Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Curtis C-72 (curtisc72-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.45 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-curtisc72-il-1000000-n5.txt Download as CSV file: xf-curtisc72-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Curtis C-72
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.0971 0.03634 0.03346 -0.0975 1.0000 0.0147
-17.000 -1.1099 0.03121 0.02814 -0.1032 1.0000 0.0148
-16.750 -1.1059 0.02942 0.02623 -0.1028 1.0000 0.0151
-16.500 -1.0996 0.02798 0.02468 -0.1015 1.0000 0.0154
-16.250 -1.0914 0.02674 0.02333 -0.1000 1.0000 0.0156
-16.000 -1.0819 0.02565 0.02214 -0.0982 1.0000 0.0158
-15.750 -1.0589 0.02457 0.02097 -0.0988 0.9987 0.0162
-15.500 -1.0301 0.02383 0.02019 -0.0998 0.9969 0.0165
-15.250 -1.0004 0.02324 0.01956 -0.1008 0.9952 0.0168
-15.000 -0.9702 0.02268 0.01896 -0.1018 0.9938 0.0171
-14.750 -0.9421 0.02216 0.01840 -0.1023 0.9911 0.0175
-14.500 -0.9129 0.02161 0.01779 -0.1031 0.9886 0.0179
-14.250 -0.8831 0.02101 0.01712 -0.1040 0.9864 0.0183
-14.000 -0.8532 0.02032 0.01634 -0.1049 0.9844 0.0187
-13.750 -0.8271 0.01965 0.01557 -0.1051 0.9795 0.0190
-13.500 -0.7984 0.01902 0.01485 -0.1057 0.9755 0.0193
-13.250 -0.7690 0.01852 0.01426 -0.1062 0.9718 0.0195
-13.000 -0.7429 0.01775 0.01340 -0.1064 0.9655 0.0198
-12.750 -0.7146 0.01707 0.01266 -0.1068 0.9603 0.0202
-12.500 -0.6878 0.01662 0.01216 -0.1068 0.9527 0.0205
-12.250 -0.6596 0.01626 0.01176 -0.1069 0.9458 0.0208
-12.000 -0.6329 0.01591 0.01135 -0.1067 0.9373 0.0211
-11.750 -0.6062 0.01551 0.01087 -0.1065 0.9296 0.0214
-11.500 -0.5800 0.01511 0.01040 -0.1061 0.9211 0.0217
-11.250 -0.5536 0.01474 0.00994 -0.1058 0.9136 0.0221
-11.000 -0.5275 0.01433 0.00945 -0.1055 0.9057 0.0225
-10.750 -0.5013 0.01390 0.00892 -0.1051 0.8986 0.0228
-10.500 -0.4748 0.01351 0.00845 -0.1048 0.8911 0.0231
-10.250 -0.4482 0.01319 0.00805 -0.1045 0.8841 0.0234
-10.000 -0.4213 0.01286 0.00765 -0.1042 0.8771 0.0236
-9.750 -0.3945 0.01253 0.00724 -0.1039 0.8698 0.0238
-9.500 -0.3675 0.01222 0.00685 -0.1036 0.8629 0.0239
-9.250 -0.3412 0.01173 0.00629 -0.1033 0.8553 0.0242
-9.000 -0.3149 0.01122 0.00570 -0.1030 0.8482 0.0246
-8.750 -0.2880 0.01086 0.00529 -0.1027 0.8401 0.0250
-8.500 -0.2608 0.01058 0.00497 -0.1024 0.8327 0.0254
-8.250 -0.2334 0.01032 0.00465 -0.1022 0.8243 0.0257
-8.000 -0.2061 0.01008 0.00435 -0.1020 0.8164 0.0260
-7.750 -0.1786 0.00985 0.00406 -0.1017 0.8074 0.0263
-7.500 -0.1510 0.00963 0.00380 -0.1015 0.7990 0.0266
-7.250 -0.1235 0.00943 0.00354 -0.1013 0.7897 0.0270
