CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CURTISS CR-1 AIRFOIL (cr1-il) Reynolds number: 200,000 Max Cl/Cd: 79.14 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cr1-il-200000.txt Download as CSV file: xf-cr1-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2863 0.11715 0.11363 -0.0392 1.0000 0.0722
-10.250 -0.3168 0.11737 0.11397 -0.0366 1.0000 0.0739
-10.000 -0.3310 0.11325 0.10988 -0.0480 0.9948 0.0748
-9.750 -0.3015 0.10793 0.10453 -0.0461 0.9937 0.0758
-9.500 -0.2728 0.10478 0.10135 -0.0465 0.9910 0.0775
-9.250 -0.2521 0.10136 0.09792 -0.0499 0.9868 0.0798
-9.000 -0.2355 0.09731 0.09385 -0.0559 0.9829 0.0833
-8.750 -0.2519 0.09049 0.08706 -0.0762 0.9699 0.0862
-8.500 -0.2209 0.08647 0.08301 -0.0725 0.9698 0.0873
-8.250 -0.1941 0.08407 0.08059 -0.0720 0.9655 0.0888
-8.000 -0.1721 0.08108 0.07758 -0.0748 0.9604 0.0912
-7.750 -0.1524 0.07691 0.07338 -0.0817 0.9561 0.0948
-7.250 -0.1904 0.04655 0.04240 -0.1146 0.9266 0.0743
-7.000 -0.1892 0.04069 0.03627 -0.1156 0.9171 0.0736
-6.750 -0.1917 0.03309 0.02800 -0.1161 0.9093 0.0730
-6.500 -0.1917 0.02907 0.02338 -0.1133 0.8995 0.0734
-6.250 -0.1749 0.02633 0.02004 -0.1123 0.8941 0.0745
-6.000 -0.1528 0.02449 0.01799 -0.1120 0.8897 0.0765
-5.750 -0.1344 0.02411 0.01759 -0.1104 0.8822 0.0784
-5.500 -0.1079 0.02319 0.01650 -0.1102 0.8779 0.0808
-5.250 -0.0800 0.02197 0.01497 -0.1102 0.8748 0.0837
-5.000 -0.0652 0.02143 0.01415 -0.1077 0.8669 0.0859
-4.750 -0.0394 0.02046 0.01319 -0.1074 0.8624 0.0895
-4.500 -0.0096 0.02004 0.01268 -0.1076 0.8592 0.0943
-4.250 0.0106 0.01980 0.01220 -0.1059 0.8530 0.0986
-4.000 0.0344 0.01906 0.01152 -0.1053 0.8478 0.1038
-3.750 0.0635 0.01871 0.01104 -0.1052 0.8440 0.1107
-3.500 0.0922 0.01821 0.01052 -0.1052 0.8406 0.1180
-3.250 0.1109 0.01818 0.01045 -0.1034 0.8335 0.1246
-3.000 0.1387 0.01771 0.00995 -0.1032 0.8290 0.1316
-2.750 0.1700 0.01748 0.00964 -0.1035 0.8255 0.1400
-2.500 0.1899 0.01732 0.00950 -0.1020 0.8184 0.1465
-2.250 0.2175 0.01718 0.00933 -0.1016 0.8131 0.1547
-2.000 0.2489 0.01680 0.00891 -0.1019 0.8093 0.1626
-1.750 0.2700 0.01679 0.00891 -0.1005 0.8022 0.1696
-1.500 0.2979 0.01647 0.00855 -0.1001 0.7967 0.1772
-1.250 0.3297 0.01617 0.00823 -0.1005 0.7926 0.1857
-1.000 0.3507 0.01607 0.00813 -0.0990 0.7850 0.1933
-0.750 0.3792 0.01581 0.00788 -0.0988 0.7795 0.2029
-0.500 0.4093 0.01549 0.00756 -0.0989 0.7747 0.2134
-0.250 0.4310 0.01542 0.00751 -0.0975 0.7670 0.2251
0.000 0.4605 0.01513 0.00722 -0.0974 0.7616 0.2396
0.250 0.4850 0.01494 0.00712 -0.0966 0.7549 0.2550
0.500 0.5105 0.01473 0.00696 -0.0958 0.7478 0.2729
0.750 0.5407 0.01440 0.00668 -0.0959 0.7423 0.2940
1.000 0.5606 0.01425 0.00668 -0.0942 0.7333 0.3146
1.250 0.5898 0.01387 0.00639 -0.0941 0.7268 0.3489
1.500 0.6058 0.01341 0.00639 -0.0916 0.7167 0.4494
1.750 0.7595 0.01202 0.00601 -0.1174 0.7038 1.0000
2.000 0.7844 0.01202 0.00590 -0.1164 0.6949 1.0000
2.250 0.8056 0.01209 0.00593 -0.1148 0.6846 1.0000
2.500 0.8314 0.01208 0.00581 -0.1140 0.6758 1.0000
2.750 0.8513 0.01213 0.00584 -0.1122 0.6639 1.0000
