CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CURTISS CR-1 AIRFOIL (cr1-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.87 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cr1-il-1000000.txt Download as CSV file: xf-cr1-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.3701 0.14184 0.14002 -0.0384 1.0000 0.0188
-14.250 -0.7533 0.06575 0.06353 -0.0779 1.0000 0.0256
-14.000 -0.9640 0.03198 0.02918 -0.1040 0.9944 0.0244
-13.750 -0.9425 0.02977 0.02682 -0.1064 0.9903 0.0249
-13.500 -0.9185 0.02800 0.02489 -0.1083 0.9862 0.0254
-13.250 -0.8903 0.02676 0.02352 -0.1102 0.9834 0.0257
-13.000 -0.8737 0.02466 0.02123 -0.1109 0.9766 0.0262
-12.750 -0.8512 0.02296 0.01942 -0.1120 0.9717 0.0267
-12.500 -0.8190 0.02214 0.01856 -0.1139 0.9693 0.0273
-12.250 -0.7907 0.02144 0.01780 -0.1148 0.9627 0.0278
-12.000 -0.7582 0.02066 0.01695 -0.1166 0.9579 0.0284
-11.750 -0.7266 0.01985 0.01603 -0.1182 0.9517 0.0289
-11.500 -0.6960 0.01915 0.01521 -0.1194 0.9434 0.0295
-11.250 -0.6668 0.01863 0.01457 -0.1202 0.9343 0.0300
-11.000 -0.6397 0.01811 0.01392 -0.1204 0.9247 0.0303
-10.750 -0.6224 0.01708 0.01271 -0.1190 0.9139 0.0308
-10.500 -0.6039 0.01620 0.01172 -0.1178 0.9046 0.0315
-10.250 -0.5822 0.01574 0.01119 -0.1168 0.8957 0.0321
-10.000 -0.5592 0.01539 0.01078 -0.1159 0.8877 0.0327
-9.750 -0.5366 0.01500 0.01031 -0.1150 0.8791 0.0333
-9.500 -0.5141 0.01458 0.00979 -0.1140 0.8710 0.0337
-9.250 -0.4914 0.01417 0.00929 -0.1130 0.8624 0.0343
-9.000 -0.4681 0.01379 0.00881 -0.1121 0.8543 0.0347
-8.750 -0.4438 0.01353 0.00846 -0.1113 0.8454 0.0353
-8.500 -0.4196 0.01324 0.00808 -0.1105 0.8369 0.0355
-8.250 -0.3995 0.01250 0.00721 -0.1091 0.8274 0.0364
-8.000 -0.3767 0.01203 0.00668 -0.1081 0.8188 0.0372
-7.750 -0.3527 0.01171 0.00628 -0.1073 0.8103 0.0378
-7.500 -0.3279 0.01143 0.00594 -0.1066 0.8023 0.0385
-7.250 -0.3031 0.01118 0.00562 -0.1059 0.7946 0.0393
-7.000 -0.2777 0.01093 0.00531 -0.1053 0.7881 0.0400
-6.750 -0.2520 0.01073 0.00504 -0.1047 0.7815 0.0408
-6.500 -0.2262 0.01058 0.00480 -0.1041 0.7756 0.0414
-6.250 -0.2015 0.01018 0.00435 -0.1034 0.7703 0.0428
-6.000 -0.1760 0.00992 0.00406 -0.1028 0.7650 0.0442
-5.750 -0.1500 0.00975 0.00384 -0.1023 0.7600 0.0456
-5.500 -0.1234 0.00957 0.00363 -0.1019 0.7558 0.0470
-5.250 -0.0967 0.00943 0.00346 -0.1015 0.7513 0.0482
-5.000 -0.0710 0.00917 0.00318 -0.1009 0.7470 0.0514
-4.750 -0.0444 0.00905 0.00302 -0.1005 0.7426 0.0545
-4.500 -0.0178 0.00886 0.00284 -0.1001 0.7388 0.0586
