NACA 65(3)-218 (naca653218-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 65(3)-218 (naca653218-il) Reynolds number: 100,000 Max Cl/Cd: 35.2 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca653218-il-100000.txt Download as CSV file: xf-naca653218-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4243 0.11396 0.10881 -0.0452 1.0000 0.1905
-12.000 -0.7864 0.06298 0.05686 -0.0696 1.0000 0.0806
-11.750 -0.8080 0.06091 0.05474 -0.0655 1.0000 0.0799
-11.500 -0.8444 0.06093 0.05478 -0.0578 1.0000 0.0796
-11.250 -0.8813 0.06117 0.05504 -0.0497 1.0000 0.0795
-11.000 -0.9096 0.06027 0.05407 -0.0434 1.0000 0.0789
-10.750 -0.9305 0.05850 0.05216 -0.0384 0.9994 0.0781
-10.500 -0.9224 0.05380 0.04695 -0.0395 0.9919 0.0760
-10.250 -0.9108 0.04970 0.04226 -0.0402 0.9844 0.0745
-10.000 -0.8902 0.04691 0.03914 -0.0411 0.9777 0.0751
-9.750 -0.8632 0.04442 0.03635 -0.0428 0.9723 0.0764
-9.500 -0.8378 0.04209 0.03368 -0.0437 0.9664 0.0772
-9.250 -0.8060 0.03983 0.03112 -0.0453 0.9611 0.0779
-9.000 -0.7633 0.03766 0.02866 -0.0484 0.9579 0.0794
-8.750 -0.7330 0.03632 0.02705 -0.0493 0.9518 0.0816
-8.500 -0.6815 0.03426 0.02505 -0.0533 0.9496 0.0857
-8.250 -0.6267 0.03271 0.02354 -0.0578 0.9478 0.0906
-8.000 -0.5684 0.03121 0.02213 -0.0624 0.9467 0.0981
-7.750 -0.5252 0.03018 0.02114 -0.0654 0.9439 0.1084
-7.500 -0.5076 0.02929 0.02045 -0.0646 0.9367 0.1184
-7.250 -0.4896 0.02814 0.01945 -0.0644 0.9301 0.1381
-7.000 -0.4999 0.02730 0.01883 -0.0597 0.9198 0.1588
-6.750 -0.5171 0.02550 0.01768 -0.0547 0.9115 0.2317
-6.500 -0.5476 0.02507 0.01756 -0.0459 0.8999 0.2778
-6.250 -0.5537 0.02469 0.01865 -0.0396 0.8942 0.5405
-6.000 -0.5679 0.02547 0.01942 -0.0319 0.8841 0.5680
-5.750 -0.5376 0.02701 0.02079 -0.0308 0.8801 0.6079
-5.500 -0.3211 0.03808 0.03166 -0.0447 0.8899 0.6485
-5.250 -0.5049 0.02979 0.02341 -0.0242 0.8691 0.6434
-5.000 -0.2220 0.04052 0.03376 -0.0483 0.8836 0.6786
-4.750 -0.1269 0.04125 0.03425 -0.0569 0.8844 0.6868
-4.500 -0.1015 0.04098 0.03387 -0.0571 0.8800 0.6985
-4.250 -0.0590 0.04076 0.03352 -0.0596 0.8773 0.7078
-4.000 -0.0681 0.04112 0.03388 -0.0544 0.8679 0.7163
-3.750 -0.0354 0.04094 0.03360 -0.0557 0.8642 0.7244
-3.500 -0.0133 0.04052 0.03310 -0.0556 0.8609 0.7331
-3.250 -0.0088 0.04102 0.03359 -0.0524 0.8533 0.7394
-3.000 -0.0372 0.04095 0.03350 -0.0447 0.8459 0.7487
-2.750 0.0283 0.04055 0.03299 -0.0510 0.8447 0.7533
-2.500 -0.0179 0.04149 0.03399 -0.0402 0.8355 0.7602
-2.250 -0.0469 0.04141 0.03390 -0.0321 0.8289 0.7675
-2.000 0.0178 0.04107 0.03346 -0.0387 0.8275 0.7714
-1.750 -0.2009 0.04147 0.03409 -0.0004 0.8135 0.7841
-1.500 -0.1499 0.04163 0.03416 -0.0046 0.8109 0.7870
-1.250 -0.1000 0.04161 0.03406 -0.0088 0.8088 0.7906
-1.000 -0.2154 0.04085 0.03336 0.0116 0.8025 0.8017
-0.750 -0.2043 0.04099 0.03348 0.0136 0.7987 0.8056
-0.500 -0.1937 0.04089 0.03334 0.0151 0.7956 0.8104
-0.250 -0.1932 0.04032 0.03270 0.0174 0.7931 0.8177
0.250 -0.1707 0.04067 0.03302 0.0207 0.7864 0.8253
0.500 -0.1725 0.04059 0.03291 0.0235 0.7840 0.8317
0.750 -0.1617 0.04053 0.03281 0.0246 0.7804 0.8363
1.000 -0.1408 0.04081 0.03308 0.0248 0.7775 0.8400