3.000 0.8729 0.01216 0.00584 -0.1107 0.6524 1.0000
3.250 0.8955 0.01217 0.00579 -0.1093 0.6406 1.0000
3.500 0.9172 0.01220 0.00576 -0.1078 0.6277 1.0000
3.750 0.9372 0.01226 0.00579 -0.1060 0.6127 1.0000
4.000 0.9574 0.01233 0.00581 -0.1042 0.5964 1.0000
4.250 0.9771 0.01243 0.00583 -0.1023 0.5787 1.0000
4.500 0.9953 0.01259 0.00592 -0.1002 0.5583 1.0000
4.750 1.0130 0.01280 0.00602 -0.0980 0.5365 1.0000
5.000 1.0297 0.01308 0.00615 -0.0956 0.5141 1.0000
5.250 1.0452 0.01341 0.00636 -0.0931 0.4907 1.0000
5.500 1.0599 0.01381 0.00661 -0.0905 0.4686 1.0000
5.750 1.0742 0.01424 0.00691 -0.0878 0.4476 1.0000
6.000 1.0881 0.01468 0.00724 -0.0851 0.4279 1.0000
6.250 1.1015 0.01514 0.00760 -0.0824 0.4096 1.0000
6.500 1.1147 0.01562 0.00798 -0.0797 0.3929 1.0000
6.750 1.1276 0.01611 0.00839 -0.0769 0.3771 1.0000
7.000 1.1403 0.01662 0.00882 -0.0742 0.3626 1.0000
7.250 1.1522 0.01715 0.00926 -0.0713 0.3496 1.0000
7.500 1.1633 0.01768 0.00969 -0.0683 0.3378 1.0000
7.750 1.1752 0.01815 0.01017 -0.0654 0.3265 1.0000
8.000 1.1885 0.01871 0.01066 -0.0629 0.3167 1.0000
8.250 1.2018 0.01924 0.01115 -0.0605 0.3073 1.0000
8.500 1.2164 0.01978 0.01168 -0.0584 0.2988 1.0000
8.750 1.2309 0.02034 0.01219 -0.0563 0.2909 1.0000
9.000 1.2462 0.02090 0.01277 -0.0543 0.2834 1.0000
9.250 1.2613 0.02145 0.01332 -0.0524 0.2766 1.0000
9.500 1.2798 0.02208 0.01390 -0.0511 0.2708 1.0000
9.750 1.2953 0.02262 0.01454 -0.0493 0.2652 1.0000
10.000 1.3124 0.02321 0.01511 -0.0479 0.2600 1.0000
10.250 1.3293 0.02385 0.01576 -0.0464 0.2545 1.0000
10.500 1.3414 0.02442 0.01642 -0.0443 0.2489 1.0000
10.750 1.3561 0.02506 0.01702 -0.0427 0.2431 1.0000
11.000 1.3677 0.02574 0.01779 -0.0406 0.2375 1.0000
11.250 1.3784 0.02640 0.01853 -0.0386 0.2320 1.0000
11.500 1.3942 0.02712 0.01917 -0.0372 0.2264 1.0000
11.750 1.4021 0.02789 0.02012 -0.0350 0.2215 1.0000
12.000 1.4118 0.02867 0.02098 -0.0331 0.2164 1.0000
12.250 1.4257 0.02948 0.02171 -0.0317 0.2109 1.0000
12.500 1.4316 0.03043 0.02286 -0.0295 0.2062 1.0000
12.750 1.4382 0.03141 0.02393 -0.0276 0.2006 1.0000
13.000 1.4504 0.03234 0.02480 -0.0262 0.1957 1.0000
13.250 1.4545 0.03352 0.02621 -0.0243 0.1907 1.0000
13.500 1.4596 0.03475 0.02753 -0.0227 0.1851 1.0000
13.750 1.4648 0.03607 0.02887 -0.0211 0.1794 1.0000
14.000 1.4676 0.03757 0.03056 -0.0196 0.1727 1.0000
14.250 1.4699 0.03922 0.03219 -0.0182 0.1665 1.0000
14.500 1.4727 0.04094 0.03414 -0.0171 0.1584 1.0000
14.750 1.4725 0.04302 0.03629 -0.0160 0.1491 1.0000
15.000 1.4711 0.04539 0.03876 -0.0152 0.1342 1.0000
15.250 1.4645 0.04844 0.04176 -0.0144 0.1095 1.0000
15.500 1.4451 0.05294 0.04605 -0.0137 0.0852 1.0000
15.750 1.4256 0.05773 0.05076 -0.0131 0.0674 1.0000
16.000 1.4086 0.06250 0.05550 -0.0130 0.0529 1.0000
16.250 1.3906 0.06764 0.06063 -0.0133 0.0458 1.0000
16.500 1.3757 0.07267 0.06573 -0.0139 0.0426 1.0000
16.750 1.3600 0.07799 0.07116 -0.0149 0.0404 1.0000
17.000 1.3435 0.08365 0.07694 -0.0162 0.0389 1.0000
17.250 1.3263 0.08961 0.08302 -0.0178 0.0380 1.0000
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