NACA 63(2)-615 (naca632615-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 63(2)-615 (naca632615-il) Reynolds number: 500,000 Max Cl/Cd: 104.5 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca632615-il-500000-n5.txt Download as CSV file: xf-naca632615-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)-615
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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.7272 0.10321 0.10014 -0.0555 1.0000 0.0124
-16.750 -0.7732 0.09020 0.08693 -0.0628 1.0000 0.0123
-16.500 -0.8023 0.08090 0.07748 -0.0683 1.0000 0.0123
-16.250 -0.8275 0.07257 0.06899 -0.0734 1.0000 0.0124
-16.000 -0.8454 0.06594 0.06219 -0.0774 1.0000 0.0124
-15.750 -0.8588 0.06043 0.05656 -0.0807 1.0000 0.0123
-15.500 -0.8700 0.05552 0.05150 -0.0834 1.0000 0.0125
-15.250 -0.8800 0.05117 0.04704 -0.0857 1.0000 0.0126
-15.000 -0.8870 0.04742 0.04318 -0.0875 1.0000 0.0126
-14.750 -0.8926 0.04405 0.03974 -0.0889 1.0000 0.0128
-14.500 -0.8957 0.04112 0.03673 -0.0898 1.0000 0.0129
-14.250 -0.8967 0.03861 0.03414 -0.0904 1.0000 0.0131
-14.000 -0.8971 0.03632 0.03177 -0.0906 1.0000 0.0133
-13.750 -0.8939 0.03452 0.02992 -0.0905 1.0000 0.0136
-13.500 -0.8942 0.03263 0.02795 -0.0899 1.0000 0.0137
-13.250 -0.8932 0.03110 0.02636 -0.0889 1.0000 0.0139
-13.000 -0.8833 0.02940 0.02457 -0.0896 0.9978 0.0143
-12.750 -0.8640 0.02770 0.02276 -0.0918 0.9867 0.0147
-12.500 -0.8422 0.02610 0.02103 -0.0942 0.9764 0.0150
-12.250 -0.8165 0.02456 0.01935 -0.0972 0.9661 0.0154
-12.000 -0.7873 0.02313 0.01786 -0.1006 0.9558 0.0159
-11.750 -0.7547 0.02202 0.01666 -0.1039 0.9451 0.0164
-11.500 -0.7239 0.02101 0.01554 -0.1066 0.9321 0.0170
-11.250 -0.6971 0.02016 0.01455 -0.1082 0.9180 0.0177
-11.000 -0.6743 0.01947 0.01372 -0.1085 0.9045 0.0183
-10.750 -0.6542 0.01878 0.01294 -0.1083 0.8918 0.0189
-10.250 -0.6119 0.01778 0.01178 -0.1076 0.8696 0.0203
-10.000 -0.5903 0.01729 0.01118 -0.1072 0.8602 0.0210
-9.750 -0.5682 0.01681 0.01060 -0.1068 0.8506 0.0218
-9.500 -0.5460 0.01630 0.01001 -0.1064 0.8420 0.0225
-9.250 -0.5227 0.01588 0.00954 -0.1061 0.8335 0.0234
-9.000 -0.4985 0.01552 0.00911 -0.1059 0.8260 0.0245
-8.750 -0.4739 0.01517 0.00867 -0.1058 0.8181 0.0256
-8.500 -0.4494 0.01478 0.00819 -0.1056 0.8110 0.0266
-8.250 -0.4247 0.01436 0.00774 -0.1055 0.8038 0.0277
-8.000 -0.3992 0.01404 0.00735 -0.1054 0.7968 0.0289
-7.750 -0.3732 0.01373 0.00698 -0.1054 0.7901 0.0303
-7.500 -0.3471 0.01342 0.00659 -0.1054 0.7832 0.0315
-7.250 -0.3212 0.01304 0.00618 -0.1054 0.7768 0.0331
-7.000 -0.2943 0.01275 0.00586 -0.1056 0.7701 0.0347
-6.750 -0.2674 0.01251 0.00553 -0.1056 0.7636 0.0363
-6.500 -0.2403 0.01220 0.00518 -0.1058 0.7575 0.0381
