CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: CURTISS CR-1 AIRFOIL (cr1-il) Reynolds number: 200,000 Max Cl/Cd: 72.87 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cr1-il-200000-n5.txt Download as CSV file: xf-cr1-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CURTISS CR-1 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4970 0.03298 0.02794 -0.1120 0.9275 0.0410
-9.500 -0.4853 0.02971 0.02418 -0.1126 0.9186 0.0416
-9.250 -0.4626 0.02826 0.02258 -0.1130 0.9114 0.0423
-9.000 -0.4393 0.02703 0.02122 -0.1133 0.9045 0.0430
-8.750 -0.4176 0.02602 0.02006 -0.1130 0.8964 0.0438
-8.500 -0.3935 0.02491 0.01874 -0.1131 0.8904 0.0450
-8.250 -0.3753 0.02378 0.01737 -0.1119 0.8816 0.0460
-8.000 -0.3525 0.02257 0.01586 -0.1115 0.8754 0.0472
-7.750 -0.3330 0.02157 0.01460 -0.1103 0.8669 0.0480
-7.500 -0.3100 0.02070 0.01359 -0.1097 0.8604 0.0489
-7.250 -0.2870 0.02008 0.01290 -0.1089 0.8541 0.0500
-7.000 -0.2639 0.01956 0.01230 -0.1081 0.8472 0.0512
-6.750 -0.2384 0.01901 0.01160 -0.1077 0.8419 0.0530
-6.500 -0.2158 0.01844 0.01088 -0.1067 0.8349 0.0547
-6.250 -0.1916 0.01785 0.01013 -0.1060 0.8292 0.0562
-6.000 -0.1659 0.01735 0.00958 -0.1056 0.8247 0.0579
-5.750 -0.1426 0.01699 0.00918 -0.1047 0.8181 0.0599
-5.500 -0.1174 0.01660 0.00868 -0.1041 0.8128 0.0625
-5.250 -0.0907 0.01619 0.00815 -0.1038 0.8087 0.0655
-5.000 -0.0666 0.01593 0.00790 -0.1031 0.8029 0.0687
-4.750 -0.0410 0.01566 0.00754 -0.1025 0.7977 0.0726
-4.500 -0.0143 0.01534 0.00716 -0.1021 0.7936 0.0765
-4.250 0.0114 0.01516 0.00695 -0.1016 0.7888 0.0810
-4.000 0.0372 0.01497 0.00666 -0.1010 0.7836 0.0862
-3.750 0.0635 0.01477 0.00647 -0.1007 0.7792 0.0912
-3.500 0.0912 0.01461 0.00620 -0.1004 0.7754 0.0971
-3.250 0.1159 0.01443 0.00603 -0.0997 0.7700 0.1019
-3.000 0.1420 0.01430 0.00587 -0.0993 0.7651 0.1076
-2.750 0.1695 0.01415 0.00564 -0.0990 0.7608 0.1136
-2.500 0.1949 0.01402 0.00554 -0.0984 0.7554 0.1199
-2.250 0.2206 0.01392 0.00538 -0.0978 0.7493 0.1262
-2.000 0.2477 0.01375 0.00520 -0.0975 0.7441 0.1322
-1.750 0.2729 0.01366 0.00510 -0.0968 0.7379 0.1385
-1.500 0.2985 0.01354 0.00498 -0.0962 0.7318 0.1446
-1.250 0.3260 0.01344 0.00485 -0.0959 0.7267 0.1518
-1.000 0.3504 0.01337 0.00479 -0.0950 0.7200 0.1591
-0.750 0.3761 0.01328 0.00473 -0.0944 0.7138 0.1672
-0.500 0.4031 0.01322 0.00463 -0.0940 0.7084 0.1766
-0.250 0.4273 0.01317 0.00462 -0.0932 0.7015 0.1865
0.000 0.4533 0.01309 0.00455 -0.0926 0.6954 0.1964
0.250 0.4787 0.01306 0.00452 -0.0920 0.6890 0.2081
0.500 0.5031 0.01300 0.00451 -0.0911 0.6817 0.2197
0.750 0.5290 0.01294 0.00445 -0.0905 0.6750 0.2316
1.000 0.5524 0.01289 0.00445 -0.0895 0.6664 0.2433
1.500 0.6004 0.01276 0.00439 -0.0876 0.6473 0.2745
1.750 0.6230 0.01267 0.00437 -0.0864 0.6357 0.2959
2.000 0.6454 0.01255 0.00434 -0.0851 0.6232 0.3283
2.250 0.6649 0.01219 0.00434 -0.0834 0.6109 0.4512
2.750 0.8258 0.01152 0.00463 -0.1057 0.5669 1.0000
3.000 0.8459 0.01169 0.00467 -0.1039 0.5482 1.0000
