CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: CURTISS CR-1 AIRFOIL (cr1-il) Reynolds number: 100,000 Max Cl/Cd: 53 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cr1-il-100000-n5.txt Download as CSV file: xf-cr1-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3013 0.11752 0.11226 -0.0471 1.0000 0.0558
-10.750 -0.2996 0.11501 0.10979 -0.0462 1.0000 0.0555
-10.500 -0.3014 0.11270 0.10754 -0.0451 1.0000 0.0551
-10.250 -0.3097 0.11042 0.10534 -0.0439 1.0000 0.0551
-10.000 -0.3177 0.10748 0.10245 -0.0442 0.9988 0.0554
-9.750 -0.3138 0.10124 0.09620 -0.0507 0.9918 0.0559
-9.250 -0.2969 0.09122 0.08616 -0.0601 0.9779 0.0560
-9.000 -0.2894 0.08589 0.08081 -0.0654 0.9706 0.0560
-8.750 -0.2691 0.08418 0.07911 -0.0668 0.9638 0.0570
-8.500 -0.2490 0.08189 0.07680 -0.0696 0.9576 0.0587
-8.250 -0.2414 0.07748 0.07238 -0.0744 0.9488 0.0594
-8.000 -0.2349 0.07199 0.06687 -0.0813 0.9406 0.0599
-7.750 -0.2344 0.06602 0.06084 -0.0875 0.9288 0.0600
-7.500 -0.2341 0.05891 0.05359 -0.0945 0.9184 0.0604
-7.250 -0.2388 0.04901 0.04335 -0.1021 0.9085 0.0618
-7.000 -0.2729 0.03564 0.02874 -0.1041 0.8939 0.0644
-6.750 -0.2563 0.03354 0.02636 -0.1036 0.8876 0.0657
-6.500 -0.2367 0.03240 0.02508 -0.1029 0.8807 0.0669
-6.250 -0.2121 0.03083 0.02326 -0.1032 0.8764 0.0687
-6.000 -0.1954 0.02942 0.02155 -0.1018 0.8695 0.0711
-5.750 -0.1771 0.02754 0.01913 -0.1008 0.8634 0.0744
-5.500 -0.1490 0.02674 0.01826 -0.1011 0.8596 0.0768
-5.250 -0.1281 0.02616 0.01760 -0.1000 0.8536 0.0791
-5.000 -0.1063 0.02533 0.01654 -0.0990 0.8478 0.0824
-4.750 -0.0789 0.02434 0.01525 -0.0989 0.8439 0.0870
-4.500 -0.0521 0.02398 0.01490 -0.0988 0.8398 0.0908
-4.250 -0.0331 0.02355 0.01431 -0.0972 0.8329 0.0956
-4.000 -0.0060 0.02290 0.01350 -0.0970 0.8287 0.1007
-3.750 0.0244 0.02252 0.01309 -0.0974 0.8255 0.1068
-3.500 0.0432 0.02224 0.01262 -0.0957 0.8187 0.1131
-3.250 0.0685 0.02201 0.01245 -0.0952 0.8137 0.1191
-3.000 0.0989 0.02160 0.01185 -0.0954 0.8102 0.1274
-2.750 0.1216 0.02147 0.01179 -0.0945 0.8047 0.1334
-2.500 0.1452 0.02127 0.01148 -0.0935 0.7988 0.1407
-2.250 0.1747 0.02097 0.01119 -0.0937 0.7947 0.1478
-2.000 0.2022 0.02073 0.01087 -0.0934 0.7900 0.1556
-1.750 0.2236 0.02062 0.01077 -0.0921 0.7830 0.1621
-1.500 0.2540 0.02032 0.01042 -0.0922 0.7783 0.1707
-1.250 0.2802 0.02010 0.01020 -0.0917 0.7726 0.1783
-1.000 0.3039 0.01998 0.01006 -0.0907 0.7656 0.1873
-0.750 0.3353 0.01963 0.00971 -0.0910 0.7609 0.1967
-0.500 0.3580 0.01956 0.00960 -0.0899 0.7537 0.2071
0.000 0.4180 0.01897 0.00907 -0.0900 0.7425 0.2321
0.250 0.4373 0.01897 0.00912 -0.0883 0.7336 0.2440
0.500 0.4696 0.01868 0.00884 -0.0887 0.7279 0.2613
0.750 0.4933 0.01862 0.00885 -0.0878 0.7196 0.2786
1.000 0.5234 0.01839 0.00866 -0.0880 0.7127 0.3007
1.250 0.5497 0.01822 0.00861 -0.0875 0.7048 0.3302
1.500 0.5753 0.01789 0.00854 -0.0870 0.6966 0.3931
2.000 0.7215 0.01645 0.00826 -0.1047 0.6772 1.0000
2.250 0.7399 0.01659 0.00834 -0.1027 0.6651 1.0000
2.500 0.7609 0.01665 0.00832 -0.1010 0.6532 1.0000
2.750 0.7833 0.01667 0.00826 -0.0996 0.6411 1.0000
3.000 0.8041 0.01672 0.00824 -0.0979 0.6277 1.0000
