NACA 66(3)-418 (naca663418-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(3)-418 (naca663418-il) Reynolds number: 200,000 Max Cl/Cd: 44.86 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca663418-il-200000-n5.txt Download as CSV file: xf-naca663418-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(3)-418
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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.4585 0.09017 0.08582 -0.1120 0.9399 0.0250
-15.250 -0.4873 0.07958 0.07503 -0.1201 0.9340 0.0248
-15.000 -0.5151 0.07119 0.06640 -0.1259 0.9268 0.0247
-14.750 -0.5405 0.06462 0.05957 -0.1296 0.9192 0.0247
-14.500 -0.5618 0.05948 0.05416 -0.1315 0.9123 0.0247
-14.250 -0.5863 0.05484 0.04920 -0.1320 0.9046 0.0248
-13.750 -0.6149 0.04826 0.04206 -0.1306 0.8917 0.0249
-13.500 -0.6259 0.04555 0.03905 -0.1290 0.8856 0.0250
-13.250 -0.6283 0.04333 0.03660 -0.1276 0.8807 0.0251
-13.000 -0.6261 0.04157 0.03471 -0.1263 0.8752 0.0253
-12.750 -0.6217 0.03996 0.03296 -0.1249 0.8701 0.0255
-12.500 -0.6144 0.03879 0.03168 -0.1236 0.8659 0.0259
-12.250 -0.6081 0.03736 0.03009 -0.1222 0.8619 0.0262
-12.000 -0.6001 0.03616 0.02875 -0.1208 0.8575 0.0266
-11.750 -0.5907 0.03488 0.02732 -0.1193 0.8536 0.0270
-11.500 -0.5795 0.03362 0.02587 -0.1180 0.8502 0.0275
-11.250 -0.5652 0.03231 0.02433 -0.1170 0.8474 0.0280
-11.000 -0.5480 0.03109 0.02292 -0.1162 0.8445 0.0283
-10.750 -0.5298 0.02998 0.02163 -0.1155 0.8413 0.0289
-10.500 -0.5093 0.02899 0.02045 -0.1149 0.8384 0.0293
-10.250 -0.4862 0.02804 0.01939 -0.1148 0.8359 0.0298
-10.000 -0.4625 0.02717 0.01851 -0.1147 0.8336 0.0303
-9.750 -0.4408 0.02645 0.01775 -0.1143 0.8314 0.0308
-9.500 -0.4205 0.02583 0.01706 -0.1138 0.8294 0.0318
-9.250 -0.4006 0.02523 0.01641 -0.1131 0.8268 0.0329
-9.000 -0.3798 0.02461 0.01573 -0.1125 0.8241 0.0337
-8.750 -0.3598 0.02406 0.01510 -0.1118 0.8213 0.0346
-8.500 -0.3412 0.02339 0.01443 -0.1109 0.8187 0.0354
-8.250 -0.3238 0.02278 0.01382 -0.1098 0.8164 0.0362
-8.000 -0.3066 0.02223 0.01324 -0.1088 0.8144 0.0372
-7.500 -0.2726 0.02125 0.01215 -0.1064 0.8106 0.0403
-7.250 -0.2589 0.02075 0.01167 -0.1048 0.8081 0.0418
-7.000 -0.2446 0.02029 0.01122 -0.1032 0.8056 0.0435
-6.750 -0.2294 0.01989 0.01078 -0.1017 0.8033 0.0456
-6.500 -0.2142 0.01949 0.01034 -0.1001 0.8012 0.0481
-6.250 -0.1999 0.01905 0.00990 -0.0984 0.7992 0.0509
-6.000 -0.1842 0.01868 0.00949 -0.0968 0.7975 0.0555
-5.750 -0.1704 0.01828 0.00911 -0.0949 0.7959 0.0627