3.250 0.8652 0.01189 0.00475 -0.1021 0.5278 1.0000
3.500 0.8839 0.01213 0.00486 -0.1002 0.5069 1.0000
3.750 0.9018 0.01240 0.00500 -0.0981 0.4865 1.0000
4.250 0.9362 0.01303 0.00538 -0.0938 0.4482 1.0000
4.500 0.9528 0.01336 0.00561 -0.0916 0.4303 1.0000
4.750 0.9691 0.01371 0.00585 -0.0893 0.4135 1.0000
5.000 0.9849 0.01406 0.00612 -0.0870 0.3972 1.0000
5.250 1.0003 0.01443 0.00640 -0.0846 0.3818 1.0000
5.500 1.0152 0.01481 0.00670 -0.0821 0.3673 1.0000
6.000 1.0444 0.01557 0.00734 -0.0772 0.3404 1.0000
6.250 1.0585 0.01595 0.00767 -0.0747 0.3289 1.0000
6.500 1.0700 0.01634 0.00801 -0.0716 0.3188 1.0000
6.750 1.0823 0.01672 0.00836 -0.0688 0.3085 1.0000
7.000 1.0948 0.01712 0.00874 -0.0660 0.2993 1.0000
7.250 1.1068 0.01756 0.00915 -0.0633 0.2902 1.0000
7.500 1.1207 0.01799 0.00956 -0.0610 0.2819 1.0000
7.750 1.1332 0.01848 0.01003 -0.0585 0.2742 1.0000
8.000 1.1477 0.01894 0.01051 -0.0564 0.2670 1.0000
8.250 1.1610 0.01947 0.01103 -0.0542 0.2601 1.0000
8.500 1.1750 0.02001 0.01156 -0.0521 0.2541 1.0000
8.750 1.1892 0.02055 0.01212 -0.0502 0.2474 1.0000
9.000 1.2011 0.02122 0.01276 -0.0480 0.2412 1.0000
9.250 1.2164 0.02176 0.01335 -0.0463 0.2350 1.0000
9.500 1.2297 0.02241 0.01400 -0.0444 0.2295 1.0000
9.750 1.2427 0.02311 0.01470 -0.0426 0.2250 1.0000
10.000 1.2583 0.02370 0.01537 -0.0411 0.2206 1.0000
10.250 1.2723 0.02438 0.01609 -0.0395 0.2163 1.0000
10.500 1.2848 0.02517 0.01688 -0.0378 0.2123 1.0000
10.750 1.2984 0.02589 0.01766 -0.0363 0.2070 1.0000
11.000 1.3109 0.02668 0.01850 -0.0347 0.2010 1.0000
11.500 1.3343 0.02843 0.02034 -0.0317 0.1899 1.0000
11.750 1.3453 0.02938 0.02132 -0.0302 0.1847 1.0000
12.000 1.3550 0.03044 0.02239 -0.0286 0.1803 1.0000
12.250 1.3676 0.03134 0.02342 -0.0274 0.1743 1.0000
12.500 1.3767 0.03249 0.02460 -0.0260 0.1691 1.0000
12.750 1.3862 0.03365 0.02582 -0.0247 0.1634 1.0000
13.000 1.3963 0.03479 0.02705 -0.0235 0.1575 1.0000
13.250 1.4025 0.03625 0.02853 -0.0222 0.1517 1.0000
13.500 1.4133 0.03741 0.02982 -0.0212 0.1451 1.0000
13.750 1.4183 0.03904 0.03148 -0.0200 0.1379 1.0000
14.000 1.4241 0.04069 0.03318 -0.0190 0.1263 1.0000
14.250 1.4276 0.04258 0.03508 -0.0179 0.1126 1.0000
14.500 1.4246 0.04513 0.03756 -0.0168 0.0958 1.0000
14.750 1.4175 0.04819 0.04056 -0.0158 0.0824 1.0000
15.000 1.4084 0.05159 0.04392 -0.0149 0.0683 1.0000
15.250 1.3945 0.05568 0.04794 -0.0143 0.0460 1.0000
15.500 1.3774 0.06035 0.05256 -0.0140 0.0355 1.0000
15.750 1.3650 0.06471 0.05697 -0.0140 0.0311 1.0000
16.000 1.3558 0.06886 0.06123 -0.0143 0.0288 1.0000
16.250 1.3443 0.07349 0.06597 -0.0149 0.0269 1.0000
16.500 1.3348 0.07799 0.07061 -0.0157 0.0259 1.0000
16.750 1.3245 0.08277 0.07553 -0.0167 0.0248 1.0000
17.000 1.3122 0.08797 0.08088 -0.0181 0.0240 1.0000
17.250 1.2993 0.09341 0.08646 -0.0196 0.0234 1.0000
17.500 1.2827 0.09956 0.09275 -0.0216 0.0227 1.0000
17.750 1.2671 0.10571 0.09904 -0.0238 0.0224 1.0000
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