-7.000 -0.0958 0.00925 0.00330 -0.1011 0.7802 0.0273
-6.750 -0.0683 0.00909 0.00307 -0.1008 0.7695 0.0277
-6.250 -0.0134 0.00883 0.00267 -0.1003 0.7431 0.0284
-6.000 0.0142 0.00872 0.00250 -0.1001 0.7299 0.0287
-5.750 0.0418 0.00864 0.00235 -0.0998 0.7164 0.0291
-5.500 0.0692 0.00854 0.00217 -0.0996 0.7014 0.0297
-5.250 0.0967 0.00843 0.00200 -0.0994 0.6882 0.0305
-5.000 0.1244 0.00835 0.00187 -0.0992 0.6770 0.0313
-4.750 0.1524 0.00826 0.00175 -0.0991 0.6666 0.0322
-4.500 0.1803 0.00820 0.00165 -0.0990 0.6567 0.0331
-4.250 0.2084 0.00815 0.00156 -0.0989 0.6469 0.0342
-4.000 0.2364 0.00810 0.00148 -0.0988 0.6374 0.0354
-3.750 0.2642 0.00806 0.00141 -0.0986 0.6265 0.0398
-3.500 0.2919 0.00795 0.00135 -0.0986 0.6147 0.0607
-3.250 0.3198 0.00788 0.00131 -0.0985 0.6042 0.0776
-3.000 0.3476 0.00784 0.00128 -0.0984 0.5939 0.0915
-2.750 0.3753 0.00777 0.00125 -0.0984 0.5825 0.1145
-2.500 0.4029 0.00767 0.00123 -0.0983 0.5703 0.1546
-2.250 0.4302 0.00756 0.00122 -0.0983 0.5569 0.2053
-2.000 0.4575 0.00749 0.00123 -0.0982 0.5435 0.2507
-1.750 0.4848 0.00740 0.00125 -0.0982 0.5307 0.3070
-1.500 0.5119 0.00732 0.00129 -0.0981 0.5170 0.3697
-1.250 0.5390 0.00728 0.00135 -0.0980 0.5022 0.4255
-1.000 0.5661 0.00732 0.00143 -0.0979 0.4855 0.4667
-0.750 0.5931 0.00739 0.00150 -0.0978 0.4673 0.4937
-0.500 0.6202 0.00749 0.00157 -0.0976 0.4499 0.5117
-0.250 0.6473 0.00760 0.00166 -0.0975 0.4329 0.5324
0.000 0.6741 0.00770 0.00175 -0.0974 0.4148 0.5559
0.250 0.7006 0.00780 0.00187 -0.0972 0.3965 0.5899
0.500 0.7271 0.00788 0.00199 -0.0971 0.3803 0.6288
1.000 0.7797 0.00800 0.00224 -0.0967 0.3524 0.7168
1.250 0.8077 0.00763 0.00240 -0.0966 0.3369 1.0000
1.500 0.8339 0.00785 0.00253 -0.0964 0.3220 1.0000
1.750 0.8602 0.00804 0.00266 -0.0963 0.3108 1.0000
2.000 0.8870 0.00820 0.00278 -0.0962 0.3016 1.0000
2.250 0.9135 0.00839 0.00292 -0.0960 0.2926 1.0000
2.500 0.9404 0.00853 0.00304 -0.0960 0.2863 1.0000
2.750 0.9668 0.00871 0.00319 -0.0959 0.2799 1.0000
3.000 0.9937 0.00886 0.00332 -0.0958 0.2733 1.0000
3.250 1.0198 0.00906 0.00349 -0.0957 0.2650 1.0000
3.500 1.0464 0.00922 0.00364 -0.0956 0.2587 1.0000
3.750 1.0724 0.00942 0.00381 -0.0955 0.2508 1.0000
4.000 1.0987 0.00960 0.00398 -0.0954 0.2435 1.0000
4.250 1.1242 0.00984 0.00418 -0.0952 0.2341 1.0000
4.500 1.1498 0.01006 0.00437 -0.0950 0.2240 1.0000
4.750 1.1745 0.01035 0.00461 -0.0947 0.2103 1.0000
5.000 1.1970 0.01082 0.00494 -0.0941 0.1849 1.0000
5.250 1.2182 0.01138 0.00534 -0.0933 0.1579 1.0000
5.500 1.2391 0.01196 0.00577 -0.0924 0.1337 1.0000
5.750 1.2604 0.01250 0.00619 -0.0917 0.1135 1.0000