-5.500 -0.1573 0.01792 0.00878 -0.0929 0.7945 0.0737
-5.250 -0.1531 0.01766 0.00865 -0.0892 0.7916 0.0934
-5.000 -0.1517 0.01723 0.00848 -0.0852 0.7886 0.1402
-4.750 -0.1515 0.01662 0.00824 -0.0810 0.7860 0.2170
-4.500 -0.1521 0.01591 0.00794 -0.0767 0.7837 0.3092
-4.250 -0.1526 0.01506 0.00761 -0.0723 0.7816 0.4211
-4.000 -0.1475 0.01451 0.00790 -0.0681 0.7800 0.5723
-3.750 -0.1226 0.01490 0.00844 -0.0670 0.7790 0.6529
-3.500 -0.0976 0.01524 0.00873 -0.0663 0.7781 0.6842
-3.250 -0.0725 0.01604 0.00955 -0.0650 0.7769 0.7104
-3.000 -0.0534 0.01702 0.01057 -0.0626 0.7747 0.7272
-2.750 -0.0377 0.01751 0.01102 -0.0603 0.7721 0.7396
-2.500 -0.0130 0.01803 0.01154 -0.0592 0.7701 0.7435
-2.250 0.0104 0.01829 0.01177 -0.0584 0.7684 0.7467
-2.000 0.0330 0.01841 0.01184 -0.0577 0.7669 0.7504
-1.750 0.0546 0.01834 0.01169 -0.0572 0.7655 0.7556
-1.500 0.0789 0.01833 0.01162 -0.0570 0.7643 0.7588
-1.250 0.1055 0.01841 0.01167 -0.0570 0.7633 0.7603
-1.000 0.1333 0.01844 0.01165 -0.0572 0.7623 0.7620
-0.750 0.1617 0.01844 0.01161 -0.0576 0.7614 0.7637
-0.500 0.1815 0.01861 0.01177 -0.0565 0.7596 0.7660
-0.250 0.1725 0.01926 0.01248 -0.0506 0.7534 0.7699
0.000 0.1921 0.01931 0.01250 -0.0497 0.7509 0.7726
0.250 0.2177 0.01924 0.01237 -0.0500 0.7491 0.7749
0.500 0.2454 0.01918 0.01229 -0.0505 0.7478 0.7761
0.750 0.2743 0.01914 0.01224 -0.0510 0.7467 0.7770
1.000 0.3042 0.01910 0.01220 -0.0516 0.7457 0.7780
1.250 0.3352 0.01906 0.01215 -0.0525 0.7448 0.7791
1.750 0.3273 0.02027 0.01346 -0.0422 0.7323 0.7833
2.000 0.3589 0.02015 0.01335 -0.0433 0.7311 0.7845
2.250 0.3929 0.01999 0.01319 -0.0447 0.7301 0.7857
2.500 0.4288 0.01980 0.01301 -0.0465 0.7292 0.7868
2.750 0.4650 0.01962 0.01285 -0.0484 0.7284 0.7880
3.250 0.4635 0.02081 0.01409 -0.0397 0.7146 0.7937
3.500 0.4979 0.02053 0.01386 -0.0410 0.7136 0.7945
3.750 0.5350 0.02018 0.01355 -0.0427 0.7127 0.7954
4.000 0.5750 0.01977 0.01320 -0.0449 0.7118 0.7962
4.500 0.5865 0.02068 0.01424 -0.0381 0.6975 0.8000
4.750 0.5793 0.02181 0.01542 -0.0331 0.6862 0.8026
5.000 0.6122 0.02138 0.01506 -0.0340 0.6836 0.8040
5.250 0.6515 0.02064 0.01439 -0.0357 0.6818 0.8053
5.500 0.6958 0.01973 0.01355 -0.0381 0.6800 0.8066
6.000 0.7258 0.02011 0.01405 -0.0347 0.6643 0.8113
6.250 0.7208 0.02103 0.01507 -0.0300 0.6501 0.8137
6.500 0.7248 0.02165 0.01577 -0.0267 0.6350 0.8162
6.750 0.7265 0.02241 0.01658 -0.0232 0.6120 0.8188
7.000 0.8115 0.01814 0.01186 -0.0287 0.5318 0.8190
7.250 0.8259 0.01841 0.01173 -0.0265 0.4685 0.8213