-6.250 -0.2130 0.01191 0.00487 -0.1060 0.7509 0.0401
-6.000 -0.1854 0.01169 0.00459 -0.1061 0.7448 0.0424
-5.750 -0.1575 0.01145 0.00431 -0.1063 0.7387 0.0449
-5.500 -0.1297 0.01121 0.00405 -0.1065 0.7322 0.0483
-5.250 -0.1016 0.01102 0.00381 -0.1067 0.7264 0.0524
-5.000 -0.0733 0.01078 0.00358 -0.1071 0.7203 0.0587
-4.750 -0.0450 0.01055 0.00336 -0.1074 0.7141 0.0688
-4.500 -0.0167 0.01031 0.00315 -0.1077 0.7084 0.0854
-4.250 0.0120 0.01003 0.00295 -0.1082 0.7022 0.1111
-4.000 0.0406 0.00971 0.00274 -0.1087 0.6964 0.1493
-3.750 0.0696 0.00934 0.00254 -0.1093 0.6908 0.2015
-3.500 0.0989 0.00891 0.00234 -0.1101 0.6847 0.2711
-3.250 0.1282 0.00855 0.00217 -0.1108 0.6787 0.3404
-3.000 0.1577 0.00831 0.00210 -0.1115 0.6734 0.3980
-2.750 0.1872 0.00820 0.00205 -0.1119 0.6675 0.4323
-2.500 0.2163 0.00813 0.00203 -0.1122 0.6617 0.4669
-2.250 0.2457 0.00807 0.00204 -0.1126 0.6561 0.4980
-2.000 0.2749 0.00806 0.00204 -0.1129 0.6504 0.5158
-1.750 0.3038 0.00807 0.00203 -0.1131 0.6450 0.5293
-1.500 0.3330 0.00808 0.00204 -0.1134 0.6395 0.5428
-1.250 0.3621 0.00810 0.00204 -0.1136 0.6335 0.5525
-1.000 0.3909 0.00813 0.00204 -0.1138 0.6282 0.5598
-0.750 0.4200 0.00815 0.00206 -0.1141 0.6231 0.5674
-0.500 0.4490 0.00818 0.00208 -0.1143 0.6173 0.5744
-0.250 0.4777 0.00822 0.00210 -0.1145 0.6118 0.5809
0.000 0.5067 0.00826 0.00213 -0.1147 0.6067 0.5876
0.250 0.5356 0.00830 0.00217 -0.1149 0.6012 0.5934
0.500 0.5641 0.00835 0.00221 -0.1151 0.5958 0.5997
0.750 0.5930 0.00841 0.00226 -0.1153 0.5906 0.6061
1.000 0.6217 0.00845 0.00232 -0.1155 0.5851 0.6117
1.250 0.6501 0.00852 0.00238 -0.1157 0.5796 0.6178
1.500 0.6788 0.00859 0.00245 -0.1158 0.5743 0.6244
1.750 0.7073 0.00864 0.00253 -0.1160 0.5685 0.6305
2.000 0.7354 0.00873 0.00262 -0.1161 0.5627 0.6368
2.500 0.7921 0.00887 0.00281 -0.1164 0.5511 0.6493
2.750 0.8200 0.00898 0.00291 -0.1164 0.5454 0.6563
3.000 0.8483 0.00905 0.00303 -0.1166 0.5396 0.6625
3.250 0.8762 0.00914 0.00315 -0.1166 0.5331 0.6689
3.500 0.9037 0.00926 0.00328 -0.1167 0.5259 0.6760
3.750 0.9311 0.00936 0.00341 -0.1166 0.5164 0.6826
4.000 0.9582 0.00949 0.00355 -0.1165 0.5068 0.6896
4.250 0.9850 0.00964 0.00370 -0.1164 0.4972 0.6963
4.500 1.0118 0.00976 0.00387 -0.1163 0.4865 0.7032
4.750 1.0377 0.00995 0.00404 -0.1160 0.4714 0.7107
5.000 1.0628 0.01017 0.00423 -0.1156 0.4534 0.7173
5.250 1.0867 0.01045 0.00446 -0.1151 0.4320 0.7246
5.500 1.1096 0.01081 0.00472 -0.1143 0.4024 0.7319
5.750 1.1303 0.01130 0.00507 -0.1132 0.3668 0.7393
6.000 1.1509 0.01181 0.00546 -0.1122 0.3337 0.7469
6.250 1.1693 0.01244 0.00594 -0.1108 0.2957 0.7543
6.500 1.1859 0.01318 0.00649 -0.1092 0.2556 0.7626