6.000 1.2816 0.01302 0.00661 -0.0909 0.0978 1.0000
6.250 1.3043 0.01341 0.00697 -0.0903 0.0897 1.0000
6.500 1.3263 0.01383 0.00735 -0.0897 0.0825 1.0000
6.750 1.3490 0.01418 0.00770 -0.0892 0.0769 1.0000
7.000 1.3701 0.01463 0.00812 -0.0884 0.0699 1.0000
7.250 1.3915 0.01504 0.00852 -0.0877 0.0635 1.0000
7.500 1.4108 0.01557 0.00900 -0.0867 0.0538 1.0000
7.750 1.4267 0.01630 0.00963 -0.0851 0.0404 1.0000
8.000 1.4407 0.01701 0.01028 -0.0833 0.0308 1.0000
8.250 1.4550 0.01770 0.01094 -0.0814 0.0246 1.0000
8.500 1.4698 0.01834 0.01158 -0.0798 0.0204 1.0000
8.750 1.4845 0.01899 0.01224 -0.0782 0.0176 1.0000
9.000 1.4985 0.01969 0.01296 -0.0765 0.0155 1.0000
9.250 1.5133 0.02035 0.01365 -0.0751 0.0144 1.0000
9.500 1.5267 0.02111 0.01444 -0.0735 0.0132 1.0000
9.750 1.5394 0.02193 0.01529 -0.0720 0.0122 1.0000
10.000 1.5530 0.02271 0.01613 -0.0706 0.0116 1.0000
10.250 1.5656 0.02359 0.01706 -0.0692 0.0111 1.0000
10.500 1.5771 0.02457 0.01808 -0.0678 0.0105 1.0000
10.750 1.5875 0.02566 0.01921 -0.0664 0.0100 1.0000
11.000 1.5965 0.02689 0.02050 -0.0650 0.0095 1.0000
11.250 1.6070 0.02804 0.02171 -0.0638 0.0093 1.0000
11.500 1.6166 0.02929 0.02302 -0.0627 0.0090 1.0000
11.750 1.6253 0.03066 0.02447 -0.0616 0.0087 1.0000
12.000 1.6328 0.03217 0.02604 -0.0605 0.0084 1.0000
12.250 1.6394 0.03380 0.02774 -0.0595 0.0082 1.0000
12.500 1.6447 0.03561 0.02961 -0.0586 0.0079 1.0000
12.750 1.6486 0.03762 0.03168 -0.0577 0.0076 1.0000
13.000 1.6505 0.03987 0.03401 -0.0569 0.0073 1.0000
13.250 1.6523 0.04222 0.03645 -0.0563 0.0072 1.0000
13.500 1.6549 0.04457 0.03887 -0.0558 0.0070 1.0000
13.750 1.6563 0.04710 0.04150 -0.0555 0.0069 1.0000
14.000 1.6563 0.04988 0.04437 -0.0553 0.0068 1.0000
14.250 1.6553 0.05288 0.04747 -0.0553 0.0067 1.0000
14.500 1.6532 0.05611 0.05079 -0.0554 0.0065 1.0000
14.750 1.6499 0.05956 0.05433 -0.0556 0.0064 1.0000
15.000 1.6449 0.06333 0.05821 -0.0561 0.0063 1.0000
15.250 1.6389 0.06733 0.06230 -0.0567 0.0062 1.0000
15.500 1.6315 0.07163 0.06671 -0.0575 0.0061 1.0000
15.750 1.6224 0.07623 0.07141 -0.0585 0.0060 1.0000
16.000 1.6123 0.08110 0.07639 -0.0596 0.0060 1.0000
16.250 1.6007 0.08630 0.08170 -0.0610 0.0059 1.0000
16.500 1.5882 0.09169 0.08720 -0.0625 0.0058 1.0000
16.750 1.5740 0.09743 0.09306 -0.0643 0.0058 1.0000
17.000 1.5595 0.10333 0.09907 -0.0662 0.0057 1.0000
17.250 1.5445 0.10941 0.10527 -0.0683 0.0057 1.0000
17.500 1.5288 0.11564 0.11160 -0.0705 0.0056 1.0000
17.750 1.5135 0.12189 0.11796 -0.0730 0.0056 1.0000
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