-4.250 0.0088 0.00871 0.00270 -0.0997 0.7342 0.0639
-4.000 0.0351 0.00858 0.00257 -0.0992 0.7291 0.0704
-3.750 0.0621 0.00853 0.00250 -0.0988 0.7243 0.0752
-3.500 0.0889 0.00840 0.00241 -0.0984 0.7201 0.0818
-3.250 0.1161 0.00836 0.00235 -0.0981 0.7155 0.0857
-3.000 0.1427 0.00829 0.00226 -0.0977 0.7109 0.0913
-2.750 0.1698 0.00823 0.00221 -0.0974 0.7068 0.0957
-2.500 0.1972 0.00819 0.00216 -0.0971 0.7026 0.0984
-2.250 0.2238 0.00808 0.00206 -0.0967 0.6984 0.1035
-2.000 0.2506 0.00804 0.00200 -0.0963 0.6942 0.1077
-1.750 0.2778 0.00799 0.00196 -0.0960 0.6904 0.1112
-1.500 0.3047 0.00791 0.00189 -0.0956 0.6859 0.1155
-1.250 0.3313 0.00784 0.00183 -0.0952 0.6814 0.1211
-1.000 0.3579 0.00783 0.00179 -0.0948 0.6763 0.1260
-0.750 0.3845 0.00773 0.00174 -0.0944 0.6711 0.1326
-0.500 0.4107 0.00768 0.00169 -0.0938 0.6641 0.1405
-0.250 0.4365 0.00762 0.00166 -0.0932 0.6565 0.1507
0.000 0.4627 0.00757 0.00164 -0.0927 0.6487 0.1625
0.250 0.4887 0.00756 0.00163 -0.0922 0.6420 0.1755
0.500 0.5152 0.00752 0.00163 -0.0918 0.6346 0.1882
0.750 0.5408 0.00752 0.00163 -0.0911 0.6272 0.1989
1.000 0.5674 0.00750 0.00163 -0.0908 0.6187 0.2079
1.250 0.5926 0.00751 0.00164 -0.0901 0.6094 0.2181
1.500 0.6181 0.00752 0.00165 -0.0894 0.5978 0.2265
1.750 0.6429 0.00755 0.00167 -0.0887 0.5846 0.2367
2.000 0.6666 0.00760 0.00170 -0.0877 0.5677 0.2488
2.250 0.6894 0.00769 0.00175 -0.0866 0.5489 0.2633
2.500 0.7117 0.00779 0.00182 -0.0854 0.5286 0.2838
2.750 0.7331 0.00786 0.00191 -0.0840 0.5073 0.3236
3.000 0.7401 0.00715 0.00208 -0.0799 0.4890 0.6920
3.250 0.8697 0.00739 0.00275 -0.1025 0.4442 0.9929
3.500 0.9331 0.00772 0.00290 -0.1105 0.4158 0.9994
3.750 0.9589 0.00794 0.00303 -0.1101 0.3971 1.0000
4.000 0.9793 0.00817 0.00317 -0.1086 0.3807 1.0000
4.250 0.9994 0.00839 0.00331 -0.1070 0.3653 1.0000
4.500 1.0193 0.00862 0.00347 -0.1054 0.3507 1.0000
4.750 1.0388 0.00886 0.00363 -0.1037 0.3365 1.0000
5.000 1.0586 0.00908 0.00379 -0.1021 0.3234 1.0000
5.250 1.0780 0.00931 0.00397 -0.1004 0.3105 1.0000
5.500 1.0967 0.00956 0.00415 -0.0986 0.2976 1.0000
5.750 1.1148 0.00982 0.00435 -0.0966 0.2856 1.0000
6.000 1.1318 0.01011 0.00457 -0.0945 0.2719 1.0000
6.250 1.1491 0.01037 0.00478 -0.0924 0.2599 1.0000
6.500 1.1664 0.01062 0.00499 -0.0903 0.2499 1.0000
6.750 1.1823 0.01091 0.00523 -0.0880 0.2405 1.0000
7.000 1.1991 0.01115 0.00544 -0.0858 0.2327 1.0000
7.250 1.2120 0.01143 0.00569 -0.0829 0.2249 1.0000
7.500 1.2243 0.01165 0.00589 -0.0798 0.2182 1.0000