7.500 0.8258 0.01945 0.01249 -0.0227 0.4186 0.8242
7.750 0.8226 0.02075 0.01352 -0.0188 0.3695 0.8274
8.000 0.8190 0.02213 0.01465 -0.0151 0.3228 0.8301
8.250 0.8155 0.02357 0.01586 -0.0115 0.2745 0.8327
8.500 0.8140 0.02504 0.01709 -0.0083 0.2259 0.8355
8.750 0.8146 0.02653 0.01831 -0.0057 0.1767 0.8385
9.000 0.8169 0.02802 0.01952 -0.0034 0.1280 0.8417
9.250 0.8210 0.02951 0.02074 -0.0014 0.0871 0.8448
9.500 0.8289 0.03072 0.02184 0.0003 0.0655 0.8475
9.750 0.8387 0.03180 0.02288 0.0018 0.0528 0.8504
10.000 0.8498 0.03284 0.02393 0.0031 0.0457 0.8537
10.250 0.8612 0.03392 0.02503 0.0043 0.0412 0.8575
10.500 0.8734 0.03501 0.02615 0.0053 0.0376 0.8613
10.750 0.8842 0.03614 0.02733 0.0065 0.0351 0.8647
11.000 0.8955 0.03722 0.02849 0.0076 0.0325 0.8683
11.250 0.9046 0.03855 0.02985 0.0088 0.0307 0.8722
11.500 0.9164 0.03973 0.03114 0.0097 0.0292 0.8765
11.750 0.9267 0.04107 0.03255 0.0106 0.0278 0.8806
12.000 0.9360 0.04241 0.03396 0.0117 0.0268 0.8848
12.250 0.9438 0.04394 0.03554 0.0127 0.0261 0.8897
12.500 0.9534 0.04542 0.03712 0.0135 0.0252 0.8949
12.750 0.9628 0.04684 0.03864 0.0145 0.0244 0.9001
13.000 0.9720 0.04833 0.04022 0.0154 0.0236 0.9063
13.250 0.9815 0.04984 0.04180 0.0161 0.0230 0.9129
13.500 0.9908 0.05133 0.04337 0.0168 0.0226 0.9205
13.750 0.9995 0.05294 0.04501 0.0174 0.0220 0.9292
14.250 1.0228 0.05607 0.04839 0.0178 0.0210 0.9538
14.750 1.0442 0.05936 0.05191 0.0178 0.0198 1.0000
15.000 1.0550 0.06120 0.05384 0.0177 0.0194 1.0000
15.250 1.0657 0.06308 0.05579 0.0177 0.0191 1.0000
15.500 1.0753 0.06508 0.05785 0.0175 0.0188 1.0000
15.750 1.0847 0.06712 0.05996 0.0174 0.0185 1.0000
16.000 1.0942 0.06915 0.06204 0.0172 0.0183 1.0000
16.250 1.1025 0.07140 0.06439 0.0171 0.0181 1.0000
16.500 1.1084 0.07397 0.06713 0.0169 0.0179 1.0000
16.750 1.1123 0.07681 0.07016 0.0166 0.0178 1.0000
17.000 1.1132 0.08006 0.07362 0.0162 0.0176 1.0000
17.250 1.1131 0.08347 0.07723 0.0156 0.0174 1.0000
17.500 1.1107 0.08725 0.08122 0.0148 0.0173 1.0000
17.750 1.1054 0.09152 0.08571 0.0137 0.0172 1.0000
18.000 1.0987 0.09610 0.09050 0.0122 0.0171 1.0000
18.250 1.0898 0.10112 0.09574 0.0104 0.0170 1.0000
18.500 1.0783 0.10670 0.10154 0.0081 0.0169 1.0000
18.750 1.0650 0.11277 0.10784 0.0053 0.0169 1.0000
19.000 1.0487 0.11962 0.11492 0.0018 0.0169 1.0000
19.250 1.0294 0.12737 0.12290 -0.0025 0.0169 1.0000
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Polar data table (+)
Polar graphs
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