Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Curtis C-72 (curtisc72-il) Reynolds number: 500,000 Max Cl/Cd: 95.45 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-curtisc72-il-500000-n5.txt Download as CSV file: xf-curtisc72-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.4430 0.14257 0.13999 -0.0214 1.0000 0.0138
-15.500 -0.4385 0.13894 0.13637 -0.0229 1.0000 0.0143
-14.000 -0.8123 0.03807 0.03490 -0.0883 1.0000 0.0201
-13.750 -0.8039 0.03634 0.03308 -0.0888 0.9986 0.0203
-13.500 -0.7782 0.03461 0.03124 -0.0918 0.9952 0.0206
-13.250 -0.7540 0.03276 0.02925 -0.0943 0.9913 0.0209
-13.000 -0.7293 0.03093 0.02723 -0.0966 0.9872 0.0213
-12.750 -0.7024 0.02911 0.02520 -0.0990 0.9843 0.0219
-12.500 -0.6789 0.02740 0.02327 -0.1002 0.9788 0.0225
-12.250 -0.6527 0.02570 0.02131 -0.1018 0.9748 0.0231
-12.000 -0.6272 0.02428 0.01964 -0.1026 0.9697 0.0235
-11.750 -0.6001 0.02327 0.01842 -0.1033 0.9643 0.0239
-11.500 -0.5735 0.02160 0.01658 -0.1044 0.9600 0.0244
-11.250 -0.5481 0.02067 0.01557 -0.1045 0.9532 0.0248
-11.000 -0.5196 0.01983 0.01464 -0.1051 0.9482 0.0252
-10.750 -0.4928 0.01906 0.01376 -0.1053 0.9417 0.0256
-10.500 -0.4653 0.01836 0.01297 -0.1055 0.9353 0.0261
-10.250 -0.4379 0.01770 0.01220 -0.1056 0.9291 0.0266
-10.000 -0.4115 0.01703 0.01141 -0.1054 0.9216 0.0271
-9.750 -0.3844 0.01635 0.01059 -0.1053 0.9153 0.0275
-9.500 -0.3585 0.01573 0.00986 -0.1050 0.9075 0.0279
-9.250 -0.3317 0.01516 0.00917 -0.1048 0.9007 0.0282
-9.000 -0.3054 0.01467 0.00858 -0.1044 0.8932 0.0286
-8.750 -0.2785 0.01427 0.00807 -0.1042 0.8860 0.0289
-8.500 -0.2517 0.01388 0.00760 -0.1038 0.8788 0.0292
-8.250 -0.2260 0.01315 0.00679 -0.1035 0.8711 0.0297
-8.000 -0.1997 0.01263 0.00621 -0.1031 0.8639 0.0302
-7.750 -0.1731 0.01221 0.00574 -0.1028 0.8559 0.0306
-7.500 -0.1461 0.01185 0.00532 -0.1025 0.8486 0.0311
-7.250 -0.1191 0.01153 0.00495 -0.1023 0.8403 0.0315
-7.000 -0.0919 0.01124 0.00460 -0.1020 0.8327 0.0321
-6.750 -0.0647 0.01097 0.00428 -0.1017 0.8241 0.0326
-6.500 -0.0373 0.01072 0.00397 -0.1015 0.8160 0.0332
-6.250 -0.0098 0.01051 0.00370 -0.1013 0.8071 0.0340
-6.000 0.0177 0.01031 0.00345 -0.1010 0.7980 0.0347
-5.750 0.0450 0.01015 0.00320 -0.1007 0.7875 0.0353
-5.500 0.0723 0.00996 0.00295 -0.1004 0.7750 0.0361
-5.250 0.0996 0.00979 0.00271 -0.1001 0.7619 0.0374
-5.000 0.1268 0.00966 0.00252 -0.0998 0.7486 0.0388
-4.750 0.1540 0.00956 0.00235 -0.0995 0.7343 0.0407
-4.500 0.1813 0.00948 0.00221 -0.0993 0.7213 0.0433
-4.250 0.2088 0.00935 0.00209 -0.0991 0.7105 0.0523
-4.000 0.2363 0.00921 0.00200 -0.0989 0.7006 0.0740
-3.750 0.2638 0.00911 0.00191 -0.0988 0.6903 0.0912
-3.500 0.2912 0.00900 0.00183 -0.0986 0.6795 0.1130
-3.250 0.3186 0.00882 0.00177 -0.0986 0.6699 0.1553
-3.000 0.3458 0.00869 0.00172 -0.0984 0.6598 0.1985
-2.750 0.3731 0.00853 0.00168 -0.0983 0.6486 0.2500
-2.500 0.4000 0.00832 0.00167 -0.0982 0.6372 0.3253
-2.250 0.4269 0.00821 0.00170 -0.0981 0.6262 0.3881
-2.000 0.4542 0.00816 0.00174 -0.0979 0.6150 0.4368
-1.750 0.4813 0.00813 0.00179 -0.0978 0.6035 0.4816
-1.500 0.5083 0.00813 0.00184 -0.0976 0.5909 0.5163
-1.250 0.5354 0.00817 0.00188 -0.0974 0.5773 0.5364
-1.000 0.5623 0.00822 0.00192 -0.0971 0.5636 0.5568
-0.750 0.5890 0.00824 0.00199 -0.0969 0.5499 0.5875