7.750 1.2348 0.01195 0.00615 -0.0764 0.2101 1.0000
8.000 1.2493 0.01218 0.00638 -0.0739 0.2046 1.0000
8.250 1.2625 0.01250 0.00667 -0.0712 0.1989 1.0000
8.500 1.2776 0.01279 0.00696 -0.0689 0.1945 1.0000
8.750 1.2938 0.01306 0.00724 -0.0668 0.1902 1.0000
9.000 1.3090 0.01340 0.00758 -0.0647 0.1858 1.0000
9.250 1.3232 0.01381 0.00797 -0.0625 0.1807 1.0000
9.500 1.3412 0.01409 0.00828 -0.0609 0.1776 1.0000
9.750 1.3573 0.01446 0.00866 -0.0591 0.1733 1.0000
10.000 1.3723 0.01492 0.00910 -0.0572 0.1691 1.0000
10.250 1.3885 0.01533 0.00953 -0.0555 0.1652 1.0000
10.500 1.4056 0.01572 0.00994 -0.0540 0.1611 1.0000
10.750 1.4208 0.01622 0.01044 -0.0523 0.1566 1.0000
11.000 1.4353 0.01679 0.01101 -0.0506 0.1518 1.0000
11.250 1.4521 0.01724 0.01148 -0.0493 0.1464 1.0000
11.500 1.4650 0.01794 0.01215 -0.0475 0.1393 1.0000
11.750 1.4796 0.01854 0.01275 -0.0460 0.1313 1.0000
12.000 1.4870 0.01961 0.01370 -0.0437 0.1137 1.0000
12.250 1.4857 0.02125 0.01516 -0.0406 0.0886 1.0000
12.500 1.4870 0.02282 0.01664 -0.0380 0.0731 1.0000
12.750 1.4731 0.02552 0.01910 -0.0343 0.0398 1.0000
13.000 1.4686 0.02771 0.02123 -0.0316 0.0256 1.0000
13.250 1.4719 0.02939 0.02292 -0.0299 0.0209 1.0000
13.500 1.4759 0.03108 0.02464 -0.0282 0.0185 1.0000
13.750 1.4847 0.03242 0.02603 -0.0271 0.0176 1.0000
14.000 1.4898 0.03410 0.02776 -0.0257 0.0164 1.0000
14.250 1.4935 0.03594 0.02965 -0.0245 0.0156 1.0000
14.500 1.4990 0.03768 0.03146 -0.0234 0.0150 1.0000
14.750 1.5054 0.03937 0.03322 -0.0225 0.0145 1.0000
15.000 1.5096 0.04133 0.03524 -0.0215 0.0140 1.0000
15.250 1.5138 0.04331 0.03728 -0.0207 0.0135 1.0000
15.500 1.5136 0.04579 0.03982 -0.0199 0.0129 1.0000
15.750 1.5095 0.04879 0.04291 -0.0191 0.0125 1.0000
16.000 1.5101 0.05137 0.04557 -0.0186 0.0123 1.0000
16.250 1.5129 0.05374 0.04802 -0.0183 0.0120 1.0000
16.500 1.5110 0.05673 0.05110 -0.0180 0.0118 1.0000
16.750 1.5114 0.05953 0.05398 -0.0179 0.0114 1.0000
17.000 1.5078 0.06288 0.05742 -0.0180 0.0112 1.0000
17.250 1.5030 0.06647 0.06110 -0.0182 0.0111 1.0000
17.500 1.4963 0.07042 0.06514 -0.0186 0.0107 1.0000
17.750 1.4884 0.07464 0.06946 -0.0192 0.0107 1.0000
18.000 1.4776 0.07935 0.07427 -0.0201 0.0105 1.0000
18.250 1.4622 0.08483 0.07987 -0.0213 0.0104 1.0000
18.500 1.4485 0.09018 0.08533 -0.0227 0.0102 1.0000
18.750 1.4299 0.09641 0.09169 -0.0244 0.0101 1.0000
19.000 1.4069 0.10342 0.09884 -0.0266 0.0100 1.0000
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