1.250 -0.1025 0.04114 0.03338 0.0226 0.7740 0.8441
1.500 -0.1039 0.04121 0.03343 0.0251 0.7701 0.8505
1.750 -0.0994 0.04145 0.03367 0.0272 0.7669 0.8549
2.000 -0.0844 0.04176 0.03399 0.0280 0.7628 0.8598
2.250 -0.0521 0.04205 0.03427 0.0265 0.7582 0.8649
2.500 -0.0354 0.04238 0.03460 0.0269 0.7528 0.8701
2.750 -0.0299 0.04273 0.03498 0.0289 0.7480 0.8753
3.000 -0.0047 0.04307 0.03533 0.0283 0.7426 0.8810
3.250 0.0223 0.04341 0.03567 0.0278 0.7355 0.8865
3.500 0.0293 0.04381 0.03612 0.0296 0.7293 0.8929
3.750 0.0730 0.04407 0.03640 0.0271 0.7228 0.8980
4.000 0.0745 0.04451 0.03688 0.0293 0.7143 0.9049
4.250 0.1066 0.04480 0.03722 0.0283 0.7074 0.9113
4.500 0.1227 0.04521 0.03767 0.0289 0.6982 0.9190
4.750 0.1551 0.04553 0.03806 0.0276 0.6907 0.9259
5.000 0.1749 0.04598 0.03857 0.0276 0.6814 0.9339
5.250 0.2130 0.04622 0.03889 0.0256 0.6735 0.9406
5.500 0.2360 0.04685 0.03960 0.0247 0.6628 0.9490
5.750 0.2875 0.04693 0.03979 0.0212 0.6557 0.9550
6.000 0.3153 0.04772 0.04070 0.0190 0.6434 0.9626
6.250 0.3809 0.04732 0.04044 0.0142 0.6379 0.9666
6.500 0.4122 0.04799 0.04125 0.0115 0.6241 0.9736
6.750 0.4562 0.04826 0.04167 0.0078 0.6119 0.9789
7.000 0.5259 0.04687 0.04048 0.0034 0.6056 0.9826
7.250 0.5715 0.04672 0.04051 -0.0003 0.5919 0.9880
7.500 0.6401 0.04396 0.03798 -0.0035 0.5797 0.9925
7.750 0.8451 0.02750 0.02182 -0.0096 0.5688 0.9785
8.000 0.8863 0.02549 0.01998 -0.0106 0.5374 0.9863
8.250 0.8984 0.02552 0.02013 -0.0101 0.4889 1.0000
8.500 0.8558 0.02616 0.02075 -0.0010 0.4885 1.0000
8.750 0.8263 0.02668 0.02122 0.0060 0.4706 1.0000
9.000 0.8316 0.02584 0.01934 0.0106 0.3259 1.0000
9.250 0.8065 0.02875 0.02145 0.0143 0.2331 1.0000
9.500 0.7854 0.03208 0.02403 0.0172 0.1608 1.0000
9.750 0.7805 0.03454 0.02602 0.0190 0.1277 1.0000
10.000 0.7882 0.03617 0.02743 0.0202 0.1112 1.0000
10.250 0.8014 0.03750 0.02856 0.0212 0.0997 1.0000
10.500 0.8224 0.03844 0.02949 0.0218 0.0919 1.0000
10.750 0.8532 0.03922 0.03006 0.0221 0.0856 1.0000
11.000 0.8798 0.04019 0.03107 0.0222 0.0802 1.0000
11.250 0.9316 0.04120 0.03184 0.0209 0.0752 1.0000
11.500 0.9653 0.04263 0.03348 0.0205 0.0727 1.0000
11.750 0.9995 0.04433 0.03535 0.0199 0.0705 1.0000
12.000 1.0286 0.04613 0.03721 0.0193 0.0678 1.0000
12.250 1.0784 0.04919 0.04025 0.0167 0.0654 1.0000
12.500 1.0981 0.05221 0.04356 0.0168 0.0648 1.0000
12.750 1.1087 0.05498 0.04662 0.0177 0.0647 1.0000
13.000 1.1131 0.05797 0.04991 0.0190 0.0646 1.0000
13.250 1.1173 0.06127 0.05347 0.0201 0.0647 1.0000
13.500 1.1154 0.06469 0.05716 0.0215 0.0648 1.0000
13.750 1.1146 0.06855 0.06125 0.0224 0.0650 1.0000
14.000 1.1050 0.07223 0.06516 0.0237 0.0651 1.0000
14.250 1.0865 0.07499 0.06821 0.0254 0.0654 1.0000
14.500 1.0169 0.07959 0.07340 0.0274 0.0673 1.0000
14.750 0.9601 0.08726 0.08151 0.0264 0.0691 1.0000
15.000 0.9157 0.09541 0.08995 0.0237 0.0708 1.0000
15.250 0.8759 0.10428 0.09900 0.0199 0.0724 1.0000
15.500 0.8461 0.11321 0.10805 0.0156 0.0739 1.0000
15.750 0.8449 0.11906 0.11392 0.0137 0.0751 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 65(3)-218 (naca653218-il)