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 65(3)-218 (naca653218-il)