6.750 1.2014 0.01394 0.00709 -0.1074 0.2173 0.7703
7.000 1.2170 0.01467 0.00768 -0.1056 0.1860 0.7789
7.250 1.2313 0.01538 0.00829 -0.1037 0.1578 0.7874
7.500 1.2431 0.01613 0.00891 -0.1013 0.1318 0.7971
7.750 1.2519 0.01688 0.00958 -0.0983 0.1090 0.8068
8.000 1.2612 0.01765 0.01029 -0.0956 0.0894 0.8175
8.500 1.2793 0.01925 0.01183 -0.0904 0.0615 0.8423
8.750 1.2886 0.02006 0.01265 -0.0879 0.0522 0.8567
9.000 1.2972 0.02089 0.01352 -0.0855 0.0453 0.8744
9.250 1.3053 0.02167 0.01436 -0.0829 0.0406 0.8994
9.500 1.3109 0.02237 0.01517 -0.0800 0.0377 0.9765
9.750 1.3237 0.02333 0.01615 -0.0787 0.0349 1.0000
10.000 1.3353 0.02441 0.01725 -0.0774 0.0324 1.0000
10.250 1.3479 0.02545 0.01833 -0.0762 0.0307 1.0000
10.500 1.3595 0.02660 0.01951 -0.0750 0.0291 1.0000
10.750 1.3694 0.02791 0.02085 -0.0738 0.0276 1.0000
11.000 1.3808 0.02914 0.02213 -0.0728 0.0264 1.0000
11.250 1.3916 0.03045 0.02350 -0.0718 0.0252 1.0000
11.500 1.4011 0.03190 0.02500 -0.0708 0.0240 1.0000
11.750 1.4089 0.03354 0.02667 -0.0698 0.0228 1.0000
12.000 1.4187 0.03504 0.02824 -0.0690 0.0219 1.0000
12.250 1.4280 0.03663 0.02989 -0.0682 0.0208 1.0000
12.500 1.4359 0.03839 0.03170 -0.0675 0.0198 1.0000
12.750 1.4419 0.04035 0.03371 -0.0667 0.0189 1.0000
13.000 1.4499 0.04218 0.03561 -0.0662 0.0181 1.0000
13.250 1.4571 0.04414 0.03764 -0.0656 0.0173 1.0000
13.500 1.4635 0.04622 0.03979 -0.0652 0.0165 1.0000
13.750 1.4688 0.04847 0.04209 -0.0648 0.0159 1.0000
14.000 1.4732 0.05090 0.04458 -0.0645 0.0153 1.0000
14.250 1.4785 0.05329 0.04707 -0.0643 0.0148 1.0000
14.500 1.4834 0.05579 0.04965 -0.0642 0.0143 1.0000
14.750 1.4875 0.05843 0.05236 -0.0642 0.0139 1.0000
15.000 1.4909 0.06121 0.05523 -0.0643 0.0134 1.0000
15.250 1.4936 0.06416 0.05825 -0.0646 0.0131 1.0000
15.500 1.4953 0.06731 0.06146 -0.0649 0.0128 1.0000
15.750 1.4959 0.07064 0.06488 -0.0653 0.0125 1.0000
16.000 1.4974 0.07393 0.06828 -0.0659 0.0123 1.0000
16.250 1.4981 0.07742 0.07187 -0.0665 0.0121 1.0000
16.500 1.4984 0.08103 0.07558 -0.0673 0.0119 1.0000
16.750 1.4982 0.08475 0.07940 -0.0682 0.0117 1.0000
17.000 1.4975 0.08862 0.08338 -0.0693 0.0115 1.0000
17.250 1.4962 0.09265 0.08750 -0.0704 0.0113 1.0000
17.500 1.4946 0.09679 0.09175 -0.0718 0.0112 1.0000
17.750 1.4927 0.10104 0.09609 -0.0732 0.0110 1.0000
18.000 1.4903 0.10540 0.10055 -0.0748 0.0109 1.0000
18.250 1.4872 0.10992 0.10519 -0.0765 0.0108 1.0000
18.500 1.4837 0.11461 0.10997 -0.0785 0.0106 1.0000
18.750 1.4796 0.11943 0.11489 -0.0806 0.0105 1.0000
19.000 1.4749 0.12440 0.11996 -0.0829 0.0104 1.0000
19.250 1.4697 0.12949 0.12514 -0.0853 0.0103 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 63(2)-615 (naca632615-il)