3.250 0.8228 0.01684 0.00832 -0.0959 0.6130 1.0000
3.500 0.8421 0.01695 0.00838 -0.0940 0.5977 1.0000
3.750 0.8616 0.01706 0.00842 -0.0922 0.5819 1.0000
4.000 0.8814 0.01718 0.00846 -0.0903 0.5653 1.0000
4.250 0.9011 0.01732 0.00852 -0.0885 0.5480 1.0000
4.500 0.9199 0.01751 0.00861 -0.0866 0.5292 1.0000
4.750 0.9380 0.01775 0.00874 -0.0845 0.5101 1.0000
5.000 0.9556 0.01803 0.00890 -0.0824 0.4904 1.0000
5.250 0.9724 0.01836 0.00911 -0.0802 0.4711 1.0000
5.500 0.9885 0.01873 0.00936 -0.0780 0.4526 1.0000
5.750 1.0041 0.01914 0.00966 -0.0757 0.4354 1.0000
6.000 1.0192 0.01958 0.01001 -0.0733 0.4192 1.0000
6.250 1.0340 0.02004 0.01039 -0.0710 0.4039 1.0000
6.500 1.0486 0.02052 0.01080 -0.0686 0.3897 1.0000
6.750 1.0620 0.02101 0.01123 -0.0661 0.3761 1.0000
7.000 1.0748 0.02151 0.01168 -0.0635 0.3635 1.0000
7.250 1.0874 0.02205 0.01214 -0.0609 0.3515 1.0000
7.500 1.1004 0.02259 0.01266 -0.0585 0.3399 1.0000
7.750 1.1141 0.02315 0.01320 -0.0562 0.3294 1.0000
8.000 1.1279 0.02375 0.01374 -0.0541 0.3201 1.0000
8.250 1.1425 0.02434 0.01435 -0.0521 0.3109 1.0000
8.500 1.1575 0.02497 0.01493 -0.0502 0.3034 1.0000
8.750 1.1728 0.02559 0.01560 -0.0485 0.2955 1.0000
9.000 1.1882 0.02626 0.01623 -0.0468 0.2890 1.0000
9.250 1.2038 0.02691 0.01696 -0.0452 0.2820 1.0000
9.500 1.2191 0.02760 0.01766 -0.0435 0.2759 1.0000
9.750 1.2351 0.02831 0.01838 -0.0420 0.2701 1.0000
10.000 1.2501 0.02904 0.01920 -0.0405 0.2641 1.0000
10.250 1.2660 0.02977 0.01993 -0.0391 0.2592 1.0000
10.500 1.2819 0.03054 0.02075 -0.0377 0.2542 1.0000
10.750 1.2955 0.03135 0.02167 -0.0361 0.2487 1.0000
11.000 1.3099 0.03215 0.02249 -0.0346 0.2439 1.0000
11.250 1.3235 0.03301 0.02342 -0.0331 0.2390 1.0000
11.500 1.3345 0.03395 0.02449 -0.0314 0.2336 1.0000
11.750 1.3475 0.03484 0.02544 -0.0300 0.2292 1.0000
12.000 1.3616 0.03573 0.02635 -0.0287 0.2250 1.0000
12.250 1.3691 0.03688 0.02770 -0.0269 0.2199 1.0000
12.500 1.3762 0.03798 0.02888 -0.0251 0.2144 1.0000
12.750 1.3826 0.03917 0.03011 -0.0234 0.2088 1.0000
13.000 1.3850 0.04062 0.03174 -0.0215 0.2028 1.0000
13.250 1.3888 0.04197 0.03311 -0.0199 0.1970 1.0000
13.500 1.3903 0.04365 0.03495 -0.0183 0.1912 1.0000
13.750 1.3922 0.04534 0.03679 -0.0168 0.1856 1.0000
14.000 1.3941 0.04703 0.03850 -0.0155 0.1802 1.0000
14.250 1.3935 0.04914 0.04084 -0.0143 0.1744 1.0000
14.500 1.3929 0.05123 0.04304 -0.0133 0.1690 1.0000
14.750 1.3915 0.05354 0.04547 -0.0124 0.1635 1.0000
15.000 1.3877 0.05623 0.04835 -0.0117 0.1571 1.0000
15.250 1.3847 0.05887 0.05104 -0.0112 0.1520 1.0000
15.500 1.3800 0.06203 0.05447 -0.0110 0.1456 1.0000
15.750 1.3720 0.06555 0.05808 -0.0110 0.1390 1.0000
16.000 1.3637 0.06950 0.06226 -0.0113 0.1314 1.0000
16.250 1.3528 0.07384 0.06673 -0.0120 0.1245 1.0000
16.500 1.3394 0.07883 0.07189 -0.0130 0.1157 1.0000
16.750 1.3228 0.08449 0.07768 -0.0146 0.1066 1.0000
17.000 1.3028 0.09088 0.08414 -0.0166 0.0988 1.0000
17.250 1.2821 0.09762 0.09095 -0.0190 0.0929 1.0000
17.500 1.2602 0.10479 0.09820 -0.0217 0.0872 1.0000
17.750 1.2390 0.11203 0.10553 -0.0247 0.0823 1.0000
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