-0.500 0.6154 0.00824 0.00207 -0.0966 0.5356 0.6294
-0.250 0.6413 0.00823 0.00215 -0.0962 0.5198 0.6778
0.000 0.6661 0.00819 0.00224 -0.0956 0.5027 0.7385
0.250 0.6987 0.00787 0.00234 -0.0963 0.4843 1.0000
0.500 0.7248 0.00806 0.00244 -0.0960 0.4671 1.0000
0.750 0.7507 0.00826 0.00255 -0.0957 0.4488 1.0000
1.000 0.7763 0.00849 0.00267 -0.0954 0.4296 1.0000
1.250 0.8019 0.00872 0.00281 -0.0950 0.4117 1.0000
1.500 0.8275 0.00896 0.00295 -0.0947 0.3951 1.0000
1.750 0.8530 0.00921 0.00312 -0.0944 0.3788 1.0000
2.000 0.8782 0.00947 0.00329 -0.0941 0.3625 1.0000
2.250 0.9032 0.00976 0.00348 -0.0937 0.3459 1.0000
2.500 0.9284 0.01003 0.00368 -0.0934 0.3311 1.0000
2.750 0.9539 0.01027 0.00387 -0.0931 0.3193 1.0000
3.000 0.9793 0.01052 0.00407 -0.0928 0.3105 1.0000
3.250 1.0053 0.01071 0.00426 -0.0926 0.3037 1.0000
3.500 1.0307 0.01095 0.00448 -0.0924 0.2968 1.0000
3.750 1.0565 0.01115 0.00468 -0.0922 0.2897 1.0000
4.000 1.0815 0.01141 0.00492 -0.0919 0.2812 1.0000
4.250 1.1070 0.01162 0.00515 -0.0917 0.2735 1.0000
4.500 1.1317 0.01189 0.00539 -0.0914 0.2654 1.0000
4.750 1.1569 0.01212 0.00564 -0.0911 0.2574 1.0000
5.000 1.1812 0.01241 0.00592 -0.0907 0.2483 1.0000
5.250 1.2055 0.01269 0.00619 -0.0904 0.2378 1.0000
5.500 1.2289 0.01303 0.00650 -0.0899 0.2238 1.0000
5.750 1.2504 0.01351 0.00687 -0.0892 0.2021 1.0000
6.000 1.2697 0.01414 0.00735 -0.0881 0.1742 1.0000
6.250 1.2873 0.01489 0.00792 -0.0869 0.1462 1.0000
6.500 1.3052 0.01560 0.00849 -0.0857 0.1237 1.0000
6.750 1.3241 0.01619 0.00903 -0.0846 0.1102 1.0000
7.000 1.3434 0.01673 0.00954 -0.0836 0.1006 1.0000
7.250 1.3615 0.01730 0.01008 -0.0823 0.0923 1.0000
7.500 1.3788 0.01783 0.01061 -0.0810 0.0853 1.0000
7.750 1.3955 0.01839 0.01118 -0.0796 0.0790 1.0000
8.000 1.4111 0.01903 0.01181 -0.0780 0.0715 1.0000
8.250 1.4267 0.01967 0.01245 -0.0766 0.0638 1.0000
8.500 1.4398 0.02047 0.01321 -0.0749 0.0535 1.0000
8.750 1.4499 0.02147 0.01414 -0.0728 0.0421 1.0000
9.000 1.4595 0.02253 0.01517 -0.0708 0.0334 1.0000
9.250 1.4690 0.02362 0.01627 -0.0690 0.0276 1.0000
9.500 1.4783 0.02476 0.01743 -0.0672 0.0235 1.0000
9.750 1.4882 0.02589 0.01860 -0.0656 0.0206 1.0000
10.000 1.4973 0.02711 0.01987 -0.0641 0.0186 1.0000
10.250 1.5066 0.02836 0.02118 -0.0627 0.0172 1.0000
10.500 1.5141 0.02978 0.02267 -0.0613 0.0160 1.0000
10.750 1.5215 0.03127 0.02423 -0.0600 0.0152 1.0000
11.000 1.5291 0.03279 0.02584 -0.0589 0.0145 1.0000
11.250 1.5352 0.03449 0.02761 -0.0578 0.0138 1.0000
11.500 1.5397 0.03639 0.02959 -0.0568 0.0132 1.0000
11.750 1.5424 0.03854 0.03182 -0.0558 0.0126 1.0000
12.000 1.5435 0.04091 0.03428 -0.0550 0.0122 1.0000
12.250 1.5468 0.04314 0.03662 -0.0544 0.0118 1.0000
12.500 1.5484 0.04563 0.03922 -0.0539 0.0115 1.0000
12.750 1.5487 0.04832 0.04202 -0.0535 0.0112 1.0000
13.000 1.5477 0.05126 0.04507 -0.0534 0.0109 1.0000
13.250 1.5455 0.05446 0.04838 -0.0534 0.0106 1.0000
13.500 1.5420 0.05794 0.05196 -0.0535 0.0104 1.0000
13.750 1.5367 0.06173 0.05587 -0.0539 0.0102 1.0000
14.000 1.5301 0.06586 0.06011 -0.0545 0.0100 1.0000
14.250 1.5216 0.07037 0.06473 -0.0553 0.0098 1.0000
14.500 1.5111 0.07526 0.06975 -0.0564 0.0097 1.0000
14.750 1.4987 0.08057 0.07518 -0.0577 0.0096 1.0000
15.000 1.4872 0.08591 0.08064 -0.0592 0.0094 1.0000
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